semester v - ktu.edu.in

AERONAUTICAL ENGINEERING

SEMESTER V


AOT301 AIRCRAFT STRUCTURES II CATEGORY L T P CREDIT

PCC 3 1 0 4

Preamble: Basic aim of this course is to understand the behavior of major aircraft structural components and the various methods for analysis of aircraft wing and fuselage structures.

Prerequisite: Aircraft Structures I

Course Outcomes: After the completion of the course the student will be able to

CO1 Analyze bending stress in symmetrical & Unsymmetrical sections.

CO2 Analyze the shear flow in open section beams and Torsion ofnon-circular prismatic beams.

CO3 Analyze the shear flow in closed section beams.

CO4 Analyze the buckling behavior of plates, columns under various loads.

CO5 Analyze the aircraft wing and fuselage.

Mapping of course outcomes with program outcomes

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Assessment Pattern Bloom’s Category Continuous Assessment Tests End Semester Examination

1 2 Remember 10 10 10 Understand 20 20 20 Apply 20 20 70 Analyse Evaluate Create

Mark distribution

Total Marks CIE ESE ESE Duration 150 50 100 3 hours

AERONAUTICAL ENGINEERING Continuous Internal Evaluation Pattern:

Attendance : 10marks

Continuous Assessment Test(2numbers) : 25 marks

Assignment/Quiz/Courseproject : 15marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14marks. Course Level Assessment Questions

Course Outcome 1 (CO1):

1. Explain the unsymmetrical behavior in symmetrical cross-section with suitable example & Figures.

2. Figure shows the section of an angle purlin. A bending moment of 2.5KN m is applied to the purlin in a

plane at an angle of 30◦ to the vertical y axis. If the sense of the bending moment is such that its

components Mx and My both produce tension in the positive xy quadrant, calculate the maximum

direct stress at the point A & B. Note: Use NeutralAxis Method Only.

3. A beam having the cross-section shown in fig5 is subjected to a bending moment of Mx=15KN-m; My = 10

KN-m. Using Generalized K- method, Find the Maximum bending stress act at which point. (Given a = 20cm; b = 20cm; t1= 2cm; t2 = 2cm) `



1. A thin-walled channel section with thickness 3mm web height 10cm and flange width 5 cm is subjected to a vertical load of 5kn through the shear centre. Find the shear flow distribution and shear centre.

a. 2. Explain how the wing and fuselage of an aircraft is idealised for structural analysis. Also briefly

explain how idealised structure is analysed.

Course Outcome 3(CO3):

1. A multi cell structure as shown in Figure. Is subjected to a Torque = 75000 N-cm. Find the shear flow distribution around the section and the angle of twist per unit length. (Take E = 75GPa).

a.

2. A thin-walled closed section beam has the singly symmetrical cross-section shown in Fig. Each wall of the section is flat and has the same thickness t and shear modulus G. Calculate the distance of the shear centre from point 4.



1. A thin walled pin-ended column is 2m long and has the cross section as shown in fig 6. Determine the lowest value of axial load which cause buckling. (Take E= 70GPa.)

a. 2. Derive an expression for buckling stress for a thin plate under compression.


1. Explain the V-N Diagram.

2. The doubly symmetrical fuselage section shown in Fig. has been idealized into an arrangement of direct stress carrying booms and shear stress carrying skin panels; the boom areas are all 150 mm2. Calculate the direct stresses in the booms and the shear flows in the panels when the section is subjected to a shear load of 50 kN and a bending moment of 100 kN m.


Model Question Paper QP CODE: Reg No .:_______________

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY

FIFTH SEMESTER B.TECH DEGREE EXAMINATION, MONTH & YEAR

COURSE CODE: AOT301

COURSE NAME: AIRCRAFT STRUCTURES II

Max. Marks: 100 Duration: 3 hours

PART A

Answer all Questions.

(Each question carries 3 marks)

1. Explain the unsymmetrical behavior in symmetrical cross-section with suitable example & Figures.

2. Why in symmetrical cross-section both centroidal axis and principal axis coincide with each other. Justify your answer with proof.

3. Define Shear Centre.

4. Explain the concept of structural idealization.

5. Explain Bredt - Batho theory.

6. Explain Effective skin width.

7. What is the difference between buckling and crippling load?

8. Write the Euler’s formula for crippling load for the following end conditions.

AERONAUTICAL ENGINEERINGi) Both ends pinned ii) Both ends fixed iii) one end fixed one end free.

9. Draw V-n Diagram.

10. Explain the load path of wing structure.

PART B Answer one full question from each module.


Module -1

11. Determine the direct stress distribution in the thin-walled Z-section shown in Fig,produced by a

positive bending moment Mx.

(14)

(Or)

12. Figure shows the section of an angle purlin. A bending moment of 2.5KN m is applied to the purlin in a

plane at an angle of 30◦ to the vertical y axis. If the sense of the bending moment is such that its

components Mx and My both produce tension in the positive xy quadrant, calculate the maximum

direct stress at the point A & B. Note: Use Principal Axis Method Only. (14)


Module -2

13. The thin-walled Z-section shown in Fig. due to a shear load Sy =1000N applied through the shear

centre of the section. Also draw the shear flow distribution. (Where h = 12cm; t = 3mm).

(14)

(Or)

14. A beam has the singly symmetrical, thin-walled cross-section shown in Figure . Each wall of the

section is flat and has the same length a and thickness t. Calculate the distance of the shear centre

from the point 3.

AERONAUTICAL ENGINEERING(14)

Module -3

15. Find the shear flow in the web of the box as shown in figure 4. if the area is symmetrical about a

horizontal centerline. (14)

(Or)

16. The Aluminium (G = 27.1 GPa) hollow thin-wall torsion member in Fig has the dimensions shown. Its

length is 3.00 m. If the member is subjected to a torque T = 11.0 KN -m, determine the shear flow

distribution and angle of twist.

(14)

AERONAUTICAL ENGINEERINGModule -4

17. Find the buckling stress and margin of safety for the given Wing box panel as shown in figure. Is subjected

to a compression load P1 = 10,000N. (Given: KC = 4 ; Area of each stinger is 2cm2 ; Aspect ratio is 3;

thickness of skin is 1.5mm; E= 70GPa) Assume the skin is effective in bending.

(14)

(Or)

18. The beam shown in Fig. 8 is assumed to have a complete tension field web. If the cross-sectional

areas of the flanges and stiffeners are respectively, 350mm2 and 300mm2 and the elastic section

modulus of each flange is 750mm3. Determine the maximum stress in a flange and also whether or

not the stiffeners will buckle. Given:The thickness of the web is 2mm and the second moment of area

of a stiffener about an axis in the plane of the web is 2000mm4; E =70 000 N/mm2. (14)

Module -5

19. The box beam shown in fig 6 resists bending moments of Mz = 100KN-m and My = 12KN-m. Find the bending stress in each stringer member. Assume that the webs are ineffective in bending and the areas and coordinates of the stringers are as follows: (14)

AERONAUTICAL ENGINEERINGNo Area, mm2 Z, mm Y, mm 1 1,161.288 66.548 210.82 2 258.064 -274.574 231.648 3 516.128 -627.38 247.65 4 1,483.868 -627.38 -33.02 5 645.16 66.548 -30.48

(OR)

20. Find the maximum bending stress and shear stresses in the beam cross section shown in figure 9. If the shear load Sy = 40KN. Assume the web to be ineffective in resisting bending stresses and thickness of web is 1.5mm. (14)


SYLLABUS MODULE 1

BENDING OF THICK & THIN-WALLED BEAMS: Symmetrical and unsymmetrical bending in symmetrical (skew load) and unsymmetrical cross-section - Bending stresses in thick & thin walled beams using generalized k-method - Principal axis and Neutral axis methods.

MODULE 2

SHEAR FLOW IN OPEN SECTION: Thin walled beams- Concept of shear flow. Shear flow distribution in symmetrical and unsymmetrical thin walled sections. Shear center and its determination– structural idealization – shear flow variation in idealized sections, with wall effective and ineffective in bending -Applications of shear flow calculations MODULE 3

SHEAR FLOW IN CLOSED SECTION: Bredt - Batho theory – shear center of closed section (Thin-walled, idealized sections) – single cell and multi cell tubes subject to torsion – shear flow distribution in thin walled single & multi cell structures subject to combined bending and torsion with walls effective and ineffective in bending. MODULE 4

THIN PLATES: Curved Sheet under compression, shear and Bending- Buckling under combined load (compression & Bending, compression & shear, shear & bending) - local buckling stress of thin walled section. Crippling stresses by Needham’s and Gerard’s methods, sheet stiffener panels- Effective skin width. Inter rivet buckling. Shear resistant web beams-Tension field web beams (Wagner’s) MODULE 5

STRESS ANALYSIS OF AIRCRAFT COMPONENTS: Loads on an aircraft-classification - V-n diagram. Shear force and bending moment distribution over the aircraft wing and fuselage. Shear flow in thin webbed beams with parallel flanges. Shear flow in thin webbed beams with non-parallel flanges.

Text And Reference Books:

1. Bruhn. E.H., "Analysis and Design of Flight Vehicles Structures", Tri- state off-set Company, USA,1985.

2. Megson T M G , "Aircraft Structures for Engineering Students", Elsevier Ltd,2012

Reference Books:

1. Peery, D.J., and Azar, J.J., "Aircraft Structures", 2nd edition, McGraw – Hill, N.Y.,1999 2. Michael Chun-Yung Niu, “Airframe structural Design ”,Conmilit Press Ltd,1998 3. Howard D Curtis, "Fundamentals of Aircraft Structural Analysis", WCB- McGraw Hill,1997 4. Rivello, R.M., "Theory and Analysis of Flight Structures", McGraw Hill, 1993.


Course Contents and Lecture Schedule

No Topic No. of Lectures 1 Module 1 - BENDING OF THICK & THIN-WALLED BEAMS

1.1 Symmetric Bending 1

1.2 Unsymmetric Bending in symmetrical (skew load) and unsymmetrical cross-section.

1

1.3 Bending stresses in thick & thin-walled beams using generalized k-method, Principal axis method, Neutral axis method. 6

2 Module2 - SHEAR FLOW IN OPEN SECTION 2.1 Thin-walled beams- Concept of shear flow. 1

2.2 Shear flow distribution in symmetrical and unsymmetrical thin-walled sections.

2

2.3 Shear center and its determination. 2

2.4 Structural idealization – shear flow variation in idealized sections with wall effective and ineffective in bending.

3

2.5 Applications of shear flow calculations. 1 3 Module3- SHEAR FLOW IN CLOSED SECTION

3.1 Bredt - Batho theory. 1 3.2 Shear center of closed section (Thin-walled, idealized sections). 3 3.3 Single-cell and multi-cell tubes subject to torsion. 2

3.4 Shear flow distribution in thin-walled single & multi-cell structures subject to combined bending and torsion – with walls effective and ineffective in bending.

3

4 Module4- THIN PLATES 4.1 Curved Sheet under compression, shear and Bending. 1

4.2 Buckling under combined load (compression & Bending, compression & shear, shear & bending).

2

4.3 Local buckling stress of thin-walled section. 1 4.4 Crippling stresses by Needham’s and Gerard’s methods. 2 4.5 Sheet stiffener panels- Effective skin width - Inter rivet buckling. 2 4.6 Shear resistant web beams-Tension field web beams (Wagner’s). 2 5 Module5- STRESS ANALYSIS OF AIRCRAFT COMPONENTS

5.1 Loads on an aircraft-classification. The v-n diagram. 1

5.2 Shear force and bending moment distribution over the aircraft wing and fuselage.

4

5.3 Shear flow in thin- webbed beams with parallel flanges. 2 5.4 Shear flow in thin-webbed beams with non- parallel flanges. 2


AOT303 AIRBREATHING PROPULSION CATEGORY L T P CREDIT

PCC 3 1 0 4

Preamble: Objective of this course is to introduce basic concepts and salient features of engine components of gas turbine and jet propelled engines which are operated in atmosphere.

Prerequisite: Mechanics of Fluids


CO 1 Understand the basic of gas turbine engines and its components. CO 2 Solve complex problems of centrifugal compressors. CO 3 Construct velocity triangles and solve complex problems of axial flow compressor. CO 4 Apply the design concepts of turbines and able to solve complex problems by constructing

velocity triangles.

CO 5 Understand the concepts of open ducted engines and able to solve complex problems.


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CO 1 3 2 CO 2 3 3 CO 3 3 3 2 CO 4 3 2 2 CO 5 3 2

Assessment Pattern

Bloom’s Category Continuous Assessment Tests End Semester Examination 1 2

Remember 10 10 10 Understand 20 20 20 Apply 20 20 70 Analyse Evaluate Create


Mark distribution

Total Marks CIE ESE ESE Duration

150 50 100 3 hours

Continuous Internal Evaluation Pattern:

Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks.

Course Level Assessment Questions


1. Sketch and explain the working of gas turbine engine?

2. Explain the different types of efficiencies related to gas turbine components?

3. Explain sub critical super critical and critical mode of operation of intakes.


1. Sketch and explain the components associated with centrifugal compressor.

2. What are the problems associated with centrifugal compressor in aircraft propulsion?

3. Derive an expression for work done for a centrifugal compressor?


1. Why the stage by stage compression is done in axial flow compressors?

2. An axial flow compressor stage has the following data: The static temperature and pressure at entry are 300K deg and 1bar respectively. Degree of reaction is 50%, mean blade ring diameter 38cm, rotational speed 16000rpm, blade height at entry is 6cm, air angle at stator and rotor exit 25deg, the axial velocity is 180m/s, work done factor 0.88, stage efficiency 85%, mechanical efficiency 97%. Determine air angles at rotor and stator entry, mass flow rate, and power required pressure ratio developed by the stage?


3. Design a compressor stage suitable for a pressure ratio of 1.3.


1. Sketch and explain the working of a radial turbine.

2. Explain the compressor stages are more than a turbine stage?

3. Explain the limitations of radial turbine associated to aero engines?


1. Explain why the ramjets are not self-starting?

2. Sketch and explain the working of a ramjet

3. Sketch and explain the working of a scramjet.

Model Question paper

QP CODE: Reg No: --------------------------



Course Code: AOT303

Course Name: AIRBREATHING PROPULSION

Max.Marks:100 Duration: 3 Hours

PART A


(Each question carries 3 Marks)

1. Why the normal shock is unstable in the converging section of a supersonic convergent divergent diffuser when the free stream is supersonic?

2. An aircraft is flying with a velocity of 600m/s in an atmospheric condition of density and pressure of 1.225kg/m3 and 1 bar respectively. A normal shock is formed at the lip of the intake channel. Find the static and total pressured just downstream of the shock?

3. Explain the importance of inlet guide vanes in a centrifugal compressor.

4. Sketch and explain why diffusers are required in a centrifugal compressor.


5. Explain the blockage in an axial flow compressor.

6. What are the factors affecting stage pressure ratio of an axial flow compressor?

7. Explain briefly the working of an axial flow turbine with suitable diagram.

8. Explain free vortex design and its significance.

9. Why the matching of compressor and turbine important?

10. Explain why ram jets are not self-started.

PART B

Answer any one full question from each module.

(Each question carries 14 Marks.)

Module 1

11. A turbojet engine propels at a speed of 300m/s at an altitude of 11000m.The turbojet has two air intakes of 0.5m of diameter each. The exit diameter of the two exhaust nozzles are 0.3m. The density of exit gas is 0.2kg/m3. The air fuel ratio is 50 and the heating value of the fuel is 45000KJ/Kg. Calculate the absolute velocity of the jet, drag of the aircraft, overall efficiency, propulsive efficiency and thermal efficiency?

(14) (OR)

12. A supersonic aircraft flying at an altitude of 15km in a standard atmosphere of 0.121bar, and 216K

employs a subsonic diffuser of area ratio 3. The flight speed is 2125Km/h. A normal shock is formed at the inlet of diffuser, find the ram recovery ratio of the diffuser, the total and static pressure and temperature of air at the inlet of the compressor? (14)

Module 2

13. A double sided centrifugal compressor has impeller eye root and tip diameter 17cm, and 31cm and delivered 18kg/s of air at 16000rpm with an inlet total pressure and temperature of 1bar, 288K. Find

the suitable values of impeller vane angles at root and tip of the eye. For air pre whirl angle of 20 deg at all radii and axial velocity at inlet of the eye may be assumed to be constant and it is about 155m/s.

Find the maximum Mach number at eye?

(14)

(OR)


14. Derive an expression for work done and stage pressure rise for a centrifugal compressor applied toaircraft propulsion. (14)

Module 3

15. An axial flow compressor stage has the following data. The static temperature and pressure at entryare 20 deg and 1bar respectively. Degree of reaction is 50%, mean blade ring diameter 36cm,rotational speed 18000rpm, blade height at entry is 6cm, air angle at stator and rotor exit 25deg, theaxial velocity is 180m/s, work done factor 0.88, stage efficiency 85%, mechanical efficiency 97%.Determine air angles at rotor and stator entry, mass flow rate, power required pressure ratiodeveloped by the stage and Mach number at the rotor entry.

(14) (OR)

16. (a) Derive an expression for isentropic stage efficiency and degree of reaction for an axial flowcompressor. (6)(b) Explain surging and blade stall of an axial flow compressor with suitable diagrams.(8)

Module 4

17. The following data apply to a single stage turbine designed on free vortex theory. Mass flow rate is30Kg/s, Inlet stagnation temperature is 1200K, inlet total pressure 8bar, The stagnation temperaturedrop 150K, isentropic efficiency 90%, mean blade speed 320m/s, rps is 250, absolute outlet velocity400m/s. The outlet velocity is axial, calculate the blade height, and radius ratio of the annulus from theoutlet condition. Assume nozzle lose coefficient of 0.07. Show that the continuity is satisfied when theaxial velocity at the exit from the nozzle is 340m/s. Hence calculate the inlet Mach number relative tothe rotor blade at the root. (14)

(OR)

18. (a) Explain the different cooling techniques adopted for cooling of axial flow turbine? (8) (b) Derive an expression for total to static efficiency of a radial flow turbine. (6)

Module 5

19. Explain the working of a ram jet engine with suitable figure. (14)

(OR)

20. A 0.5m diameter ramjet engine having a diverging conical inlet diffuser and a converging exhaustnozzle is designed to operate at a flight Mach number 1.7 at 8Km altitude. The total temperature ofgas at entrance to the exhaust nozzle is 2000K. The fuel heating value is 45MJ/Kg. There is no lose inpressure that the air enters the combustion chamber with a Mach number 0.2, that at the design


condition a normal shock forms at the entrance of the diffuser, and that the nozzle is choked. Calculate the cross sectional area of the diffuser exit, exit area of the nozzle, mass flow rate of air, fuel air ratio, loss in total pressure, effective jet velocity, and thrust? Assume air as working medium. (14)

Syllabus

Module 1

GAS TURBINE ENGINES : Characteristics, working principles and performance of turboprop, turbofan, turbojet and ramjet engines - Internal flow and Stall in subsonic inlets - Relation between minimum area ratio and eternal deceleration ratio, Diffuser performance - Supersonic inlets at different operating conditions – Starting problem on supersonic inlets -Shock swallowing by area variation - Illustration of working of gas turbine engine-the thrust equation -Affecting thrust – Effect of pressure, velocity and temperature Changes of air entering compressor –Methods of thrust augmentation. (Numerical problems).

MODULE 2

CENTRIFUGAL COMPRESSOR : Principle of operation of centrifugal compressor Work done and pressure rise – Velocity diagrams – Degree of reaction - Performance characteristics of centrifugal compressors Stage efficiency calculations. (Numerical problems).

MODULE 3

AXIAL FLOW COMPRESSOR: Operating principle of axial flow compressor - Work done and pressure rise – Velocity diagrams. Degree of reaction – Free vortex and constant reaction designs of axial flow compressor - Performance characteristics of axial flow compressors– Stage efficiency calculations - Cascade testing -Design of blades. (Numerical problems)

MODULE 4

AXIAL FLOW AND RADIAL FLOW TURBINES : Principle of operation of axial flow turbines and radial flow turbines - Work done and pressure rise - Velocity diagrams – Degree of reaction – Free vortex and constant nozzle angle designs - Stage efficiency calculations – Basic blade profile design considerations – Matching of compressor and turbine - Performance characteristics of axial flow turbine– Turbine blade cooling methods. Cascades and cascade testing - Design of blades. (Numerical problems)

Module 5

RAMJET ENGINE : Operating principle of ramjet engine - Various components of ramjet engines and their efficiencies - Combustion in ramjet engine – Critical, subcritical and supercritical modes of operation - Performance characteristics of Ramjet engine - Sample ramjet design calculations – Flame stability problems in ramjet combustors –Integral ram rockets. (Numerical problems)

Text and Reference Books: 1. H Cohen. G F C Rogers HIH Saravanamuthoo,”Gas Turbine Theory”. 2. Anderson, J. D, "Modern Compressible Flow", McGraw-Hill & Co. 3. Rathakrishnan E, Gas Tables, Orient Blackswan Private Limited - New Delhi (2013). 4. S M Yahya, Gas Tables for Compressible Flow Calculations, New Age International Publishing, 2001.


5. Jack D.Mattingly Elements of Gas turbine Propulsion. 6. H Cohen. G F C Rogers HIH Saravanamuthoo,”Gas Turbine Theory”. 7. S M Yahya Turbines, Compressors and Fans, McGraw- Hill & Co.,1997.


S. No Module No. of Lectures 1 Module 1 – GAS TURBINE ENGINES

1.1 Characteristics, working principles and performance of turboprop, turbofan, turbojet and ramjet engines.

2

1.2 Internal flow and Stall in subsonic inlets - Relation between minimum area ratio and eternal deceleration ratio, Diffuser performance.

2

1.3 Supersonic inlets at different operating conditions – starting problem on supersonic inlets, shock swallowing by area variation.(Numerical problems)

2

1.4 Illustration of working of gas turbine engine-the thrust equation. 2

1.5 Factors affecting thrust – effect of pressure, velocity and temperature changes of air entering compressor – Methods of thrust augmentation. (Numerical problems)

2

2 Module 2 – CENTRIFUGAL COMPRESSOR 2.1 Principle of operation of centrifugal compressor. 2 2.2 Work done and pressure rise – velocity diagrams – degree of reaction. 3

2.3 Performance characteristics of centrifugal compressor, Stage efficiency calculations. (Numerical problems) 3

3 Module 3 – AXIAL FLOW COMPRESSOR 3.1 Principle of operation of axial flow compressor. 1

3.2 Work done and stage pressure rise – velocity diagrams. Degree of reaction – free vortex and constant reaction designs of axial flow compressor.

4

3.3 Performance characteristics of axial flow compressors– stage efficiency calculations - cascade testing. (Numerical problems) 4

4 Module 4 – AXIAL FLOW AND RADIAL FLOW TURBINES

4.1 Principle of operation of axial flow turbines– limitations of radial flow turbines- Work done and pressure rise.

3

4.2 Velocity diagrams – degree of reaction – free vortex and constant nozzle angle designs.

3

4.3 Stage efficiency calculations – basic blade profile design considerations – matching of compressor and turbine. Performance characteristics of axial flow turbine– turbine blade cooling methods. (Numerical problems)

3

5 Module 5 – RAMJET ENGINE

5.1 Operating principle of ramjet engine - Various components of ramjet engines and their efficiencies. 2

5.2 Combustion in ramjet engine – critical, subcritical and supercritical modes of operation 2

5.3 Ramjet engine and its performance characteristics - Sample ramjet design 2


calculations

5.4 Flame stability problems in ramjet combustors – integral ram rockets. (Numerical problems) 3


AOT305 AERODYNAMICS II CATEGORY L T P CREDIT

PCC 3 1 0 4

Preamble: The course is meant to give the learners about compressible flow and its behaviours around various profiles.

Prerequisite: Aerodynamics I


CO 1 Apply basic theorems in compressible fluid dynamics.

CO 2 Understand the concepts of shock waves and compressible flow through variable area passage and able to solve complex problems.

CO 3 Understand the concepts of expansion waves and simple flows and able to solve complex problems.

CO 4 Apply the design concepts of high speed aerodynamics theories.

CO 5 Understand the concepts of boundary layer interaction with shockwave and hypersonic flows.


PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO 10

PO 11

PO 12

CO 1 3 3 CO 2 3 3 1 2 2 CO 3 3 3 1 2 CO 4 3 3 2 CO 5 3

Assessment Pattern Bloom’s Category Continuous Assessment Tests End Semester Examination 1 2 Remember 10 10 10 Understand 20 20 20 Apply 20 20 70 Analyse Evaluate Create

Mark distribution Total Marks CIE ESE ESE Duration

150 50 100 3 hours


Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks.



1. Derive Euler equation for a three dimensional Flow field and derive equivalent Bernoulli equation applied to compressible fluid.

2. Derive an expression for the pressure, temperature, density ratio across a normal shock .

3. Explain how a moving shock wave problem can be solved.


1. A wedge of flow deflection angle of θ is placed in a supersonic flow at an angle of attack α. Sketch the streamline and wave patterns if α =0 deg, α > θ, θ = α, α < θ.

2. A C-D Nozzle expands to a variable back pressure. Sketch the streamline and waves when it works as an under, over and optimum expanded nozzle.

3. Differentiate between normal and oblique shock.


1. Find an expression for Prandtl Mayer angle?

2. Write the conservation equations and hence sketch Fanno line and derive the condition for maximum entropy point?

3. Write the conservation equations and hence Rayleigh line and derive the condition for maximum enthalpy and entropy point.


1. Write notes about supercritical aerofoil.

2. Why delta wings are suitable for supersonic airplanes?

3. Explain design requirements for a supersonic aircraft?



1. Sketch the wave structure in the boundary layer.

2. Write the centrifugal correction requirement for hypersonic flows?

3. Explain why the hypersonic flows are represented by primitive variables.


QP CODE: Reg No: --------------------------



Course Code: AOT305

Course Name: AERODYNAMICS II


PART A



1. Write the energy equation and hence construct Prandtl velocity ellipse and indicate the important points.

2. Determine the Mach number of an aircraft when the dynamic (velocity) temperature of air at entry to the engine equals the static temperature.

3. For a given Mach number, the oblique shock is weaker than a normal shock wave, why?

4. Explain under expanded over expanded and optimum expanded nozzles.

5. A wedge is placed in a supersonic flow at an angle of attack. Sketch the streamlines and the wave patterns if the wedge angle is less than the angle of attack.

6. Sketch the Fanno line for a choked flow in h-s plane. If the duct is extended sketch the new Fanno line.

7. Sketch and explain super critical aerofoil.

8. Explain transonic area rule briefly.

9. Explain the boundary layer interaction with shock wave.

10. Explain Newton’s sine square law.


PART B

Answer any one full question from each module. Each question carries 14 Marks

Module 1

11. Derive Prandtl’s relation for stationary normal shock wave. (14) (OR)

12. (a) A normal shock wave moves into a still air at 800m/s. The air ahead of the shockwave is at 101325

Pa, 288K. Find the velocity of the air after passage of the shockwave. (10) (b) Why an expansion shock wave never exist? (4)

Module 2

13. (a) Derive the relationship connecting flow deflection angle, shock wave angle and Mach number? (6) (b) Air with Mach number M=2.5 is deflected with inward corner of a wall. The wave angles formed at the corner is 60 deg. Determine the deflection angle and final Mach number. (8)

(OR) 14. The supersonic inlet contains an oblique shock followed by a normal shock wave. If the free stream

Mach number and the flow deflection angle are 3 and 18 deg respectively, find the stagnation pressure, stagnation temperature, static pressure, temperature and density downstream of the normal shock wave? (14)

Module 3

15. A convergent divergent nozzle of area ratio of 3 is discharges in to an atmosphere of 1bar and

288K.Find the total pressure required for optimum expansion. If the total pressure is increased 1bar from optimum expansion find the Mach number after expansion of the air through the Prandtl Mayer expansion, Find the leading Mach wave and trailing Mach wave angles? (14)

(OR) 16. (a) Derive an expression for Prandtl Mayer angle. (4)

(b) Air at a Mach number 2 encounters a convex corner, the flow deflected to an angle of 10 deg. If the upstream pressure and temperature are 1bar 288K, find the final pressure temperature and Mach number of air. (10)

Module 4

17. Derive an expression for lift drag and pitching moment coefficients over an aerofoil by taking the compressibility in account. (14)

(OR) 18. (a) Explain transonic area rule with sketches. (8)


(b) Explain are the design considerations is to be made while design a supersonic aircraft. (6)

Module 5 19. Explain the Near-normal Shock interaction with laminar and turbulent boundary layer with suitable

sketches. (14)(OR)

20. Derive the pressure, density and temperature ratio across a shock wave if the free stream Machnumber is infinity?(14)

Syllabus

MODULE 1

BASICS OF COMPRESSIBLE FLUID DYNAMICS : Compressibility, Concepts of stagnation condition, Prandtl velocity ellipse, Continuity, Momentum and energy equations for steady one dimensional flow, Equivalent Bernoulli’s equation for compressible fluid dynamics, velocity relation, Mach cone, Mach angle, Normal shock relations, Prandtl’s relation, Hugoniot equation Rayleigh Supersonic Pitot tube equation, Moving normal shock waves. (Simple numerical examples.

MODULE 2

NORMAL SHOCK AND OBLIQUE SHOCK WAVES: Shock Polar, Reflection of oblique shocks, Interaction of oblique shock waves, introduction to slip line compression corner effect – incident shock interaction. Isentropic and non-isentropic flow through variable area passage and their operating characteristics. (Nozzles and Diffusers). Area- Mach number relation Internal flow and Stall in subsonic inlets (Simple numerical examples).

MODULE 3

EXPANSION WAVES: Prandtl-Meyer expansion, Maximum turning angle, Simple and non-simple regions. Rayleigh flow, Fanno flow, Expansion waves, (Simple numerical examples).

MODULE 4

SUPERSONIC CHARACTERISTICS AND CONSIDERATIONS: Critical Mach number, drag divergence, Mach number, Shock Stall, Supercritical Aerofoil Sections, Transonic area rule, Swept wing, Aerofoils for supersonic flows supersonic wings Lift, drag, Pitching moment and Centre of pressure for supersonic profiles, Shock -expansion theory, wave drag, Design considerations for supersonic aircraft- aerodynamic heating, (Simple numerical examples).

Module 5

BOUNDARY LAYER EFFECTS IN SUPERSONIC FLOW: Some boundary-layer effects in supersonic flow:- Near-normal Shock interaction with laminar and turbulent boundary layer, Shock wave boundary layer interaction in


supersonic flow, Introduction to hypersonic flows:-Basic hypersonic shock relation, similarity parameters, Hypersonic shock expansion wave relations.

Text and Reference Books: 1. Fundamentals of Aerodynamics, John D Anderson. 2. Anderson, J. D, "Modern Compressible Flow", McGraw-Hill & Co. 3. Rathakrishnan E, Gas Tables, Orient Blackswan Private Limited - New Delhi (2013). 4. S M Yahya, Gas Tables for Compressible Flow Calculations, New Age International Publishing, 2001. 5. Gas dynamics, Maurice J Zucrow, Jow D. Hoffman. 6. Aerodynamics for Engineers, John J Bertin and Russel M. 7. Shapiro, A. H., "Dynamics and Thermodynamics of Compressible Fluid Flow", Ronald Press, 1982. 8. Oosthuizen,P.H., &Carscallen,W.E., "Compressible Fluid Flow", McGraw- Hill & Co.,1997.


No Module No. of Lectures 1 MODULE 1 - BASICS OF COMPRESSIBLE FLUID DYNAMICS

1.1 Basics of compressible fluid dynamics:- Compressibility, Concepts of stagnation condition, Prandtl velocity ellipse, Continuity, Momentum and energy equations for steady one dimensional flow,

3

1.2 Equivalent Bernoulli’s equation for compressible fluid dynamics, velocity relation, Mach cone, Mach angle,

2

1.3 Normal shock relations, Prandtl’s relation, Huguenot equation Rayleigh Supersonic Pitot tube equation, Moving normal shock waves. (Simple numerical examples)

4

2 MODULE 2 – NORMAL SHOCK AND OBLIQUE SHOCK WAVES

2.1 Shock Polar, Reflection of oblique shocks, Interaction of oblique shock waves, Introduction to slip line,

3

2.2 Compression corner effect incident shock interaction. 1

2.3 Isentropic and non-isentropic flow through variable area passage and their operating characteristics under different pressure conditions. (Nozzles and Diffusers). (Simple numerical examples).

4

2.4 Area- Mach number relation 1 3 MODULE 3– EXPANSION WAVES

3.1 Rayleigh flow, Fanno flow, (Simple numerical examples). 4 3.2 Expansion waves, Prandtl-Meyer expansion, 3 3.3 Maximum turning angle, Simple and non-simple regions. 2 4 MODULE 4 -SUPERSONIC CHARACTERISTICS AND CONSIDERATIONS

4.1 Critical Mach number, drag divergence, Mach number, Shock Stall, Supercritical Aerofoil Sections, Transonic area rule, Swept wing,

4

4.2 Aerofoils for supersonic flows supersonic wings Lift, drag, Pitching moment and Centre of pressure for supersonic profiles,

3

4.3 Shock - expansion theory, wave drag, Design considerations for 2


supersonic aircraft - aerodynamic heating. (Simple numerical examples). 5 MODULE 5 -BOUNDARY LAYER EFFECTS IN SUPERSONIC FLOW

5.1 Boundary layer and boundary layer thickness, displacement thickness, momentum thickness, energy thickness,

4

5.2 Blasius solution, boundary layer equations for a steady, two dimensional incompressible flow,

4

5.3 Introduction to boundary layer interaction with shock wave, Introduction to hypersonic flows (Simple numerical examples).

1


AOT307 AVIONICS AND AIRCRAFT SYSTEMS CATEGORY L T P CREDIT

PCC 3 1 0 4 Preamble: Objective of this course is to study the electronics applications into aviation field and various systems with instruments used for successful flight. Prerequisite: Nil Course Outcomes: After the completion of the course the student will be able to CO 1 Understand the needs of integrated avionics and their subsystems in an aircraft. CO 2 Understand the avionics system architecture and various databuses used in aircraft. CO 3 Understand the principles of various cockpit displays and navigation system instruments. CO 4 Understand the various control systems used in aircraft. CO 5 Understand the conceptual design and working principles of various aircraft instruments. Mapping of course outcomes with program outcomes PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO

10 PO 11

PO 12

CO 1 3 2 1 - - - - - - - - - CO 2 3 2 1 - - - - - - - - - CO 3 3 2 1 - - - - - - - - - CO 4 3 2 1 - - - - - - - - - CO 5 3 2 1 - - - - - - - - -


1 2 Remember 15 15 30 Understand 35 35 70 Apply Analyse Evaluate Create

Mark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours


Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks.



1. What are the needs for avionics in civil and military aircraft and space systems?

2. Define Volatile memory and non-volatile memory.


1. Distinguish between disjoint and centralized architecture system in avionics.

2. List out the specifications of ARINC 429, ARINC 629, MIL-STD 1553B.


1. Why Synthetic and enhanced vision system is needed in avionics?

2. What is Situation awareness in avionics?


1. Write the role of gyro in INS system.

2. What are space segment, control segment and user segment in GPS?


1. What are the aircraft instruments which needs dynamic pressure data?

2. How total air temperature can be calculated?



QP CODE: Reg No: _______________

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY FIFTH SEMESTER B.TECH DEGREE EXAMINATION, MONTH & YEAR

Course Code: AOT307 Course Name: AVIONICS AND AIRCRAFT SYSTEMS


PART A

Answer all questions


1. What are the needs for avionics in civil and military aircraft and space systems?

2. Define Volatile memory and non-volatile memory.

3. Distinguish between disjoint and centralized architecture system in avionics.

4. List out the specifications of ARINC 429, ARINC 629, MIL-STD 1553B.

5. Why Synthetic and enhanced vision system is needed in avionics?

6. What is Situation awareness in avionics?

7. Write the role of gyro in INS system.

8. What are space segment, control segment and user segment in GPS?

9. What are the aircraft instruments which needs dynamic pressure data?

10. How total air temperature can be calculated?

PART B

Answer one full question from each module


Module – 1

11. a) How avionics is applied into aviation field? (6)

b) Give any suitable example for integrated weapon system and explain it with neat block diagram.


(8)

(OR)

12. List out the various navigation subsystems that are used in aviation field with neat figures. (14)

Module – 2

13. (a) What are all the features that are included in pave pillar architecture? (4)

(b) Explain about the bus architecture, protocol, word and message formats and coupling methods of MIL – STD – 1553B data bus. (10)

(OR)

14. (a) How centralized avionics architecture varies from federated architecture? (4 marks)

(b) Explain about the bus architecture, protocol, word formats and coupling methods of ARINC 429 data bus. (10 marks)

Module – 3

15. (a) Find Explain about HUD & HMD cockpit displays that are used in aircraft with suitable diagrams. (10 marks)

(b) Explain about Synthetic and enhanced vision system with suitable figure. (4)

(OR)

16. Explain about any two radio navigation systems with suitable diagrams. (14)

Module – 4

17. (a) List out the major components used and their functions in autopilot system. (6)

(b) Explain the working principle autopilot system with neat sketch. (8)

(OR)

18. Explain the types and working principles of hydraulic and pneumatic system with neat diagrams. (14)

Module – 5

19. Explain the working principles of gyroscopic instruments used in aircraft with neat diagrams. (14)

(OR)


20. Explain the working principles of Pressure and Temperature measurement instruments. (14)

Syllabus

Module 1

INTEGRATED AVIONICS AND SUBSYSTEMS : Need for avionics in civil and military aircraft and space systems - Integrated avionics and weapon systems - Typical avionics subsystems and their technologies - Introduction to digital computer and memories.

Module 2

AVIONICS ARCHITECTURE AND DATA BUSES : Avionics system architecture generations - Data buses: MIL-STD-1553B, ARINC 429, AFDX/ARINC 664 - Fibre optic Data buses: IEEE STD 1393, MIL STD 1773.

Module 3

AIRCRAFT DISPLAYS TECHNOLOGIES AND NAVIGATION SYSTEMS : Aircraft cockpit displays: MFD, HUD, HMD, DVI - Synthetic and enhanced vision - situation awareness - virtual cockpit - Radio navigation systems: ADF, DME, VOR, ILS - Inertial Navigation Systems (INS) - Satellite navigation systems – GPS.

Module 4

AIRCRAFT CONTROL SYSTEMS : Hydraulic and Pneumatic systems: Types, components, working principles - Aircraft Fuel Systems: components and their types, gravity and pump feed setup, fueling and defueling procedures – Aircraft Landing Gear system: Types, fixed and retractable landing gear, shock strut operation, break system – Autopilot System: components and their functions, operating principles, – Fly by Wire Systems – RVDT, LVDT and working concept.

Module 5

AIRCRAFT SYSTEMS INSTRUMENTS : Pitot-Static instruments: Altimeters, Airspeed Indicator, Vertical Speed Indicator - Gyroscopic instruments: Gyro Horizon Indicator, Turn and Bank Indicator & Directional Gyroscope – Tachometer – Synchroscope – Pressure and Temperature measurement instruments.

Text and Reference Books:

1. Collinson.R.P.G. "Introduction to Avionics", Chapman and Hall, 1996.

2. Albert Helfrick.D., "Principles of Avionics", Avionics Communications Inc., 2004

3. Mekinley, J.L. and Bent, R.D., “Aircraft Power Plants”, McGraw-Hill, 1993.

4. Spitzer. C.R. "The Avionics Hand Book", CRC Press, 2000

5. Pallet, E.H.J., “Aircraft Instruments & Principles”, Pitman & Co., 1993.


6. “Aviation Maintenance Technician Hand Book – Airframe Vol. I & II”, U.S. Dept. of Transportation, Federal

Aviation Administration, The English Book Store, New Delhi.


No Topic No. of Lectures 1 MODULE 1 - INTEGRATED AVIONICS AND SUBSYSTEMS

1.1 Need for avionics in civil and military aircraft and space systems 1 1.2 Integrated avionics and weapon systems 2 1.3 Typical avionics subsystems and their technologies 2 1.4 Introduction to digital computer and memories. 2 2 Module 2 – AVIONICS ARCHITECTURE AND DATA BUSES

2.1 Avionics system architecture generations 1 2.2 Data buses: MIL-STD-1553B, 2 2.3 ARINC 429, AFDX/ARINC 664 3 2.4 Fibre optic Data buses: IEEE STD 1393, MIL STD 1773. 4 3 Module 3 – AIRCRAFT DISPLAYS TECHNOLOGIES AND NAVIGATION SYSTEMS

3.1 Aircraft cockpit displays: MFD, HUD, HMD, DVI 2 3.2 Synthetic and enhanced vision - situation awareness - virtual cockpit 2 3.3 Radio navigation systems: ADF, DME, VOR, ILS 2 3.4 Inertial Navigation Systems (INS) 2 3.5 Satellite navigation systems – GPS. 2 4 Module 4 – AIRCRAFT CONTROL SYSTEMS

4.1 Hydraulic and Pneumatic systems: Types, components, working principles

2

4.2 Aircraft Fuel Systems: Components and their types, gravity and pump feed setup, fueling and defueling procedures

2

4.3 Aircraft Landing Gear system: Types, fixed and retractable landing gear, shock strut operation, break system

2

4.4 Autopilot System: components and their functions, operating principles 2 4.5 Fly by Wire Systems – RVDT, LVDT and working concept. 2 5 Module 5 – AIRCRAFT SYSTEMS INSTRUMENTS

5.1 Pitot-Static instruments: Altimeters, Airspeed Indicator, Vertical Speed Indicator

2

5.2 Gyroscopic instruments: Gyro Horizon Indicator, Turn and Bank Indicator & Directional Gyroscope

2

5.3 Tachometer – Synchroscope 2 5.4 Pressure and Temperature measurement instruments. 2


AOL331 PROPULSION LAB CATEGORY L T P CREDIT PCC 0 0 3 2

Preamble: Goal of this course is to provide practical knowledge in gas turbine engine also to analyse the behaviour of flow through ducts and jet engine components.


CO 1 Understand the velocity profile and nozzle flow problems. CO 2 Find out the performance using cascade tunnel. CO 3 Determine the heat transfer also studies heat exchanger working. CO 4 Understand the performance of 2-stroke and 4-stroke engines.


PO 1


PO 11

PO 12

CO 1 3 2 2 2 CO 2 3 2 2 2 CO 3 3 2 2 2 CO 4 3 2 2 2

Assessment Pattern

Mark distribution


150 75 75 2.5hours


Attendance : 15 marks Continuous Assessment Test (2 numbers) : 30 marks Assignment/Quiz/Course project : 30 marks End Semester Examination Pattern: The following guidelines should be followed regarding award of marks (a) Preliminary work : 15 Marks (b) Implementing the work/Conducting the experiment : 10 Marks (c) Performance, result and inference (usage of equipment’s and troubleshooting) : 25 Marks (d) Viva : 20 marks (e) Record : 5 Marks


General instructions: Practical examination to be conducted immediately after the second series test covering entire syllabus given below. Evaluation is a serious process that is to be conducted under the equal responsibility of both the internal and external examiners. The number of candidates evaluated per day should not exceed 20. Students shall be allowed for the University examination only on submitting the duly certified record. The external examiner shall endorse the record. Course Level Assessment Questions


1. Understand the velocity profile and analyse diffuser flow.

2. Determine the velocity profile for both wall jet and free jet.

3. Find out the pressure variation in subsonic nozzle.


1. understand the performance of cascade tunnel and flame stabilizer

2. Determine the performance of axial and turbine blades in cascade tunnel.

3. How flame stabilization can be done using different flame holders.


1. understand heat transfer and heat exchanger in detail

2. Verify the heat transfer over flat plate using forced and free convection.

3. Determine the effectiveness of heat exchanger.


1. understand automobile engine and refrigeration system

2. Find out the performance of 2-stroke and 4-stroke engine.

3. Determine the COP of a refrigeration system.


LIST OF EXPERIMENTS

1. Velocity profiles of wall jets.

2. Velocity profiles of free jets

3. Wall pressure measurements of a subsonic diffusers.

4. Flame stabilization studies using conical and hemispherical flame holders.

5. Cascade testing of axial compressor blade row.

6. Cascade testing of axial Turbine blade row.

7. Study of forced convective heat transfer over a flat plate.

8. Study of free convective heat transfer over a flat plate

9. Study of an aircraft jet engine (Includes study of assembly of sub systems, various components, their functions and operating principles

10. Determination of effectiveness of heat exchanger.

11. Determination of Propeller Thrust and Performance

12. COP test on a Vapour compression refrigeration test rig

13. Performance test on a 4-stroke engine.

14. Valve timing of a 4 – stroke engine

15. Port timing of a 2 stroke engine.

16. Determination of calorific value of a fuel.

Note: A minimum of 10 experiments are mandatory.

Textbooks: 1. Ramamurthi, K., Rocket Propulsion, Macmillan (2010). 2. Sutton, G. P. and Biblarz, O., Rocket Propulsion Elements, 7th ed., John Wiley (2000). 3. Hill and Peterson: Mechanics and Thermodynamics of Propulsion References: 1. J D Mattingly, Elements of Gas Turbine Propulsion, McGraw Hill, 1997 2. J P Holman, Heat Transfer, 2nd Ed., McGraw Hill 3. J L Kererbrock, Aircraft Engine and Gas Turbine, MIT Press, 1991 4. P G Hill & C R Peterson, Mechanics and Thermodynamics of Propulsion Wesley, 1970. 5. D. P. Mishra, Fundamentals of Combustion, Prentice Hall of India, New Delhi, 2008.


AOL333 AIRCRAFT STRUCTURAL ANALYSIS LAB CATEGORY L T P CREDIT PCC 0 0 3 2

Preamble: Aim of this course is to provide practical knowledge on static and dynamic analysis of aircraft structural components under different loading conditions. Prerequisite: Engineering Mechanics, Strength of Materials, Aircraft Structures-1, Experimental Stress Analysis Course Outcomes: After the completion of the course the student will be able to CO 1 Determine the buckling and bending strength of different structural members.

CO 2 Analyse the shear centre position for open and closed section of beams.

CO 3 Determine the natural frequency for longitudinal and torsional vibration of different structural components.

CO 4 Determine the stress-strain values for different structural components.

CO 5 Understand the concepts of photoelasticity.

Mapping of course outcomes with program outcomes PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO

10 PO 11

PO 12

CO 1 3 2 2 1 CO 2 3 2 2 1 CO 3 3 2 2 1 CO 4 3 2 2 1 CO 5 3 2 2 1 Assessment Pattern Mark distribution Total Marks CIE ESE ESE Duration

150 75 75 2.5 hours

Continuous Internal Evaluation Pattern: Attendance : 15 marks Continuous Assessment Test (2 numbers) : 30 marks Assignment/Quiz/Course project : 30 marks End Semester Examination Pattern: The following guidelines should be followed regarding award of marks (a) Preliminary work : 15 Marks (b) Implementing the work/Conducting the experiment : 10 Marks (c) Performance, result and inference (usage of equipment’s and troubleshooting) : 25 Marks (d) Viva : 20 marks (e) Record : 5 Marks


General instructions: Practical examination to be conducted immediately after the second series test covering entire syllabus given below. Evaluation is a serious process that is to be conducted under the equal responsibility of both the internal and external examiners. The number of candidates evaluated per day should not exceed 20. Students shall be allowed for the University examination only on submitting the duly certified record. The external examiner shall endorse the record. Course Level Assessment Questions Course Outcome 1 (CO 1):

1. Determine the stress at various locations along the length of a constant strength beam.

2. Determine the buckling stress of pinned end struts.

3. Determine the principal stress direction of an unsymmetrical section.

Course Outcome 2 (CO 2):

1. Determine the shear centre of an open (C) section.

2. Determine the shear centre of a closed (D) section.


1. Determine the natural frequency for longitudinal vibration of bar.

2. Determine the natural frequency for torsional vibration of shaft.


1. Determine the maximum shear stress and shear modulus of thin walled tubes.

2. Determine the maximum shear stress and shear modulus of cylindrical rod.


1. Determine the stress concentration factor in compression for different cross section models.


LIST OF EXPERIMENTS

1. Constant Strength Beams

2. Buckling of Columns

3. Unsymmetrical Bending of Beams

4. Flexibility Matrix for Cantilever Beam

5. Combined Loading

6. Wagner Beam

7. Shear Centre Location for Open Section

8. Shear Centre Location for Closed Section

9. Vibration damping test – Longitudinal

10. Vibration damping test – Torsional

11. Stress-Strain measurement on pressurized thin walled tubes of various materials using strain gauges

12. Stress-Strain measurement on flat plate and cylindrical rod with axial loads using strain gauges

13. Stress-Strain measurement on hollow cylindrical rod with torsional load using strain gauges

14. Stress-Strain measurement using strain rosette – Star and Delta Connected

15. Verification of stress optic law using photo elasticity


Reference Books:

1. Megson T M G, "Aircraft Structures for Engineering students" Elsevier, 2007.

2. Timoshenko and Gere, "Mechanics of Materials", Tata McGraw Hill, 1993.

3. Grover. G.K., “Mechanical Vibrations”, 7th Edition, Nem Chand Brothers, Roorkee,

India, 2003

4. Sadhu Singh, "Experimental Stress Analysis", Khanna Publishers, New Delhi, 1996.


SEMESTER V MINOR


AOT381 HIGHSPEED AERODYNAMICS CATEGORY L T P CREDIT VAC 3 1 0 4

Preamble: The course is meant to give the learners an introduction to high speed aerodynamics.


CO 1 Understand the basics of aerodynamics and thermodynamics. CO 2 Basics of Normal shock how its behaviour is analysed. CO 3 Application of convergent divergent nozzle. CO 4 Understand the properties of hypersonic flow in detail. CO 5 Basics of wind tunnel both in subsonic and supersonic flow. Mapping of course outcomes with program outcomes PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO

10 PO 11

PO 12

CO 1 3 CO 2 3 CO 3 3 2 CO 4 3 2 2 CO 5 3 Assessment Pattern

Bloom’s Category Continuous Assessment Tests End Semester Examination 1 2 Remember 20 20 20 Understand 20 20 30 Apply 10 10 50 Analyse Evaluate Create Mark distribution Total Marks CIE ESE ESE Duration

150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks.




1. State the importance of Thermodynamics. .

2. Discuss continuity, moment and energy equation in detail.

3. Understand the velocity of sound.


1. Define normal shock concepts.

2. Discuss oblique shock relation and variation.

3. Basic numerical on normal shocks.


1. What do you understand the Quasi 1D flow equation?

2. Discuss convergent divergent nozzle.

3. Explain Fanno and Rayleigh flow.


1. Explain in detail Newtonian flow model.

2. State Aerodynamic heating.

3. What do you understand hypersonic flow and its relation?


1. With neat diagram explain the various components of subsonic Wind tunnel.

2. Define solid blockage and wake blockage.

3. Explain Shock tube with neat diagram.



QP CODE: Reg No: -------------------------

-



Course Code: AOT 381

Course Name: HIGHSPEED AERODYNAMICS


PART A



1. What is under Expanding nozzle flow?

2. Explain Mach number?

3. Explain oblique shocks.

4. Define term moving normal shock.

5. Define chocking in nozzle.

6. Sketch compressible flow in converging and diverging ducts.

7. Prove CP=2sin2Ɵ for Newtonian theory.

8. Define few application of hypersonic flow.

9. Define wind tunnel balances.

10. What’s the difference between supersonic and hypersonic wind tunnel.

PART B



Module 1

11. (a) write short notes on 1) Thermodynamic systems 2) Enthalpy 3) Calorically perfect gas 4)Perfect gas (8)

(b) If an aircraft flying at a velocity of 250m/s, Calculate its Mach number if it is flying at a standard altitude of (a)sea level,(b)5km,(c) 10km. (6)


(OR)

12. (a)Define the principle of momentum equation and derive the equation of momentum. (8) (b) Obtain an expression to find out the velocity of sound in a fluid. (6)

Module 2 13. Derive the energy equation for normal shock waves. (14)

(OR) 14. (a)Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1atm.Calculate the loss of total pressure across the shock wave when the upstream Mach number is (a)M1=2 and (b)M1=4. (8) (b) Define how the properties vary in oblique shocks. (6)

Module 3 15. Derive the Governing equations for Quasi-one-dimensional flow. (14)

(OR) 16. (a) Bring out the essential difference between Rayleigh flow and fanno flow. Give at least two examples for each type of flow. (8)(b) A Pitot tube inserted at the exit of a supersonic nozzle reads 8.92×104N/m2. If the reservoir pressure is 2.02×105 N/m2, Calculate the area ratio Ae/A* of the nozzle. (6)

Module 4 17. (a)In detail explain Tangent wedge method and Tangent cone method (8) (b)Define Newtonian flow model. (6)

(OR) 18. (a) Explain with data’s for the topic shock relations for hypersonic flow (8) (b)Explain the term Aerodynamic heating. (6)

Module 5 19. (a) Explain in detail the factors we consider in supersonic wind tunnel calibration? (8)

(b)What are the requirements of tracer particles used for flow Visualization? (6)

(OR)

20. (a)Explain construction of subsonic open type wind tunnel with neat sketch. (8) (b)Explain solid blockage and wake blockage. (6)


Syllabus

Module 1

Introduction of Aero-Thermodynamics, Basic Concept of Compressible fluid dynamics, relation of subsonic and supersonic flow ,Continuity, momentum, energy and equation of states, velocity of sound.(Basic problems)

Module 2

Normal shock concepts, Normal shock relation. Moving normal shocks, Concepts and theory of oblique shock and its relations, Property variation in oblique shocks. (Basic problems)

Module 3

Quasi 1D flow with area variations, Convergent nozzle, Convergent Divergent nozzles. Chocking, Fanno flow and Rayleigh flow. (Basic problems)

Module 4

Introduction to Hypersonic, shock & Expansion wave relation, Applications of Hypersonic flow. Basic hypersonic shock relations, examples related to Hypersonic Flow. Newtonian flow model, stagnation region flow field properties, Modified Newtonian flow, Aerodynamic heating

Module 5

Experimental Method in Aerodynamics. Introduction to wind tunnels & its components, measurements of various quantities in wind tunnel, solid blockage, wake blockage, wind tunnel balances, corrections, flow visualization techniques, supersonic wind tunnels, high speed subsonic tunnels, transonic wind tunnel, shock tube, hypersonic wind tunnel. Text Books

1. Fundamentals of Aerodynamics, John D Anderson.

2. Anderson, J. D, "Modern Compressible Flow", McGraw-Hill & Co.

Reference Books

1. Gas dynamics by Maurice J Zucrow, Jow D. Hoffman

2. A H Shapiro, Dynamics and Thermodynamics of Compressible Fluid Flow-

Volume I & II, Ronald Press

3. Shapiro, A. H., "Dynamics and Thermodynamics of Compressible Fluid Flow", Ronald Press, 1982.

4. Oosthuizen,P.H., &Carscallen,W.E., "Compressible Fluid Flow", McGraw- Hill & Co.,1997 2.


Course Contents and Lecture Schedule No Module No. of Lectures 1 Module: 1

1.1 Introduction of Aero-Thermodynamics, Basic Concept of compressible fluid dynamics and Thermodynamics.

3

1.2 Relation of Subsonic flow and Supersonic flow, Continuity, momentum, energy and equation of state.

4

1.3 Velocity of sound, (basic problems). 2 2 Module: 2

2.1 Normal shock concepts, Normal shock relation.(Basic problems). 2 2.2 Moving normal shocks, Concepts and theory of oblique shock and its

relations. 3

2.3 Property variation in oblique shocks. 3 3 Module: 3

3.1 Quasi 1D flow with area variations. 3 3.2 Convergent nozzle, Convergent Divergent nozzles. Chocking. (Basic

problems). 3

3.3 Fanno flow and Rayleigh flow. 2 4 Module: 4

4.1 Introduction to Hypersonic, shock & Expansion wave relation, Applications of Hypersonic flow.

3

4.2 Basic hypersonic shock relations, examples related to Hypersonic Flow. 3 4.3 Newtonian flow model, stagnation region flow field properties,

Modified Newtonian flow, Aerodynamic heating. 2

5 Module: 5 5.1 Experimental Method in Aerodynamics. Introduction to wind tunnel &

its components. 3

5.2 Measurements of various quantities in wind tunnel, solid blockage, wake blockage, wind tunnel balances, corrections, flow visualization techniques.

3

5.3 Supersonic wind tunnels, high speed subsonic tunnels, transonic wind tunnel, shock tube, hypersonic wind tunnel.

4

.


AOT383 BASICS OF AERO ENGINES CATEGORY L T P CREDIT VAC 3 1 0 4

Preamble: In this course the student will learn the basic concepts of aero engines and the thermodynamic cycles. The study involves fundamental approach and application of jet engine components. Also, the analysis of flow phenomenon and estimation of thrust developed by jet engine and rocket engine.

Prerequisite: NIL


CO 1 Develop basic concept of different thermodynamic cycles used in aero engines. CO 2 Establish fundamental approach and application of jet engine components. CO 3 Establish the analysis of performance parameters and estimation of thrust developed by jet

engine. Also to calculate the various efficiencies. CO 4 Understand the workings of multistage compressor or turbine, and to be able to use

equation to estimate the performance of a compressor or turbine stage. CO 5 Get familiarity in rocket propulsion systems. To gain knowledge about the advanced

propulsion technique used for interplanetary mission. Mapping of course outcomes with program outcomes PO

1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO

10 PO 11

PO 12

CO 1 3 3 CO 2 3 CO 3 3 2 1 CO 4 3 2 1 CO 5 3 1 Assessment Pattern

Bloom’s Category Continuous Assessment Tests End Semester Examination 1 2 Remember 10 10 10 Understand 20 20 20 Apply 20 20 70 Analyse Evaluate Create Mark distribution Total Marks CIE ESE ESE Duration

150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks


Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions:


1. Derive an expression for the air standard efficiency of a Brayton cycle.

2. Define Cutoff ratio.

3. Draw the Diesel cycle on p-v and T-s diagram. Also derive expression for air standard efficiency with usual notations for the cycle.

4. Draw line diagram of Brayton cycle represent on p-v diagram and derive expression for efficiency of Brayton cycle.

Sample Problem.

1. An ideal Otto cycle has a compression ratio of 8. At the beginning of the compression stroke, the air is at 101kPa and 22OC, and 900kJ/kg of heat is added to it during the constant volume heat addition process. Considering the variation of specific heats of air with temperature, determine (a) the maximum temperature and pressure encountered during the cycle, (b) the net work done output, (c) the thermal efficiency of the cycle.

Course Outcome 2 (CO2)

1. List the advantages of turbofan engine which makes it more suitable for commercial aircraft.

2. Describe the function of diffuser in jet engines.

3. Explain the working of a ramjet engine with neat diagram.

4. Describe about the principal components of turbojet engine.


1. What is meant by TSFC? In what way it is useful in comparing the performance of different jet propulsion engines.

2. Define the term effective jet velocity associated with jet propulsion engine.

3. Define propulsive and thermal efficiency of jet propulsion engine.


Sample Problem.

1. A turbojet inducts 43.117kg/s of air while operating at an altitude of 10km. The flight speed of the aircraft is 850kmph. 1.0078kg/s of fuel is used for the combustion process. The hot gas leaving the nozzle has a static pressure of 0.3bar and its velocity is 500m/s. The exit diameter of the nozzle is 0.5m. Calculate the thrust, fuel specific impulse and TSFC.


1. Write a note on ‘choking of centrifugal compressor’.

2. Explain the three-dimensional flow in axial flow compressor and derive the free vortex condition. What does free vortex condition signify?

3. What is relative stagnation enthalpy in an axial turbine stage? Explain briefly.

4. Derive the expression for total-to-total efficiency.

Sample Problem.

1. Determine the pressure ratio for a stage of an axial flow compressor with symmetric blades under the following conditions:

Absolute velocity at mean radius = 220m/s Axial velocity = 150m/s Solidity for moving blades = 0.98 Coefficient of lift for moving blades = 0.8 The ratio of drag to lift = 0.045 Ambient conditions = 1bar and 300K Calculate the pressure ratio for non-symmetric blading and compare with pressure ratio of symmetric blading.


1. What is the difference between total impulse and specific impulse of a rocket engine?

2. Define effective jet velocity.

3. Derive a relationship for the thrust developed by a rocket engine in terms of pressure ratio.



QP CODE: Reg No: --------------------------




BASICS OF AERO ENGINES


PART A

Answer all Questions. (Each question carries 3 Marks)

1. Derive an expression for the air standard efficiency of a Diesel cycle

2. Define compression ratio and cut off ratio.

3. Briefly explain the working of pulse jet engine.

4. What do you mean by air-breathing engine? Give four examples of air-breathing engine.

5. Describe about thrust augmentation.

6. Write a short note on effective jet velocity.

7. Define the surging in a compressor.

8. Define degree of reaction for an axial flow compressor

9. What are the type of nozzles used in solid and liquid propulsion system?

10. Describe briefly the functions of hybrid rockets.

PART B



Module 1

11. Derive an expression for the efficiency of a Brayton cycle. Also derive expression for compressor turbine diffuser for nozzle efficiency. (14)

12. An ideal Diesel cycle has a compression ratio of 14. At the beginning of the compression stroke, the air is at 101kPa and 22OC, and 900kJ/kg of heat is added to it during the constant volume heat addition process. Considering the variation of specific heats of air with temperature, determine (a) the maximum


temperature and pressure encountered during the cycle, (b) the net work done output, (c) the thermal efficiency of the cycle. (14)

Module 2

13. Describe with suitable sketches the working of a turbofan engine. (14)

14. A turbojet engine propels an aircraft at speed of 300m/s at an altitude of 16000m. The turbojet has twoair intakes of 500mm diameter each. The exit diameter of the two exhaust nozzles are each 0.3m. Thedensity of the exit gas is 0.16kg/m3. The air fuel ratio is 50 and the heating value of the fuel is45000kJ/kg. Calculate (i) absolute velocity of the jet (ii) drag of the aircraft (iii) overall efficiency (iv)propulsive efficiency. (14)

Module 3

15. . A turbojet inducts 40.117kg/s of air while operating at an altitude of 10km. The flight speed of theaircraft is 850kmph. 1.0068kg/s of fuel is used for the combustion process. The hot gas leaving the nozzlehas a static pressure of 0.3bar and its velocity is 500m/s. The exit diameter of the nozzle is 0.5m.Calculate the thrust, fuel specific impulse and TSFC.

(14)

16. a) What is meant by TSFC? In what way it is useful in comparing the performance of different jetpropulsion engine? (6)

b) Derive the expression for thrust equation for jet engine. (8)

Module 4

17. The first stage of an axial flow compressor is designed on free-vortex principle, with no inlet guide vanes.The rotational speed is 6000 rpm and stagnation pressure rise is 20 K. The hub-tip ratio is 0.6, the workdone factor is 0.93 and isentropic efficiency of stage is 0.89. Assuming an inlet velocity of 140 m/sandambient conditions of 1.01 bar and 288 K, Find the tip radius and corresponding rotor air angles, if theMach number relative to tip is limited to 0.95. Also find the mass flow rate entering the stage.

(14)

18. Derive the expression for degree of reaction of a axial compressor stage. Also derive the expression forfifty percent reaction stages. (14)

Module 5

19. a) Briefly bring out the operating principle of a rocket engine. (6)

b) Derive thrust power and propulsive power as applied to a thermal rocket engine. (8)

20. Explain the working of the following propulsion used in rocket engines

(i) Ion propulsion (ii) Nuclear propulsion (14


Syllabus

Module 1 Thermodynamic Cycles: Introduction, Operating principles of piston engines-Otto Cycle, Diesel Cycle, Operating principles of Gas turbine engines- Basic components, Basic Brayton cycle, Open Brayton cycle for propulsion systems, diffusion process, Compression process, Combustion process, expansion process in turbine, Expansion in nozzle, Problems. Module 2 Aircraft Propulsion Engines: Introduction, Components and Working of Propeller engines, Turbojet engines, Turboprop and Turbo shaft engines, Turbofan engines, Ramjet engines, Pulsejet engines, Scramjet engines, Merits and Demerits of each Engines, Comparison of Propulsion systems. Module 3 Propulsion Performance Parameters: General thrust equation, Thrust of Turbojets, Thrust of Ramjet, Effective jet velocity, Jet power or thrust power, Propulsive power, Specific thrust and Specific Impulse, Specific fuel consumption, Thrust coefficient, Thrust Augmentation, Problems related to thrust. Energy Flow and Efficiency: Energy flow in propulsion engines, Efficiency considerations, Propulsive efficiency, Speed ratio, Transmission efficiency, Thermal efficiency, Overall efficiency, Problems in various efficiency. Module 4 Jet Engine Compressors and Turbines: Principle operation of centrifugal compressor, Principle operation of axial flow compressor– Work done and pressure rise – velocity diagrams – degree of reaction – free vortex and constant reaction designs of axial flow compressor – performance parameters axial flow compressors– stage efficiency. Principle of operation of axial flow turbines– limitations of radial flow turbines- Work done and pressure rise turbine blade cooling methods – stage efficiency calculations, Problems. Module 5 Rocket Propulsion: Introduction, Classification of rockets, Principle of rocket propulsion, Analysis of an ideal chemical rocket, Optimum expansion ratio for rockets, Basic principles of solid, liquid, and hybrid rockets and their functions and applications, Nuclear propulsion, Ion propulsion, Plasma propulsion, Photon propulsion, Problems. Text & Reference Books: 1. P.Balachandran, “Fundamentals of Compressible Fluid Dynamics”, PHI Learning Pvt Ltd, Ninth edition,

2014. 2. Dr.M.L.Mathur & R.P Sharma, “Gas Turbines and Jet & Rocket Propulsion”, Standard Publishers

distributers, Fourth Edition, 2014. 3. Hill, P.G. & Peterson, C.R. “Mechanics & Thermodynamics of Propulsion” Pearson education (2009). 4. H.Cohen, GFC Rogers & HIH Saravanamuttoo, “Gas Turbine Theory”, Pearson education Ltd, Fifth

Edition, 2013. 5. V.Ganesan, “Gas Turbines”, Tata McGraw hill education Pvt Ltd, Third Edition, 2011. 6. Nag.P.K., “Engineering Thermodynamics”, Tata McGraw-Hill, New Delhi, 2013. 7. Oates, G.C, “Aero thermodynamics of Aircraft Engine Components”, AIAA Education Series, New York,

1985. 8. S.M.Yahya, “Turbines, Compressors and fans”, Tata McGraw hill education Pvt Ltd, Fourth Edition,

2011.


Course Contents and Lecture Schedule No Topic No. of Lectures 1 Module 1 - Thermodynamic Cycles

1.1 Introduction, Operating principles of piston engines-Otto Cycle, Diesel Cycle 2 1.2 Operating principles of Gas turbine engines- Basic components, Basic Brayton

cycle 2

1.3 Open Brayton cycle for propulsion systems, diffusion process 2 1.4 Compression process, Combustion process, expansion process in turbine,

Expansion in nozzle, Problems 3

2 Module 2 - Aircraft Propulsion Engines 2.1 Introduction, Components and Working of Propeller engines, Turbojet engines 2 2.2 Turboprop and Turbo shaft engines, Turbofan engines 2 2.3 Ramjet engines, Pulsejet engines, Scramjet engines 3 2.4 Merits and Demerits of each Engines, Comparison of Propulsion systems 2 3 Module 3 - Propulsion Performance Parameters

3.1 General thrust equation, Thrust of Turbojets, Thrust of Ramjet, Effective jet velocity, Jet power or thrust power

3

3.2 Propulsive power, Specific thrust and Specific Impulse, Specific fuel consumption, Thrust coefficient

2

3.3 Problems related to thrust. Energy Flow and Efficiency: Energy flow in propulsion engines, Efficiency considerations

2

3.4 Propulsive efficiency, Speed ratio, Transmission efficiency, Thermal efficiency, Overall efficiency, Problems in various efficiency

2

4 Module 4 - Jet Engine Compressors and Turbines 4.1 Principle operation of centrifugal compressor, Principle operation of axial flow

compressor– Work done and pressure rise – velocity diagrams 2

4.2 degree of reaction – free vortex and constant reaction designs of axial flow compressor – performance parameters axial flow compressors– stage efficiency

2

4.3 Principle of operation of axial flow turbines– limitations of radial flow turbines 2 4.4 Work done and pressure rise turbine blade cooling methods – stage efficiency

calculations, Problems. 3

5 Module 5 - Rocket Propulsion 5.1 Introduction, Classification of rockets, Principle of rocket propulsion, Analysis of

an ideal chemical rocket 3

5.2 Optimum expansion ratio for rockets, Basic principles of solid, liquid, and hybrid rockets and their functions and applications

3

5.3 Nuclear propulsion, Ion propulsion, Plasma propulsion, Photon propulsion, Problems.

3


AOT385 AIRCRAFT STRUCTURAL ANALYSIS CATEGORY L T P CREDIT

VAC 3 1 0 4

Preamble: Basic aim of this course is to study the static and dynamic behavior of different Structural

components.

Prerequisite: Engineering Mechanics, Strength of Materials.


CO 1 Understand the concepts of basic elasticity.

CO 2 Apply the elasticity concepts in two dimensional problems.

CO 3 Apply the energy methods in statically determinate and indeterminate systems.

CO 4 Determine the buckling loads of column member with different end conditions.

CO 5 Understand the dynamic analysis of structural components. Mapping of course outcomes with program outcomes PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO

10 PO 11

PO 12

CO 1 3 2 1 - - - - - - - - - CO 2 3 2 1 - - - - - - - - - CO 3 3 2 1 - - - - - - - - - CO 4 3 2 1 - - - - - - - - - CO 5 3 2 1 - - - - - - - - - Assessment Pattern

Bloom’s Category Continuous Assessment Tests End Semester Examination 1 2 Remember Understand 25 0 40 Apply 25 50 60 Analyse Evaluate Create Mark distribution Total Marks CIE ESE ESE Duration

150 50 100 3 hours

Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks


End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions


1. What is stress?

2. What are the types of boundary conditions?

3. Differentiate between plane stress ad plane strain.


1. Define stress function.

2. Write the general torsion equation.

3. Write short note on bending of thin plates.


1. What is temperature effect?

2. Define strain energy.

3. What are the energy methods?


1. What is Euler’s theory?

2. What are the different end conditions of a loaded column?

3. Write the limitations of Euler’s formula.


1. Define natural frequency?

2. What are the parts of mechanical system?

3. What is degree of freedom?



QP CODE: Reg No: _______________


FIFTH SEMESTER B. TECH DEGREE EXAMINATION, MONTH & YEAR

Course Code: AOT385

Course Name: AIRCRAFT STRUCTURAL ANALYSIS


PART A



1. Draw the stress-strain curve for ductile material.

2. What is principal stress?

3. Define St. Venant’s principle.

4. Explain Prandtl stress function.

5. State reciprocal theorem.

6. Define principle of superposition.

7. What are the assumptions of Euler’s formula?

8. What are the different end conditions of a loaded column?

9. What is resonance?

10. Write the equation of motion for single spring-mass system in horizontal position.

PART B



Module – 1

11. A steel wire 2 m long and 3 mm in diameter is extended by 0.75 mm when a weight W is suspended from the wire. If the same weight is suspended from a brass wire 2.5 m long and 2 mm in diameter, it is elongated by 4.64 mm. Determine the modulus of elasticity of brass if that of steel be 2.0x105 N/mm2. (14)


12. Derive the principal stresses, principal strains and shear stress for two dimensional stress systems.

(14) Module – 2

13. A cantilever of length L and depth 2h is in a state of plane stress. The cantilever is of unit thickness isrigidly supported at the end x = L and is loaded as shown in fig. Show the stress function.

(14)

14. A thin rectangular plate a x b is simply supported along its edges and carries a uniformly distributed loadof intensity q0. Determine the deflected form of the plate and the distribution of bending moment.

(14)

Module – 3

15. Calculate the vertical displacements of the quarter and the mid span points B and C of the simplysupported beam of length L and the flexural rigidity EI loaded as shown in figure.

(14)

16. Derive the equation for statically indeterminate systems using energy method. (14)

Module – 4


17. A bar of length 4 m when used as a simply supported beam and subjected to a UDL of 30 KN/m over thewhole span deflects 15 mm at the centre. Determine the crippling loads when it is used as a column withfollowing end conditions: (14)

i) Both ends pin jointedii) One end fixed and other end hingediii) Both ends fixed

18. Derive the Euler’s formula for one end fixed and the other pin jointed. (14)

Module – 5

19. (i) Derive the equation of motion for single spring-mass system in vertical position using Newton’smethod.

(8)

(ii) Write short notes on simple and compound pendulum. (6)

20. (i) Find the natural frequency of the system shown in figure. Take k = 2x105 N/m and m = 20 kg.(10)

(ii) Explain the parts of a vibration system with neat diagram. (4)


Syllabus Module 1

ELASTICITY : Stress – Notation for Forces and Stresses – Equations of Equilibrium – Boundary Conditions – Plane Stress – Principal Stress – Strain – Plane Strain – Principal Strain – Determination of Stresses and Strains – Stress-Strain Relationships

Module 2

TWO DIMENSIONAL PROBLEMS : Stress Function – St. Venant’s Principle – Bending of a Cantilever Beam – Torsion of Solid Sections – Prandtl Stress Function – Bending of Thin Plates – Buckling of Thin Plates

Module 3

ENERGY METHODS : Strain Energy – Complementary Energy – Deflection Problems – Solution of Statically Indeterminate Systems – Total Potential Energy - Principle of Superposition – Reciprocal Theorem – Temperature Effects

Module 4

COLUMNS : Euler Buckling of Columns – Inelastic Buckling – Effect of Initial Imperfection – Beam Column with Different End Conditions – Energy Method for the Calculation of Buckling Loads in Columns

Module 5

VIBRATION OF STRUCTURES : Oscillation of Mechanical System – Oscillation of Bar, Beam and Shaft with Single Degree of Freedom – Simple and Compound Pendulum – Spring Combinations – Calculation of Natural Frequency for Free and Forced Vibrations

Text and Reference Books:

1. T. H. G Megson, “An Introduction to Aircraft Structural Analysis” – Published by Elsevier Ltd, 2010.

2. T. H. G Megson, “Aircraft Structures for Engineering Students” – Butterworth-Heinemann Publisher, 5th

Edition, 2012.

3. V. P Singh, “Mechanical Vibrations” – Published by Dhanpat Rai & Co Ltd, 5th Edition, 2016.

4. Bruce K Donaldson, “Analysis of Aircraft Structures” – Published by Cambridge University Press, New York.

5. Timoshenko S., “Vibration Problems in Engineering”– John Wiley and Sons, New York, 1993.

6. Peery D J and Azar J J, “Aircraft Structures” – 2nd Edition, McGraw Hill, New York, 1999.


Course Contents and Lecture Schedule No Topic No. of Lectures 1 Module 1 -ELASTICITY

1.1 Stress – Notation for Forces and Stresses 1 1.2 Equations of Equilibrium – Boundary Conditions 1 1.3 Plane Stress – Principal Stress 1 1.4 Strain – Plane Strain – Principal Strain 1 1.5 Determination of Stresses and Strains 2 1.6 Stress-Strain Relationships 2 2 Module 2 - TWO DIMENSIONAL PROBLEMS

2.1 Stress Function - St. Venant’s Principle 1 2.2 Bending of a Cantilever Beam 2 2.3 Torsion of Solid Sections 2 2.4 Prandtl Stress Function 1 2.5 Bending of Thin Plates 2 2.6 Buckling of Thin Plates 2 3 Module 3- ENERGY METHODS

3.1 Strain Energy – Complementary Energy 1 3.2 Deflection Problems 2 3.3 Solution of Statically Indeterminate Systems 2 3.4 Total Potential Energy 2 3.5 Principle of Superposition 1 3.6 Reciprocal Theorem 1 3.7 Temperature Effects 1 4 Module 4 -COLUMNS

4.1 Euler Buckling of Columns 1 4.2 Inelastic Buckling 1 4.3 Effect of Initial Imperfection 1 4.4 Beam Column with Different End Conditions 2 4.5 Energy Method for the Calculation of Buckling Loads in Columns 3 5 Module 5 - VIBRATION OF STRUCTURES

5.1 Oscillation of Mechanical System 1 5.2 Oscillation of Bar, Beam and Shaft with Single Degree of Freedom 2 5.3 Simple and Compound Pendulum 1 5.4 Spring Combinations 1 5.5 Calculation of Natural Frequency for Free Vibration 2 5.6 Calculation of Natural Frequency for Forced Vibration 2


SEMESTER V HONOURS


AOT393 HIGH SPEED AND HIGH ENTHALPY AERODYNAMICS

CATEGORY L T P CREDIT VAC 3 1 0 4

Preamble: The course is meant to give the learners an introduction to high speed chemically reacting aerodynamics Prerequisite: Nil


CO 1 Explain and use basic theorems unsteady compressible fluid dynamics and able to solve unsteady complex problems.

CO 2 Understand the concepts of steam function velocity potential function and boundary layer theory in a compressible flow field and able to solve complex problems

CO 3 Understand the concepts of invicid hypersonic flow and simple flows and able to solve complex problems

CO 4 Apply the design concepts of highspeed aerodynamics theories CO 5 Understand the concepts of boundary layer interaction with shockwave and hypersonic

flows Mapping of course outcomes with program outcomes

PO 1


PO 11

PO 12

CO 1 3 2 1 CO 2 3 2 1 CO 3 3 2 1 CO 4 3 2 1 CO 5 3 2 1 Assessment Pattern



Mark distribution



Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions


1. Explain the working of blow down supersonic wind tunnel with suitable figure. How the testing time

can be improved.

2. A wedge of constant wedge angle is place in a decelerating unsteady flow. Explain the characteristics

of shock wave with figure

3. Explain how a moving shock wave problem can be solved.


1. Derive an expression for circulation in a compressible flow field according to Kelvin’s theorem.

2. Derive Euler’s momentum equation for the steady adiabatic inviscid flow of a compressible fluid.

3. Derive the speed of sound equation.


1. Derive the expressions for the flow field parameters in a hypersonic free stream?

2. Explain why the centrifugal correction is required?

3. Explain Newton’s sine square law and derive an expression for coefficient of pressure.


1. Why the hypersonic boundary layers are thicker?

2. Why delta wings are suitable for supersonic airplanes

3. Explain the similarity parameters in a hypersonic boundary layer


1. Derive an expression for the collision frequency and mean free path of molecules.

2. Explain notes on non-equilibrium blunt-body flows with sketches.

3. Derive the boundary layer equation for chemically reacting flow.



QP CODE: Reg No: --------------------------

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY FIFTH SEMESTER (HONS.) B. TECH DEGREE EXAMINATION

MONTH & YEAR

Course Code: AOT393

HIGH SPEED AND HIGH ENTHALPY AERODYNAMICS


PART A



1. What happened to an oblique shock when the free stream supersonic flow decelerated to subsonic flow?

2. What happened to the mass flow in a convergent nozzle when the total pressure falls down?

3. Explain why the shock wave cannot penetrate in to the subsonic region of the boundary layer formed in a supersonic flow?

4. What is the physical interpretation of stream function?

5. Why the hypersonic flow exists in lower Mach number when the free stream static pressure is decreased?

6. What happened to the density ratio across a shock wave when the free stream Mach number tent to infinity? What do this interpret?

7. What is the effect of entropy layer on aerodynamic heating?

8. Explain what are the effects of strong interaction of boundary layer?

9. Explain why the temperature distribution in a chemically equilibrium flow is higher than in a frozen flow in the nozzle flow?

10. Explain why the flow through hypersonic shock layer is diabatic?

PART B



Module 1

11. An air bottle of 10 liters consists of air at 20 bar pressure. A leak of air through a 5mm hole is

observed. Find the time taken to discharge the bottle pressure to 10bar assume the expansion process

is isothermal (14)


12. a) Explain with suitable figure how a supersonic is working of a supersonic wind tunnel (10)

b)Why a secondary throat is required in a supersonic wind tunnel? (4) Module 2

13. a) Define homenergetic flow, isentropic and homentropic flow and homentropic homenergetic flow?

(6)

b) Consider a velocity potential function Ф derive the equation of motion in terms of Ф, (8)

14. The supersonic inlet contains an oblique shock followed by a normal shock wave. If the free stream

Mach number and the flow deflection angle are 3 and 18 deg respectively, find the stagnation

pressure, stagnation temperature, static pressure, temperature and density downstream of the normal

shock wave. (14)

Module 3

15. Derive an expression for Cp as per modified Newtonian-Busemann theory and its accuracy. (14)

16. a) From Newtonian theory prove that the drag coefficient for a sphere is 1 (6)

b)Derive hypersonic shock relation in terms of hypersonic similarity parameter (8)

Module 4

17. A flat plate 2m chord and planform area of 40sq m with zero incidence is tested under the condition,

at an altitude of 30 Km from international standard condition in a hypersonic velocity of 3402m/s.

Calculate the local shear stress on the plate about 0.7m from the leading edge. Assume laminar flow,

wall temperature is adiabatic wall temperature (14)

18. a) Derive an expression for the pressure ratio in terms of growth of boundary layer thickness in a

hypersonic viscus flow. (8)

(b) Explain how the entropy layer effects on aerodynamic heating (6)

Module 5

19. Derive an expression for emission coefficient radiative heat transfer process and its solution (14)

20. Explain the temperature distribution in a chemically reacting non-equilibrium flowthrough a

convergent divergent nozzle and compare with equilibrium and frozen flow? (14)


Syllabus

Module 1

Basics of compressible fluid dynamics: - Isentropic flow through variable area passage, unsteady flow through variable area passage in both isothermal and isentropic expansion, normal and oblique shockwaves under these conditions, supersonic wind tunnels and its starting, conical flow. (Simple numerical examples). Module 2

Basics of steady multidimensional adiabatic flow in an inviscid compressible fluid: -Introduction and basics, rotation, Kelvin’s theorem, Helmoltz’s vorticity theorem, Crocco’s theorem, equation of state and velocity of sound, stream function and velocity potential function, relation between stream function and potential function. Module 3

Introduction, hypersonic shock and expansion wave relations, Newtonian flow model for both 2-D and 3-D flow, modified Newtonian theory, centrifugal correction to Newtonian theory, tangent wedge tangent cone and shock expansion method, Mach number independence, hypersonic small disturbance equation, hypersonic similarity, equivalence and blast wave theory, thin shock wave theory, (Simple numerical examples). Module 4

Hypersonic boundary layer: - similarity parameters, boundary layer equation, self-similar solution, non-similar hypersonic boundary layer, transition, turbulent boundary layer, aerodynamic heating, viscus interaction, shock wave boundary layer interaction. (Simple numerical examples). Module 5

Basics on statistical thermodynamics, kinetic theory, equilibrium and non-equilibrium inviscid flows:- equilibrium normal and oblique shock wave, chemically equilibrium 1-D nozzle flows, speed of sound in equilibrium flow, equilibrium conical flow, and equilibrium flows on blunt bodies, non-equilibrium normal and oblique shock wave, chemically non-equilibrium 1-D nozzle flows, speed of sound in non-equilibrium flows, non-equilibrium conical flow, and non-equilibrium flows on blunt bodies, binary scaling, introduction to radiative gas dynamics. Text Books

1. Fundamentals of Aerodynamics John D Anderson.


3. John D Anderson “Hypersonic and High Temperatures Gas Dynamics “

Data Book (Approved for use in the examination):

1. Rathakrishnan E, Gas Tables, Orient Blackswan Private Limited - New Delhi (2013).

2. S M Yahya, Gas Tables for Compressible Flow Calculations, New Age International Publishing, (2011).

Reference Books

1. Gas dynamics by Maurice J Zucrow, Jow D. Hoffman.


2. Aerodynamics for Engineers by John J Bertin and Russel M.

3. Shapiro, A. H., "Dynamics and Thermodynamics of Compressible Fluid Flow", Ronald Press, 1982. 4. OosthuizenP.H., &CarscallenW.E., "Compressible Fluid Flow", McGraw- Hill & Co.,1997.


No TOPIC No. of Lectures 1 Module 1

1.1 Basics of compressible fluid dynamics: - Isentropic flow through variable area passage, unsteady flow through variable area passage in both isothermal and isentropic expansion,

3

1.2 Normal and oblique shockwaves under unsteady flow condition conditions, supersonic wind tunnels and its starting,

3

1.3 Conical flow 2 2 Module 2

2.1 Basics of steady multidimensional adiabatic flow in an inviscid compressible fluid:-Introduction and basics, rotation, Kelvin’s theorem, Helmoltz’s vorticity theorem.

3

2.2 Crocco’s theorem, equation of state and velocity of sound, stream function and velocity potential function,

4

2.3 Relation between stream function and potential function 1 3 Module 3

3.1 Introduction, hypersonic shock and expansion wave relations, Newtonian flow model for both 2-D and 3-D flow, modified Newtonian theory,

4

3.2 Centrifugal correction to Newtonian theory, tangent wedge tangent cone and shock expansion method, Mach number independence,

3

3.3 Hypersonic small disturbance equation, hypersonic similarity, equivalence and blast wave theory, thin shock wave theory,

2

4 Module 4 4.1 Hypersonic boundary layer: - similarity parameters, boundary layer

equation, self-similar solution, 4

4.2 Non-similar hypersonic boundary layer, transition, turbulent boundary layer,

4

4.3 Aerodynamic heating, viscus interaction, hypersonic shock wave boundary layer interaction.

3

5 Module 5 5.1 Basics on statistical thermodynamics, kinetic theory, equilibrium and

non-equilibrium inviscid flows:- equilibrium normal and oblique shock wave, chemically equilibrium 1-D nozzle flows, speed of sound in equilibrium flow, equilibrium conical flow, and equilibrium flows on blunt bodies,

4

5.2 Non-equilibrium normal and oblique shock wave, chemically non-equilibrium 1-D nozzle flows, speed of sound in non-equilibrium flows, non-equilibrium conical flow, and non-equilibrium flows on blunt bodies,

4

5.3 Binary scaling, introduction to radiative gas dynamics 1


AOT395 HIGH SPEED PROPULSION SYSTEMS CATEGORY L T P CREDIT

VAC 3 1 0 4 Preamble: The course is meant to give the learners an introduction to high speed aerodynamics

Prerequisite: Nil


CO 1 Explain and use basic of equilibrium and non-equilibrium flow through different flow conditions.

CO 2 Apply the theorems of aerodynamics and solve complex problems CO 3 Understand the concepts of supersonic combustion and able to design scramjet. CO 4 Apply rocket theory to predict performance characteristics of solid propellant rocket

motor and able to solve complex problems.

CO 5 Apply rocket theory to predict performance characteristics of liquid propellant rocket engines and able to solve complex problems.


PO

1

PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO

10

PO

11

PO

12

CO 1 2 CO 2 3 3 1 CO 3 3 3 1 CO 4 3 3 2 1 CO 5 3 3 Assessment Pattern

Bloom’s Category Continuous Assessment Tests End Semester Examination

1 2 Remember 10 10 10 Understand 20 20 20 Apply 20 20 70 Analyse Evaluate Create Mark distribution


150 50 100 3 hours


Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions


1. Derive Euler equation for a three-dimensional Flow field and derive Bernoulli equation.

2. Explain Barotropic flow, Kelvin’s theorem, streamline, irrotational flows.

3. Explain Green’s lemma, Circulation and Vorticity, Stoke’s theorem.


1. Derive mathematical expression for stream function, potential function, equipotential line,

2. Trace stream lines and equipotential lines of the effective body for the combination of a source

and a sink equal strength in a free stream.

3. Prove that the stream function and equipotential lines are orthogonal to each other


1. Find the complex velocity of a line source?

2. Transform a circular cylinder in to a flat plate at an angle of attack α?

3. Write notes on Modified Joukowski’s transformation.


1. Demonstrate Biot and Savert law, bound vortex and trailing vortex, horse shoe vortex.

2. Derive an expression for Cl, Cd according to thin aerofoil theory.

3. An airplane having an elliptical wing all up weight is 100000N, span 20m, having a wing area

50cm2 flying at an altitude of where the density ratio 0.6 at a speed of 360Km/hr. If the lift drag

ratio is 10, estimate the parasite drag coefficient of the airplane?


1. Derive an expression for thrust produced by a propeller disc according to momentum theory.

2. An airscrew is required to produce a thrust of 4000 N at a flight speed of 120m/s at sea level. If the

diameter is 2.5 m, estimate the minimum power that must be supplied on the basis of Froude’s

theory

3. Explain the characteristics of turbulent flow.



QP CODE: Reg No: --------------------------

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY FIFTH SEMESTER (HONS.) B. TECH DEGREE EXAMINATION MONTH & YEAR

Course Code: AOT395

HIGH SPEED PROPULSION SYSTEMS


PART A


1. Sketch the temperature distribution of an equilibrium and non-equilibrium flow through a C-D Nozzle

and compare with frozen flow?

2. Explain briefly why the shockwave in a non-equilibrium flow is curve while an equilibrium is oblique?

3. Explain why the ramjets are not self-starting?

4. Sketch the schematic of a ramjet while its intake is working as super critical mode of operation?

5. Explain why supersonic combustion is essential in a high-speed air breath propulsion system?

6. Explain the importance of an isolator?

7. Explain briefly with suitable sketches progressive, regressive and neutral burning grain with figure?

8. Explain the effect of particle size in burning rate and how the desired thrust program is obtained different particle size?

9. Why the contour nozzles are preferred in liquid engines while conical nozzles are used in solid motor?

10. With the help of three typical injector discuss how atomization and mixing in the specific design are affected, and suggest criterion for selection of an injector for a liquid bipropellant system?

PART B

Answer any one full question from each module. (Each question carries 14 Marks)

Module 1

11. Derive an expression for entropy produced by chemical non-equilibrium (14)

12. a) Explain the characteristics of non-equilibrium normal and oblique shock flows? (8) b) Consider a centered Prandtl-Mayer expansion wave in a chemically reacting gas. Assume local chemical and thermodynamic equilibrium, describe how you would calculate the change in properties across this wave for a given upstream condition and a given expansion angle. (6)


Module 2

13. A ramjet engine is to be designed to produce a thrust of 100N, when flying at Mach 2 at an altitude of 11KM. Calculate the initial dimensions of the engine? Assume complete expansion in C-D Nozzle. Total pressure ratio of intake 0.85. Combustion entry Mach no is 0.2, combustion exit temperature is 1600K. Assume no loss in combustor and nozzle (14)

14. Derive the thrust equation for a ramjet engine and an expression for jet velocity. (14)

Module 3

15. a) Explain the dual mode combustion system in a scramjet engine with suitable (7)

b) Explain the characteristics of combustor flow with suitable figure? (7)

16. a) Describe the important types of hypersonic inlets with sketches (7)

b) Explain the performance parameters of scramjet engine (7)

Module 4

17. The characteristics of a propellant with a mass flow rate of 0.25kg/sec for a gas generator are as

follows.

Burn rate at 7MPa = 4mm/sec,

Burning time = 120sec,

Chamber pressure= 5MPa,

Pressure exponent = 0.5,

Propellant specific gravity = 1.65.

Determine the size of an end burning cylindrical grain (14)

18. a) Why do port – burning grains find wider application in large rocket motor? Show some typical neutral burning grain configurations generally used and compare them on the basis of loading density and neutrality (8) b) A solid propellant rocket is operating at a combustion chamber pressure of 7MPa at sealevel standard condition. The combustion chamber temperature is 3000K and the propellant consumed is 3Kg/sec. If the gas constant is 285J/kg K and the specific heat ratiois 1.22, find the nozzle exhaust velocity, throat velocity and the nozzle area expansion ratio? (6)


Module 5

19. Thrust chamber for Nitric acid – Aniline bi-propellant engine of cylindrical shape and multiple hole injector is to be designed with the following specifications. Mixture ratio 2.75, Chamber pressure = 2.06MPa, Ambient pressure = 0.101MPa, Thrust = 5000N, Chamber temperature = 4000K, Mean mole weight of exhaust gas = 25kg/mol, Ideal specific impulse = 200sec, Gas velocities in the chamber at 80m/sec, and characteristics length of 1.5m, may be assumed. Specific gravity of the propellant may be taken as 0.97 and 1.5 for aniline and nitric acid respectively. The injection pressure drop of 0.55MPa and the discharge coefficient 0.75 may be taken. Suggest suitable dimension for the chamber. Determine oxidizer and fuel flow rate, the number and diameter of respective injector orifice? (14)

20. Sketch and explain the turbo pump feed system and pressure feed system (14)

Syllabus

Module 1

Fundamentals of high temperature gas dynamics: -High temperature effects, Calculation of entropy produced by equilibrium and non-equilibrium chemically reacting gases, governing equations for inviscid non-equilibrium flows, Normal shockwave, Oblique shock waves for equilibrium and non-equilibrium chemically reacting flows, equilibrium and non-equilibrium one dimensional nozzle flows.

Module 2

Principle of operation of Ram jet, Ideal ramjet performance, Ram jet calculations, various components of Ramjet engines and their efficiencies, combustion chamber, combustion efficiency, combustion in Ramjet engine, flame stability problems in ramjet combustors –integral ram rockets. quasi one dimensional heat addition Ram jet intakes with different operation condition,(Numerical calculations).

Module 3

Principle of operation of scramjet, need of supersonic combustion, performance parameters, Scramjet inlets, starting and contraction limit, high temperature effect, blunt leadingedge effect, viscous phenomenon, boundary layer interaction and separation, design and performance of scram jet inlets, three dimensional inlet design. Combustor flow, step combustor, isolator combustor, different types of fuel injection, mixing, combustor reaction, dual mode combustor, isolator, thermal choking, and nozzles.

Module 4

Solid propellant rocket: - Thrust equation, burning rate, different types of grain for different thrust requirements, propellant casting, importance if particle size, types of ignition systems, combustion of solid propellant, solid propellant motor design, solid propellants. (Numerical calculations).


Module 5

Operating principle of liquid propellant rocket engines, propellants injectors and feed systems, Types of ignition systems, gelled propellants, gaseous propellant, selection of nozzles, combustion chamber and combustion in liquid propellant, cryogenic engines, (Numerical calculations). Text Books

1. H Cohen. G F C Rogers HIH Saravanamuthoo,”Gas Turbine Theory”. 2. Anderson, J. D, "Modern Compressible Flow", McGraw-Hill & Co.


3. Rathakrishnan E, Gas Tables, Orient Blackswan Private Limited - New Delhi (2013) 4. S. M. Yahya, Gas Tables for Compressible Flow Calculations, New Age International Publishing, 2011.

Reference Books 1. Jack D.Mattingly Elements of Gas turbine Propulsion 2. H Cohen. G F C Rogers HIH Saravanamuthoo,” Gas Turbine Theory” 3. S M Yahya Turbines, “Compressors and Fans”, McGraw- Hill & Co.,1997.


No Topic No. of Lectures

1 Module 1 1.1 Fundamentals of high temperature gas dynamics:-High temperature

effects, thermodynamics of chemically reacting gases 2

1.2 Calculation of entropy produced by equilibrium and non-equilibrium chemically reacting gases, governing equations for inviscid non-equilibrium flows,

3

1.3 Normal shockwave, Oblique shock waves for equilibrium and non-equilibrium chemically reacting flows, equilibrium and non-equilibrium one dimensional nozzle flows

4

2 Module 2 2.1 Principle of operation of Ram jet, Ideal ramjet performance, Ram jet

calculations, 3

2.2 Various components of Ramjet engines and their efficiencies, combustion chamber, combustion efficiency, combustion in Ramjet engine,

3

2.3 Flame stability problems in ramjet combustors –integral ram rockets. quasi one dimensional heat addition Ram jet intakes with different operation condition,

3

3 Module 3 3.1 Principle of operation of scramjet, need of supersonic combustion,

performance parameters, Scramjet inlets, starting and contraction limit, high temperature effect,

4

3.2 blunt leading edge effect, viscous phenomenon, boundary layer interaction and separation, design and performance of scram jet inlets, three dimensional inlet design.

3


3.3 Combustor flow, step combustor, isolator combustor, different types of fuel injection, mixing, combustor reaction, dual mode combustor, isolator, thermal choking, and nozzles.

3

4 Module 4 4.1 Fundamental of solid propellant rocket equations, thrust equation,

burning rate, different types of grain for different thrust requirements, propellant casting, importance if particle size,

3

4.2 Types of ignition systems, combustion of solid propellant, solid propellant motor design, solid propellants, different types of grain configuration for different thrust requirements,

3

4.3 Propellant casting, importance if particle size, types of ignition systems, combustion of solid propellant, solid propellant motor design, solid propellants.

3

5 Module5 5.1 Operating principle of liquid propellant rocket engines, propellants

injectors and feed systems, 3

5.2 Types of ignition systems, gelled propellants, gaseous propellant, 2 5.3 Selection of nozzles, combustion chamber and combustion in liquid

propellant, cryogenic engines,. 3


AOT397 ADVANCED CONCEPTS IN AIRCRAFT STRUCTURES


Preamble: The course is meant to give the learners to explore advanced techniques and methods involved

in the analysis of aircraft structural components.

Prerequisite: Mechanics of solids, Aircraft structures, Theory of elasticity


CO 1 Understand the aircraft structural weight and size estimation. Design the aircraft components with suitable materials.

CO 2 Analyse any kind of internal structure. Explore the buckling of thin plate and its behaviour after buckling.

CO 3 Understand the usage of cutouts in the various locations and the effects cutouts in the structural strength.

CO 4 Explore the different joints and fittings usage and analyse the load transfer behaviour. CO 5 Experience the damage detection techniques and monitor the health of the structure. Mapping of course outcomes with program outcomes

PO 1


PO 11

PO 12

CO 1 2 2 CO 2 3 3 1 CO 3 3 3 1 CO 4 3 2 1 CO 5 3 Assessment Pattern


Remember 10 10 10 Understand 20 20 20 Apply 20 20 70 Analyse Evaluate Create Mark distribution

Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks




1. Describe the Aircraft sizing and weight estimation.

2. Brief about the loads acting on aircraft.

3. Discuss about the materials used in aircraft manufacturing and its mechanical properties.


1. Discuss safe life structure requirements.

2. Describe the buckling behaviour of supporting struts of the wing.

3. Define Critical buckling load of slender structure.


1. Discuss post-buckling behaviour of thin panels.

2. Explain the curvature effects in lateral deformation.

3. Discuss about the various cutouts and its applications.


1. Discuss about the stress concentration.

2. What are the different joints used in semi-monocoque structures?

3. What is the role of fittings in load transfer?


1. What are techniques available for damage detection.

2. Explain about real time structural health monitoring

3. What is the effect residual stress?



QP CODE: Reg No: -------------------------

-

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY FIFTH SEMESTER (HONS.) B. TECH DEGREE EXAMINATION

MONTH & YEAR

Course Code: AOT397

ADVANCED CONCEPTS IN AIRCRAFT STRUCTURES


PART A


1. Define the loads acting on aircraft while landing?

2. Briefly describe sandwich construction?

3. Explain crippling load?

4. Write the differences between long and short columns?

5. Write the advantages of welded joints over riveted joints?

6. What are different types of welded joints?

7. Briefly explain the shear-lag method?

8. Describe the use of fittings according to the loading?

9. What is mean by damage tolerant model?

10. What is mean by safe-life structure?

PART B


Module 1

11. An Airplane is flying at 200 km/hr in level flight when it is pulled upward into curved path of 600m radius (see the fig-1). Find the load factor of the airplane


FIGURE 1 (14)

12. Find the weight ratio of a sandwich column of that of solid column whose material is the same as that of the sandwich facings. The core density 415 kg/m3 and the following specific cases of facing materials: (a) 2024-T3 aluminium alloy (density = 2767 kg/m3) (b) 6A1-4V titanium (density = 4428 kg/m3) (c) 321 stainless steels (density = 7916 kg/m3) (d) Inconel (density = 8303 kg/m3) (e) Beryllium (density = 1909 kg/m3) (f) Reinforce composite (unidirection)

1. Glass fiber (density = 2491 kg/m3) 2. Boron fiber (density = 2629 kg/m3) 3. Graphite (density = 41602 kg/m3)

(14)

Module 2

13. The sheet stringer panel shown in Fig 2 is loaded in compression by means of rigid members The sheet is assumed to be simply supported at the loaded ends and at the rivet lines and to be free at the sides. Each stringer has an area of 64 mm2 . Assume E=71 GPa for the sheet and stringers. Find the total compressive load P: (a) When sheet first buckles (b) When the stringers stress 𝜎𝜎𝑐𝑐 = 68 MPa (c) When the stringers stress 𝜎𝜎𝑐𝑐 = 206 MPa


FIGURE 2 (14)

14. Find the buckling load of a 1 m long and simply supported bar having a thin-walled circular cross-section 50 mm in diameter and 2 mm wall thickness. If the closed section is made into an open one by cutting a longitudinal slit over the entire length of the bar, what is the buckling load? Assume that E = 70GPa and G = 27GPa. (14)

Module 3

15. a) Explain the structural effects of cutouts in flat plate with different loading condition? (7)

b) Explain the necessary of using secondary structure on skins with cutouts? (7)

16. For the upper deck of a transport fuselage made from aluminium alloys, assume a 1.25m x 1.15m cutout with a radius r=1.9m under the three loading conditions given below, and determine the internal load redistribution in the structures surrounding the cutout. a) Given load conditions at the centerline of the cutout: b) Constant shear flow 50 N/m

FIGURE 3 (14)


Module 4

17. The fitting shown in Fig 4 is made of a 1014 aluminium forging, for which stress 𝜎𝜎𝑎𝑎𝑎𝑎=448MPa, 𝜏𝜏𝑎𝑎= 268 MPa and 𝜎𝜎𝑎𝑎𝑎𝑎𝑎𝑎 = 675 MPa. The bolt and bushing are made of steel for which 𝜎𝜎𝑎𝑎𝑎𝑎 = 861 MPa, 𝜏𝜏𝑎𝑎= 517 MPa and 𝜎𝜎𝑎𝑎𝑎𝑎𝑎𝑎 = 1206 MPa. The fitting resists limit or applied loads of 6803 kg compression and 544 3 kg tension. A fitting factor of 1.2 and bearing factor of 2.0 are used. Find the margins of safety for the fitting for various types of failure.

FIGURE 4 (14)

18. a) Explain different type of welding methods and welded joints? (6) b) A welded joint is formed by welding two plates as shown in Fig 5. The materials are aluminium alloy in 𝑇𝑇1 condition before welding and left as welded. Weld efficiency = 0.7, F=248 MPa. Find the margin of safety of this welded joint under the load of 13kN at 𝑇𝑇1 plate. Assume 𝑇𝑇1= 3mm, 𝑇𝑇2=1.5mm, S=6mm

FIGURE 5 (8)

Module 5

19. a) Explain the different damage detection techniques (6)

b) Explain anyone real-time structural health monitoring technique with application in aircraft components. (8)

20. The split beam of Fig. 6 is subjected to a pair of cyclic opening forces P with Pmax = 2000N, Pmin =0


The initial crack length is a0=40 mm. The material is 2024-T651 Al, and t=2×10−2m, ℎ = 1 × 10 − 2𝑚𝑚. The crack growth rate is given by

𝑑𝑑𝑎𝑎𝑑𝑑𝑑𝑑

= 1.6 × 10−11(∆𝐾𝐾𝐼𝐼)3.59𝑚𝑚/𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐𝑐

in which is in 𝐾𝐾𝐼𝐼 𝑀𝑀𝑀𝑀𝑎𝑎√𝑚𝑚. Find the number of cycles to failure (at which the crack becomes unstable under the load Pmax). Assume that the plane strain condition exists.

FIGURE 6 (14)

Syllabus

Module 1

Flight-vehicle imposed loads, Basic flight loading conditions, Flight-vehicle aerodynamic loads, Flight-vehicle inertia loads, Load factors for translational acceleration, Velocity-load factor diagram, Gust load factors, Behaviour and evaluation of vehicle material, Mechanical properties of materials, Equations for stress-strain curve, Fatigue, Strength-weight comparisons of materials, Sandwich construction, Airworthiness requirements, Toughness and crack growth rate. Module 2

Buckling of columns and thin plates, Long columns, Eccentrically loaded columns, Columns subject to local crippling failure, Short columns, Buckling of isotropic flat plates in compression, Ultimate compressive strength of isotropic flat sheet, Plastic buckling of flat sheet, Curved sheet in compression, Elastic shear buckling of flat plates, Elastic buckling of curved rectangular plates. Module 3

Analysis of structures with cutouts, Stiffened-web having doubler-reinforced holes, Web cutout with bent-doubler, Framing cutouts in deep shear beam, Cutouts in skin-stringer panel under axial load, Large cutouts in curved skin-stringer panel (fuselage). Module 4

Joints and fittings, Bolted or riveted joints, Fastener, Splices, Eccentric joints, Gusset joints, Welded joints, Bonded joints, Accuracy of fitting analysis, Lug analysis (bolt in shear), Tension fittings (bolt in tension), Tension clips, Gaps and the use of shims, Fatigue considerations, Eccentrically loaded connections.


Module 5

Damage analysis and structural health monitoring, Damage tolerant panels (tension), The stress cycle and the load spectra, Structural life prediction (safe-life), Structural crack growth (inspection interval), Residual strength (fail-safe design), Residual strength of beam assembly. Text Books

1. Michael Chun-Yu Niu, “Airframe Stress Analysis and Sizing”, Hong Kong Conmilit Press limited.

2. David J. Peery and J. J. Azar, “Aircraft Structures”, McGraw- Hill book Company.

Reference Books

1. 1.C. T. Sun, “Mechanics of Aircraft Structures” Wiley-Interscience.

1. E. F. Bruhn, “Analysis and Design of Flight Vehicle Structures”, 1973.

2. T.H.G. Megson, “Introduction to Aircraft Structural Analysis”, Butterworth-Heinemann.


No Topic No. of Lectures 1 Module: 1

1.1 Flight-vehicle imposed loads, Basic flight loading conditions, Flight-vehicle aerodynamic loads, Flight-vehicle inertia loads, Load factors for translational acceleration, Velocity-load factor diagram, Gust load factors

3

1.2 Behavior and evaluation of vehicle material, Mechanical properties of materials, Equations for stress-strain curve

3

1.3 Fatigue, Strength-weight comparisons of materials, Sandwich construction, Airworthiness requirements, Toughness and crack growth rate

3

2 Module: 2 2.1 Buckling of columns and thin plates, long columns, eccentrically

loaded columns, Columns subject to local crippling failure, Short columns

4

2.2 Buckling of isotropic flat plates in compression, Ultimate compressive strength of isotropic flat sheet, Plastic buckling of flat sheet

4

2.3 Curved sheet in compression, Elastic shear buckling of flat plates, Elastic buckling of curved rectangular plates

3

3 Module: 3 3.1 Analysis of structures with cutouts, Stiffened-web having doubler-

reinforced holes, Web cutout with bent-doubler 3

3.2 Framing cutouts in deep shear beam, Cutouts in skin-stringer panel under axial load

3

3.3 Large cutouts in curved skin-stringer panel (fuselage). 2 4 Module: 4


4.1 Joints and fittings, Bolted or riveted joints, Fastener, Splices, Eccentric joints, Gusset joints, Welded joints, Bonded joints

3

4.2 Accuracy of fitting analysis, Lug analysis (bolt in shear), Tension fittings (bolt in tension)

3

4.3 Tension clips, Gaps and the use of shims, Fatigue considerations, eccentrically loaded connections.

3

5 Module: 5 5.1 Damage analysis and structural health monitoring, Damage tolerant

panels (tension) 3

5.2 The stress cycle and the load spectra, Structural life prediction (safe-life), Structural crack growth (inspection interval)

3

5.3 Residual strength (fail-safe design), Residual strength of beam assembly

2


SEMESTER VI


AOT 302 HEAT TRANSFER CATEGORY L T P CREDIT

PCC 3 1 0 4 Preamble: In this course the student will learn the basic concepts of heat transfer, as it is applied to the design of engineering devices and systems, that involve transfer of heat or thermal energy. The study involves heat transfer processes by conduction, convection and radiation, their mathematical formulations and their practical solutions. Attention is also given to special heating problems encountered in high-speed high temperature flows. Prerequisite: Knowledge of thermodynamics and mathematical theory of partial differential equations Course Outcomes: After the completion of the course the student will be able to

CO 1 Formulate and solve heat conduction problems with temperature dependent thermal properties, heat generation and across multi-layer materials.

CO 2 Solve forced and free convection problems using boundary layer concepts and empirical solutions. Use of important non-dimensional parameters

CO 3 Solve radiation problems using basic radiation laws like Planck’law, Wein’s displacement law and Kirchoff’s law

CO 4 Solve design problems involving heat exchangers CO 5 Develop familiarity with special problems encountered in high speed flights and design

ofcooling systems and ablative heat shields Mapping of course outcomes with program outcomes

PO 1


PO 11

PO 12

CO 1 3 3 2 1 1 CO 2 3 3 2 1 1 CO 3 3 3 2 1 1 CO 4 3 3 2 1 1 CO 5 3 3 2 1 1 Assessment Pattern




Mark distribution

Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions


1. What are the basic modes of heat transfer and the laws governing them?

2. What is the general form of Fourier’s heat conduction law?

3. What are the effects of temperature dependent thermal conductivity and heat generation?

4. What is electrical analogy and its applications?

5. What is lumped mass concept for transient heat conduction? Under what conditions it is valid?

6. What are similarity solutions and their applications to transient heat conduction?

7. What are Biot and Fourier numbers? How to use Heisler’s charts for transient heat transfer problems?


1. What are the differences between natural free convection and forced convection?

2. What are the non-dimensional parameters governing these convective heat transfer processes?

3. How does free convection occur in atmosphere?

4. How does free convection occur over a vertical flat plate?

5. How we can use the concept of boundary layers in analysing laminar and turbulent free convection?

6. How to analyse free convection process in flows between parallel plates, over a flat plate and in

circular pipes?

7. What are the needs and applications of numerical methods for heat transfer analysis? How to solve

steady state heat conduction problems using finite difference methods?


1. What are the fundamental processes of radiation heat transfer?


2. What are the radiative properties of materials and their spectral dependence?

3. What are the fundamental laws governing radiative heat transfer?

4. What is the concept of radiosity?

5. What is the radiation shape factor and its dependence on geometries? How to use standard charts for specific geometries using shape factor algebraic laws?

6. What are radiation heat shields and how to design them?


1. What are heat exchangers and their applications? How they are classified?

2. What are the temperature distributions in parallel flow and counter flow heat exchangers?

3. How to use LMTD and e-NTU methods to design heat exchangers and what are their limitations?

4. What are special heat exchangers like boilers and condensers?

5. What are compact heat exchangers?


1. What are the heat transfer problems in high-speed hypersonic flights?

2. What is the concept of adiabatic wall temperature and the idea of recovery factor?

3. What does Eckert number signify? What are the various cooling methods for combustion

chambers and rockets and missiles?

4. What are the materials used for high speed thermal protection systems?

5. What is ablation process? How to analyse one dimensional ablation using moving boundary

concept?



QP CODE: Reg No: --------------------------

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY SIXTH SEMESTER B. TECH DEGREE EXAMINATION

MONTH & YEAR


HEAT TRANSFER

Max.Marks:100 Duration: 3 Hours PART A


1. Write down the general three-dimensional heat conduction equation with heat generation and show that for the case of steady heat transfer through a material of constant physical properties with no heat generation this equation reduces to the Laplace’s equation.

2. The flat roof of an electrically heated home measures 8m by 6m and it consists of 25 cm thick concrete slab, whose conductivity k = 0.8 W/m/K. If the interior of the house is maintained at 25 deg C while the outside ambient temperature is 0 deg C, calculate the heat loss through the roof during one night for 10 hours

3. What is critical thickness of insulation?

4. Define Nusselt number and explain its physical significance

5. Explain the need for numerical solutions to the heat transfer problems. What are the different types of boundary conditions that are normally used in obtaining the solutions

6. Distinguish bewteen Irradiation G and Radiosity J

7. What is Wein’s displacement law? Using this law, estimate the surface temperature of the Sun knowing that the its radiant energy has peak at a wave length λ = 0.52 μm.

8. Briefly explain how the different types of heat exchangers can be classified

9. Mention different types of cooling methods adopted in the design of structure of high-speed vehicles

10. A missile is flying at Mach No. Of 6 at an altitude of 14 Km where the ambient temperature is 209 deg K. What is the total temperature and the adiabatic wall temperature if the flow is assumed to be laminar?


PART B Answer any one full question from each module.

(Each question carries 14 Marks) Module 1

11. A 0.5m diameter thin-walled spherical tank containing liquid nitrogen at 80 deg K is covered with a 25 mm thick insulation layer made of compressed silicon powder having a thermal conductivity of 0.0017 W /m/K. The outer surface of the tank has a convective heat transfer coefficient of 20 W/m2/K and the ambient temperature is 37 deg C. Calculate the heat transfer rate and the amount of boil-off of the liquid nitrogen, taking the density ρ = 804 Kg/m3 and the latent heat of vaporisation as 200 KJ/Kg.

(14) 12. a) If the conductivity of a solid material varies linearly with temperature as k(T) = ko(1+βT), show that

the heat flux across a wall of thickness L whose end surfaces are maintained at temperatures T1 and T2

is given by qw= - kav(T2-T1)/L where kav is the thermal conductivity evaluated at the average temperature Tav given by (T1 + T2) / 2.

(8) b)Air flows over a rectangular plate having dimensions 0.5 m x 0.25 m. The free stream temperature

of the air is 300°C. At steady state, the plate temperature is 40C. If the convective heat transfer coefficient is 250 W/m2/K, determine the heat transfer rate from the air to one side of the plate.

(6) Module 2

13. a) An electrically heated thin foil of length 25 mm and width 8 mm is used as a sensor for measuring the velocity of an air stream that has a temperature of 32 deg C. The foil is internally heated from both sides of the foil and dissipates 0.5 W. Using this data and the air properties at 20 deg C estimate the velocity of the air stream

(10) b)Explain the need for numerical solutions to the heat transfer problems. What are the different types of boundary conditions that are normally used in obtaining the solutions?

(4) 14. a) A solar concentrator causes a heat flux of 2000 W/m2 on tube of 60 mmID.Pressurized water flows

through the tube at a rate of 0.01 kg/s. If the bulk temperature at inletis 20°C, what will be the length required to heat the water to a bulk temperature of 80°C. Alsofind the wall temperature at exit. Assume fully developed conditions.

(14)

Module 3

15. a)A long hemispherical groove is as shown below. Find the view factor F12


(9)

b)Distinguish between Irradiation G and Radiosity J (5)

16. A furnace is shaped like a long equilateraltriangular duct (as shown above) where the width of each

side is 2 m. Heat is supplied from the base surface, whose emissivity is ε1 = 0.8, at a rate of 800 W/m2 while the side surfaces, whose emissivities are 0.5, are maintained at 500 K. Neglecting the end effects, determine the temperature of the base surface. Can you treat this geometry as a two-surface enclosure?

(14)

Module 4

17. a) Show that the use of lograthmic mean temperature difference (LMTD) always results in conservative design of heat exchangers compared to using the arithmetic temperature difference (AMTD).

(6)


b) Cold water enters a counter-flow heat exchanger at 10 deg C at a rate of 8 kg/s, where it is heated by a hot water stream that enters at 70 deg C at a rate 2 kg/s, as shown in the figure above. Assuming that the specific heat of water remains constant at 4184 J/kg/K, determine the maximum possible heat transfer rate and the corresponding outlet temperatures of cold and hot water streams.

(8)

18. a) Briefly explain how the different types of heat exchangers can be classified (4)

b) A concentric tube heat exchanger is used to cool the lubricating oil of a large diesel engine The inner tube is 30 mm diameter and is 2 mm thick and is made of stainless steel k=16 W/m/K. Cooling water flows through the inner tube at a rate of 0.3 Kg.s . The outer tube is 50 mm diameter through which oil flows at a rate of 0.15 Kg/s. The oil cools from 90 deg C to 50 deg C and water is available at 10 deg C. Calculate the length of the tube for parallel flow and counter flow heat exchangers configurations

(10)

Module 5

19. a) Show that the velocity of an ablating surface is given by

( ),

,

c wa

f m w i

qV

L c T Tρ ρ=

+ −where qcw is the heat flux Lf is the heat of ablation Tm is the ablation

temperature Twi is the initial surface temperature and ρ is the density (7)

b) For a constant heat flux of 3 MW / m2, compute the ablation velocity using the following property values Cp 1256 J/Kg/K ρ = 1600 Kg/m3 k = 0.8655 W/m/K,

Latent Heat = 9.304 MJ/kg. Tablation = 1650 deg C Tinitial = 15 deg C (7)

20. Starting from unsteady one-dimensional heat conduction equation, derive the governingequation for a moving boundary problem that moves with a velocity V, by thecoordinate transformation

ay V tη = −

2

2 0aVd T dTd dη α η

+ =

Write down also the general solution of this equation (14)


Syllabus Module 1

Introduction to heat transfer and its relation to thermodynamics. Basic modes of heat transfer and the laws governing them. Fourier’s law and derivation of general three-dimensional heat conduction equation and the boundary conditions. One dimensional steady state heat conduction in composite mediums and with variable thermal properties and heat generation. Idea of electrical analogy and use of thermal resistance and capacitance concepts. Idea of critical thickness of insulation. Heat transfer in extended surfaces and design of fins. One dimensional transient heat conduction analysis and the idea of lumped mass analysis and its validity. Use of similarity solutions for heat transfer problems in semi-infinite and infinite solids. Application of non-dimensional parameters Fourier number and Biot number and the use of transient temperature (Heisler’s) charts Module 2

Free and forced convection and non-dimensional parameters Nusselt, Prandtl and Eckert and Grashof numbers. Free convection in atmosphere. Free convection on a vertical flat plate. Empirical relation for heat transfer. Concept of Laminar and turbulent convective heat transfer analysis using the boundary layer concepts in flows between parallel plates. over a flat plate and in a circular pipe. Need and application of numerical techniques in solving heat transfer problems. Use of finite difference method for solving steady stat heat conduction problems. Module 3

Introduction to physical mechanism of radiation heat transfer. Radiation properties of materials and their wave length dependence. Planck’s radiation Law. Wein’s displacement law and Kirchoff’s law. Formulation of radiation shape factors for different geometries Concept of radiosity. Stefan-Boltzmann law Heat exchange between non-black bodies. Design of radiation shields. Module 4

Heat exchangers and their classifications and applications. Temperature distribution in parallel flow and counter-flow heat exchangers. Concept of overall heat transfer coefficient. Design of heat exchangers using LMTD and e-NTU methods. Special heat exchangers like boilers and condensers and compact heat exchangers Module 5

Heat transfer problems in high-speed hypersonic flows. Adiabatic wall temperature and the idea of recovery factor and Eckert number. Various cooling techniques and Heat transfer in combustion chambers. Ablation process materials and their applications in thermal protection against aerodynamic heating. Concept of moving boundary value problems and its application to the design of ablative heat shields. Text Books:

1. S.C. Sachdeva, “Fundamentals of Engineering Heat & Mass Transfer”, Wiley Eastern Ltd., New Delhi,1981.

2. Yunus A. Cengel, Heat Transfer – A Practical Approach, Tata McGraw Hill Edition, 2003. 3. P.K. Nag, “Heat and Mass Transfer “, Third edition, Tata=McGraw Hill publications, 2011


4. F.P. Incropera and D.P. Dewitt, “Fundamentals of Heat and Mass Transfer “, John Wiely and Sons

Publications, 2006.

5. FrankKreith, Raj M. Manglik, Mark S. Bohn, ‘Principals of Heat Transfer’, Seventh Edition, Cengage Learning, 2011.

Reference Books:

1. C.Y.Chow, “Introduction to Computational Fluid Dynamics”, John Wiley, 1979. 2. J.P. Holman, “Heat Transfer”, McGraw-Hill Book Co., Inc., New York, 6e, 1991. 3. John H. Lienhard, “A Heat Transfer Text Book”, Prentice Hall Inc., 1981 4. P. S. Ghoshdasidar , “Computer simulation of flow and Heat transfer” McGraw-Hill Book Co, Inc,

NewDelhi, 1998 5. M. NecatiOzisik,’Heat Transfer, A Basic Approach’ , McGraw Hill, New York, 2005.

E-Books/Web references:

1. John H Lienhard, ‘A Text book of Heat Transfer’, 4th Edition, 2. NPTEL Heat Transfer course for Mechanical Engineering,http://nptel.ac.in/courses/112101097/ 3. Heat Transfer, Chris Long & Naser Sayma, www.bookboon.com



1 Module 1 1.1 Introduction Basic modes of heat transfer - Fourier’s law and

derivation of general three-dimensional heat conduction equation and the boundary conditions.

2

1.2 One dimensional steady state heat conduction in composite mediums and with variable thermal properties and heat generation. Idea of electrical analogy and use of thermal resistance and capacitance concepts. Idea of critical thickness of insulation.

2

1.3 Heat transfer in extended surfaces and design of fins. 2 1.4 One dimensional transient heat conduction analysis and the idea of

lumped mass analysis and its validity. 1

1.5 Use of similarity solutions for heat transfer problems in semi-infinite and infinite solids.

1

1.6 Application of non-dimensional parameters Fourier number and Biot number and the use of transient temperature (Heisler’s) charts

1

2 Module 2 2.1 Free and forced convection and non-dimensional parameters Nusselt,

Prandtl and Eckert and Grashof numbers. 1

2.2 Free convection in atmosphere. Free convection on a vertical flat plate. Empirical relations for heat transfer.

2

2.3 Concept of Laminar and turbulent convective heat transfer analysis using the boundary layer concepts

2


2.4 Analysis of free convection between parallel plates. over a flat plate and in a circular pipe.

2

2.5 Need and application of numerical techniques in solving heat transfer problems. Use of finite difference methods for steady state heat conduction problems

2

3 Module 3 3.1 Introduction to physical mechanism of radiation heat transfer. 1 3.2 Radiation properties of materials and their wavelength dependence.

and Planck’s radiation Law. Wein’s displacement law and Kirchoff’s law.

2

3.3 Formulation of radiation shape factors for different geometries Concept of radiosity. Use of standard charts

2

3.4 Stefan-Boltzmann law Heat exchange between non-black bodies. 2 3.5 Design of radiation shields. Heat transfer in enclosed spaces 2 4 Module 4

4.1 Heat exchangers and their classifications and applications. 2 4.2 Temperature distribution in parallel flow and counter-flow heat

exchangers. 2

4.3 Concept of overall heat transfer coefficient. 2 4.4 Design of heat exchangers using LMTD and e-NTU methods. 3 5 Module 5

5.1 Heat transfer problems in high-speed hypersonic flows and aerodynamic heating

2

5.2 Adiabatic wall temperature and the idea of recovery factor and Eckert number.

1

5.3 Various cooling techniques and Heat transfer in combustion chambers.

2

5.4 Ablation process, materials and its applications in thermal protection against aerodynamic heating.

2

5.5 Concept of moving boundary value problems and its application to the design of ablative heat shields.

2


AOT304 VIBRATION AND AERO ELASTICITY CATEGORY L T P CREDIT PCC 3 1 0 4

Preamble: Basic aim of this course is to study the dynamic behaviour of different structural components

and the interaction of aerodynamic, elastic and inertia forces.

Prerequisite: Engineering Mechanics, Strength of Materials, Aircraft Structures and Flight Mechanics.


CO 1 Determine the natural frequency of free, damped and forced vibration for different conditions

CO 2 Understand the vibrational concepts of several degrees of freedom systems CO 3 Apply the approximate methods to find the natural frequency CO 4 Understand the vibrational concepts of elastic bodies CO 5 Understand the aeroelastic instabilities and the methods of prevention



PO 11

PO 12

CO 1 3 2 1 - - - - - - - - - CO 2 3 2 1 - - - - - - - - - CO 3 3 2 1 - - - - - - - - - CO 4 3 2 1 - - - - - - - - - CO 5 3 2 1 - - - - - - - - -

Assessment Pattern


Remember Understand 25 25 50 Apply 25 25 50 Analyse Evaluate Create

Mark distribution


150 50 100 3 hours



Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks.



1. Determine the natural frequency of free vibration.

2. Define simple harmonic motion.

3. Explain the transmissibility condition.


1. What are the types of vibration absorber?

2. What are the principle mode of vibration?

3. Define Hamilton’s principle.


1. Differentiate between Rayleigh’s method and Holzer’s method.

2. How to find the natural frequencies of the system using Stodola’s method?

3. Write the procedure of Rayleigh-Ritz method.


1. Derive the equation of motion for longitudinal vibration of bars.

2. Differentiate between boundary and initial conditions.

3. Write the wave equation for vibration of strings.


1. Describe the different types of flutter?

2. How to prevent the aero elastic instabilities?

3. What is aileron control reversal?



QP CODE: Reg No: _______________


SIXTH SEMESTER B. TECH DEGREE EXAMINATION, MONTH & YEAR

Course Code: AOT304

VIBRATION AND AEROELASTICITY


PART A Answer all questions


1. Define free, damped and forced vibrations.

2. In what way accelerometer is different from vibrometer?

3. What is an Eigen value problem?

4. What are static and dynamic couplings?

5. How to find natural frequencies using Holzer method?

6. Using Dunkerley’s method find the natural frequency of a double pendulum with equal masses and lengths.

7. What are the assumptions of a continuous system?

8. Write the one-dimensional wave equation for lateral vibrations of the string.

9. When the wing is said to be torsionally divergence?

10. What is critical aileron-reversal speed?

PART B Answer one full question from each module

(Each question carries 14 marks) Module – 1

11. A thin semi-circular cylinder of radius r and mass m slides on the horizontal surface without slipping.

Determine the natural frequency by Rayleigh’s method. (14)


12. a) Determine the following for a vibrating system with viscous damping subjected to harmonic excitation of 10 N. The mass of 1 kg is suspended by a spring of stiffness 1000 N/m and damper capacity of 40 N-s/m. (10)

a) Resonance frequency b) Phase angle at resonance c) Amplitude at resonance d) Frequency corresponding to peak amplitude e) Damped frequency

b) Write short notes on vibration measuring instruments. (4)

Module – 2

13. a) The main vibration system consists of mass m1 supported by spring of stiffness k1 which is subjected to an excitation Fosin ωt. And a vibration absorber consists of mass m2 and spring with stiffness k2. Find out the amplitudes for coupling of main system and vibration absorber. (8)

b) Use Hamilton’s principle to derive the equation of motion of the system shown in figure.

(6)

14. Determine the natural frequencies of the system shown in figure. (14)


Module – 3

15. Find the fundamental natural frequency and the corresponding mode shape for the system shown for k1 = k2 = k3 and m1 = m2 = m3. (14)

16. Find the natural frequency of the following system by using Stodola’s method. Take E = 1.96x1011 and I = 4x10-7. (14)

Module – 4

17. Determine the normal functions in transverse vibration for a simply supported beam of length l and uniform cross section. (14)

18. Derive the equation of motion for vibration of strings. (14)


Module – 5

19. Derive an expression for the aileron control reversal speed for a 2-D wing with aileron attached. (14)

20. Using Collar’s triangle, explain various aeroelastic phenomena in detail. (14)

Syllabus

Module 1

SINGLE DEGREE OF FREEDOM SYSTEMS:Vibration Terminologies – Simple Harmonic Motion, Free Vibrations – Newton’s Law – D’ Alembert’s Principle – Spring Combination – Energy Method – Rayleigh’s Method – Simple and Compound Pendulum – Longitudinal, Transverse and Torsional Vibrations, Damped Vibrations – Types – Differential Equations – Logarithmic Decrement, Forced Vibrations – With and Without Damping – Support Excitation – Vibration Isolation – Transmissibility – Vibration Measuring Instruments

Module 2

SEVERAL DEGREES OF FREEDOM SYSTEMS: Two Degrees of Freedom Systems – Coordinate Coupling – Principle Co-ordinates – Principle Modes – Vibration Absorber, Multi Degrees of freedom Systems – Orthogonality Principle – Hamilton’s Principle – Eigen Value Problems

Module 3

APPROXIMATE METHODS: Rayleigh’s Method – Dunkerley’s Method – Holzer’s Method – Stodola Method – Matrix Method – Matrix Iteration Method – Rayleigh-Ritz Method

Module 4

CONTINUOUS SYSTEMS: Vibration of Strings – Longitudinal Vibration of Bars – Lateral Vibration of Beams – Torsional Vibration of Shafts

Module 5

AEROELASTICITY: Aero Elasticity Concepts – Coupling – Collar’s Triangle – Aero Elastic Instabilities and their Prevention – Wing Divergence – Loss and Reversal of Aileron Control – Flutter and its Prevention

Text Books

1. V P Singh, “Mechanical Vibrations”, Dhanpat Rai & Co (P) Ltd 2. Grover. G.K., “Mechanical Vibrations”, 7th Edition, Nem Chand Brothers, Roorkee, India, 2003 3. Thomson W T, “Theory of Vibration with Application” - CBS Publishers, 1990. 4. Fung Y.C., “An Introduction to the Theory of Aeroelasticity” – John Wiley & Sons, New York, 1995.


Reference Books

1. Timoshenko S., “Vibration Problems in Engineering”– John Wiley and Sons, New York, 1993. 2. Tse. F.S., Morse, I.F., Hinkle, R.T., “Mechanical Vibrations”, – Prentice Hall, New York, 1984. 3. Bisplinghoff R.L., Ashley H and Hoffman R.L., “Aeroelasticity” – Addision Wesley Publication, New York,

1983. 4. Tongue. B. H., “Principles of Vibration”, Oxford University Press, 2000.



1 Module 1 1.1 Vibration Terminologies – Simple Harmonic Motion 1

1.2 Free Vibrations – Newton’s Law – D’ Alembert’s Principle – Spring Combination

2

1.3 Energy Method – Rayleigh’s Method 3

1.4 Simple and Compound Pendulum – Longitudinal, Transverse and Torsional Vibrations

1

1.5 Damped Vibrations – Types – Differential Equations – Logarithmic Decrement

3

1.6 Forced Vibrations – With and Without Damping – Support Excitation 3 1.7 Vibration Isolation – Transmissibility – Vibration Measuring Instruments 1 2 Module 2

2.1 Two Degrees of Freedom Systems – Coordinate Coupling 2 2.2 Principle Co-ordinates – Principle Modes 1 2.3 Vibration Absorber 2 2.4 Multi Degrees of freedom Systems – Orthogonality Principle 1 2.5 Hamilton’s Principle 2 2.6 Eigen Value Problems 2 3 Module 3

3.1 Rayleigh’s Method 1 3.2 Dunkerley’s Method 1 3.3 Holzer’s Method 1 3.4 Stodola Method 1 3.5 Matrix Method 1 3.6 Matrix Iteration Method 1 3.7 Rayleigh-Ritz Method 1 4 Module 4

4.1 Vibration of Strings 2 4.2 Longitudinal Vibration of Bars 2 4.3 Lateral Vibration of Beams 2 4.4 Torsional Vibration of Shafts 2


5 Module 5 5.1 Aero Elasticity Concepts – Coupling 1 5.2 Collar’s Triangle 1 5.3 Aero Elastic Instabilities and their Prevention 1 5.4 Wing Divergence 1 5.5 Loss and Reversal of Aileron Control 1 5.6 Flutter and its Prevention 1


AOT306 NON-AIRBREATHING PROPULSION CATEGORY L T P CREDIT PCC 3 1 0 4

Preamble: The course is meant to give the learners an introduction to high speed non air breathing propulsion systems. Prerequisite: Nil Course Outcomes: After the completion of the course the student will be able to

CO 1 Understand the basic concepts of operating characteristics of rockets and able to solve basic problems

CO 2 Understand the basic concepts and operating characteristics of solid propellant rocket motor and able to solve basic problems

CO 3 Understand the basic concepts and operating characteristics of liquid propulsion system and able to solve basic problems

CO 4 Understand the basic concepts and operating characteristics of hybrid rockets and different kind of nozzles applied to rocket propulsion and able to solve basic problems

CO 5 Understand the basic concepts of other than chemical rockets. Mapping of course outcomes with program outcomes

PO 1


PO 11

PO 12

CO 1 2 2 CO 2 3 3 1 CO 3 3 3 1 CO 4 3 2 2 1 CO 5 3 Assessment Pattern


Remember 10 10 10 Understand 20 20 20 Apply 20 20 70 Analyse Evaluate Create Mark distribution

Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks


Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions


1. Derive an expression for coefficient of thrust.

2. Derive an expression for characteristic velocity, effective exhaust velocity and jetvelocity.

3. Discuss the effect of molecular weight of jet velocity.


1. How the particle size affects the burning rate,

2. Discuss the effect of chamber pressure on burning rate.

3. Discuss the how a desired thrust program can be achieved by desired thrust program


1. What are the different types of cooling system adopted for liquid propulsion system explain?

2. Explain the different types of injectors?

3. Explain the function of turbo pump feed system?


1. Is the regenerative cooling system adaptable in a hybrid rocket explain.

2. Explain the working of an inverse hybrid rockets?

3. Why the conical nozzles are not suitable for liquid engine explain?


1. Explain the working of a fission rocket engine.

2. Explain the working of electrical propulsion system

3. Explain how the solar energy can be used for propulsion?



QP CODE: Reg No: --------------------------


MONTH & YEAR

Course Code: AOT306

NON- AIRBREATHING PROPULSION


PART A Answer all Questions


1. Write thrust equation, explain the effect of trust with altitude according to this equation?

2. What is specific impulse and deduce total impulse?

3. Explain what is progressive regressive and neutral burning propellant grain?

4. Write the demerits of solid propellants?

5. Explain what is regenerative cooling system in liquid engines?

6. Explain why a high pressure injection system is needed for injection of fuel and oxidizer?

7. Explain why the conical nozzles are suitable for solid booster?

8. Explain the effect of particle size in burning rate and how the desired thrust program is obtained

different particle size?

9. Why the solar rockets important for space propulsion?

10. What are the different sources of nuclear energy used for rocket propulsion?

PART B

Answer any one full question from each module (Each question carries 14 Marks)

Module 1

11. A rocket engine develops a thrust of 10KN while consuming 3.5kg/s of propellants having an energy content of 25MJ/kg. When the vehicle velocity is 500m/s, determine specific impulse, specific propellant consumption, effective exhaust velocity, thrust power, and overall efficiency (14)

12. a) For an ideal rocket with characteristic velocity is1800m/s, the thrust coefficient is 1.4, the radius


of the throat is 0.09m, the burned propellant flow rate is 40kg/s, calculate the specific impulse, thrust and the chamber pressure (8)

b) Derive an expression for internal efficiency, propulsive efficiency and overall efficiency(6)

Module 2

13. The characteristics of a propellant with a mass flow rate of 0.5kg/sec for a gas generator are as follows. Burn rate at 7MPa = 4mm/sec, Burning time = 120sec, Chamber pressure = 5MPa, Pressure exponent = 0.5, Propellant specific gravity = 1.65. Determine the size of an end burning cylindrical grain nozzle (14)

14. Explain the working of a solid propellant rocket motor with suitable sketch? What are the different types of ignition system used in solid propellants explain with sketches (14)

Module 3

15. Sketch and explain a bi-propellant liquid propulsion system? (14)

16. a) What air tank volume is required to pressurize the propellant tank of 8500N thrust rocket thrustchamber using 90% hydrogen per oxide as a propellant with chamber pressure of 5 MPa for 50 secin conjunction with a solid catalyst The air tank pressure is 17MPa. Allow 1.2% residual propellant(7)b)Sketch and explain different types of ignition system used in liquid engines (7)

Module 4

17. A convergent divergent nozzle of area ratio of 3.5 is expanded to an atmosphere of 1bar 288K. Find

the total pressure, temperature, density, exit Mach number, jet velocity, throat static pressure,

temperature and velocity of air at throat for optimum expansion

(14)

18. a) Sketch and explain the working of a hybrid rockets (8) b) Explain the contour nozzles are suitable for liquid engines? What are the problems associated with contour nozzles in a solid propellant rockets (6)

Module 5 19. Sketch and explain the working of fission and fusion nuclear rockets? (14)

20. Sketch and explain working of any two electric propulsion system (14)


Syllabus

Module 1

Fundamentals and principles and of rockets and its operation, basic principles and thrust equation, specific impulse, total impulse, exhaust velocity, characteristic velocity, thrust coefficient and mass flow coefficient, design parameters for rocket engine, energy flow and efficiencies, (Basic numerical calculations). Module 2

Solid propellant rocket motor:- General features, solid propellants and its chemical compositions, double bas propellant, composite propellant, desirable properties and its demerits, combustion of solid propellant, burning rate and its relation with temperature, erosive burning, combustion instability, strand and T- burner, regressive, neutral and progressive, propellant grain configuration restricted and unrestricted burning, ignition, different loads on propellant during flight, (Basic numerical calculations). Module 3

Liquid propellant rocket engines: - Comparison with other propulsion system, disadvantages of liquid engines, liquid propellants, monopropellant, bi-propellant, selection of liquid propellants and bi-propellant combination, pressure and turbo pump feed system, ignition of propellants, cooling system, regenerate cooling, injectors for liquid propellant rockets Thrust control and cooling in liquid propellant rockets and the associated heat transfer problems. Combustion instability in liquid propellant rockets. Problems associated with operation of cryogenic engines. Module 4

Hybrid rocket engines, inverse hybrid rocket engines, comparisons and its limitations, types of nozzles used for rocket application, effect of back pressure on nozzles, over expanded under expanded and optimum expanded nozzles, effect of altitude on nozzle performance. Rocket dispersion and launching problems (Basic numerical calculations). Module 5

Other non-air breath propulsion systems: - Nuclear rockets, electric rocket engines, electro thermal propulsion, electrostatic propulsion, solar thermal rocket, solar sail, Text Books

1. George P Sutton, “Rocket Propulsion Elements”



S M Yahya, Gas Tables for Compressible Flow Calculations, New Age International Publishing. Reference Books

1. 1.Hill and Peterson, Non-Air breath Propulsion

2. P Balachandran, Modern Compressible flow”



No Topic No. of Lectures 1 Module 1

1.1 Fundamentals and principles and of rockets and its operation, basic principles and thrust equation,

2

1.2 specific impulse, total impulse, exhaust velocity, characteristic velocity, thrust coefficient and mass flow coefficient,

3

1.3 design parameters for rocket engine, energy flow and efficiencies, 3 2 Module 2

2.1 Solid propellant rocket motor: - General features, solid propellants and its chemical compositions, double bas propellant, composite propellant, desirable properties and its demerits,

2

2.2 combustion of solid propellant, burning rate and its relation with temperature, erosive burning, combustion instability, strand and T- burner, regressive, neutral and progressive,

3

2.3 propellant grain configuration restricted and unrestricted burning, ignition, different loads on propellant during flight.

3

3 Module 3 3.1 Liquid propellant rocket engines: -. Comparison with other propulsion

system, disadvantages of liquid engines, liquid propellants, monopropellant, bi-propellant, selection of liquid propellants and bi-propellant combination,

3

3.2 pressure and turbo pump feed system, ignition of propellants, cooling system, regenerate cooling, injectors for liquid propellant rockets Thrust control and cooling in liquid propellant rockets and the associated heat transfer problems.

4

3.3 Combustion instability in liquid propellant rockets. Problems associated with operation of cryogenic engines, cryogenic engines

4

4 Module 4 4.1 Hybrid rocket engines, inverse hybrid rocket engines, comparisons

and its limitations, 4

4.2 types of nozzles used for rocket application, effect of back pressure on nozzles, over expanded under expanded and optimum expanded nozzles,

4

4.3 effect of altitude on nozzle performance. Rocket dispersion and launching problems.

3

5 Module 5 5.1 Other non-air breath propulsion systems: - Nuclear rockets, electric

rocket engines, 2

5.2 electro thermal propulsion, electrostatic propulsion, 2 5.3 solar thermal rocket, solar sail, plasma propulsion 3


AOT308 COMPREHENSIVE COURSE WORK CATEGORY L T P CREDIT PCC 1 0 0 1

Preamble: Objective of this course is to assess the comprehensive knowledge gained in core courses relevant to the branch of study. Also, to comprehend the application/practical oriented questions asked and answer them with confidence.

Prerequisite: Aerodynamics, Aircraft structures, Aircraft propulsion, Flight mechanics, Avionics systems and instruments.


CO 1 Apply the theories and techniques used in aerodynamics. CO 2 Analyse the design concepts and methods used in aircraft structures. CO 3 Apply the concepts and working principles used in aircraft propulsion. CO 4 Analyse the stability and various maneuvering used in flight mechanics. CO 5 Apply the design and working principles of various avionics systems and instruments.



PO 11

PO 12

CO 1 3 2 1 - - - - - - - - - CO 2 3 2 1 - - - - - - - - - CO 3 3 2 1 - - - - - - - - - CO 4 3 2 1 - - - - - - - - - CO 5 3 2 1 - - - - - - - - -

Assessment Pattern

Bloom’s Category Continuous Assessment Test (ORAL EXAM)

End Semester Examination (WRITTEN EXAM)

Remember Understand Apply 30 30 Analyse 20 20 Evaluate Create

Assessment

Oral examination – To be conducted by the college (@ three students/hour) covering all the courses up to and including V semester – 50 marks

Written examination - To be conducted by the Dept. on the date announced by the University– common to all students of the same branch – objective type (1.5-hour duration)– 50 multiple choice questions (4 choices) of 1 mark each covering the five modules as per mentioned in the syllabus. Questions are set by the University - no


negative marks – 50 marks. Note: Both oral and written examinations are mandatory. But separate minimum marks are not insisted for pass. If a student does not complete any of the two assessments, grade I shall be awarded and the final grade shall be given only after the completion of both the assessments. The two hours allotted for the course may be used by the students for discussion, practice and for oral assessment. Course Level Assessment Questions


1) Which of the following airfoil will have location of the maximum camber at half chord length from the leading edge? a) NACA 5212 b) NACA 1225 c) NACA 2215 d) NACA 2512

2) An ideal fluid is a a) One which obeys Newton’s law of viscosity. b) Frictionless and incompressible. c) Very viscous. d) Frictionless and compressible


1) A material can return to normal after it has been deformed due to its elasticity. a) True b) (B) False c) Cannot determine d) Partially correct

2) Poisson's ratio is defined as the ratio of

a) longitudinal stress and longitudinal strain b) longitudinal stress and lateral stress c) lateral stress and longitudinal stress d) lateral stress and lateral strain


1) Combustion in gas turbine engines is ideally represented as the following process: a) Adiabatic b) Isentropic c) Isobaric d) Isochoric

2) The pressure ratio in any one stage of a jet engine compressor is limited by

a) Entry stagnation temperature in that stage


b) entry Mach number in that stage c) Pressure gradient induced separation in that stage d) mass flow rate in that stage


1) Lift on an aircraft climbing vertically up is a) equal to its weight b) zero c) equal to the drag d) equal to the thrust

2) For an airplane to be statically stable, its centre of gravity must always be

a) ahead of wing aerodynamic centre b) aft of the wing aerodynamic centre c) ahead of neutral point d) aft of neutral point


1) Which of the following instruments are works on the basis of pitot-static system? a) Air speed indicator b) Altimeter c) Vertical speed indicator d) Turn and slip indicator

2) Which one of the following flight instruments is used on an aircraft to determine its attitude in flight? a) Vertical speed indicator b) Altimeter c) Artificial Horizon d) Turn-bank indicator


Model Question paper QP CODE: Reg No: _______________


SIXTH SEMESTER B. TECH DEGREE EXAMINATION, MONTH & YEAR

Course Code: AOT308

COMPREHENSIVE COURSE WORK

Max. Marks: 50 Duration: 1.5 hours

Answer all questions (Each question carries 1 mark)

1) Which of the following airfoil will have location of the maximum camber at half chord length from the leading edge? a) NACA 5212 b) NACA 1225 c) NACA 2215 d) NACA 2512

2) Which one of the following flight instruments is used on an aircraft to determine its attitude in flight? a) Vertical speed indicator b) Altimeter c) Artificial Horizon d) Turn-bank indicator

3) In an aircraft, elevator control effectiveness determines a) Turn radius. b) forward-most location of the centre of gravity. c) Rate of climb. d) aft-most location of the centre of gravity.

4) Winglets are used on wings to minimize a) skin friction drag b) profile drag c) wave drag d) induced drag

5) A conventional altimeter is a) Pressure transducer b) Temperature transducer c) Density transducer d) Velocity transducer

6) Lift on an aircraft climbing vertically up is a) equal to its weight b) zero


c) equal to the drag d) equal to the thrust

7) For an airplane to be statically stable, its centre of gravity must always be a) ahead of wing aerodynamic centre b) aft of the wing aerodynamic centre c) ahead of neutral point d) aft of neutral point

8) During the ground roll manoeuvre of an aircraft, the force(s) acting on it parallel to the direction of motion a) is thrust alone. b) is drag alone. c) are both thrust and drag. d) are thrust, drag and a part of both weight and lift.

9) Which one of the following is the most stable configuration of an airplane in roll?

a) Sweep back, anhedral and low wing b) Sweep forward, dihedral and low wing c) Sweep forward, anhedral and high wing d) Sweep back, dihedral and high wing

10) A supersonic airplane is expected to fly at both subsonic and supersonic speeds during its whole flight

course. Which one of the following statements is TRUE? a) Airplane will experience less stability in pitch at supersonic speeds than at subsonic speeds b) Airplane will feel no change in pitch stability c) Airplane will experience more stability in pitch at supersonic speeds than at subsonic speeds d) Pitch stability cannot be inferred from the information given

11) Which one of the following is favorable for an airplane operation?

a) Tail wind in cruise and head wind in landing b) Tail wind both in cruise and landing c) Head wind both in cruise and landing d) Head wind in cruise and tail wind in landing

12) Which one of the following is TRUE with respect to Phugoid mode of an aircraft?

a) Frequency is directly proportional to flight speed b) Frequency is inversely proportional to flight speed c) Frequency is directly proportional to the square root of flight speed d) Frequency is inversely proportional to the square root of flight speed

13) Which one of the following criteria leads to maximum turn rate and minimum radius in a level turn flight?

a) Highest possible load factor and highest possible velocity b) Lowest possible load factor and lowest possible velocity c) Highest possible load factor and lowest possible velocity


d) Lowest possible load factor and highest possible velocity

14) An aircraft in trimmed condition has zero pitching moment at a) its aerodynamic centre. b) its centre of gravity. c) 25% of its mean aerodynamic chord. d) 50% of its wing root chord

15) In an aircraft, constant roll rate can be produced using ailerons by applying

a) a step input. b) a ramp input. c) a sinusoidal input. d) an impulse input.

16) Bernoulli’s equation is valid under steady state

a) only along a streamline in inviscid flow, and between any two points in potential flow. b) between any two points in both inviscid flow and potential flow. c) between any two points in inviscid flow, and only along a streamline in potential flow. d) only along a streamline in both inviscid flow and potential flow.

17) Thin airfoil theory predicts that the lift slope is CL = 2πα for

a) Symmetric airfoils only b) Cambered airfoils only c) Joukowski airfoils only d) Any airfoil shape

18) A student can measure free stream velocity of a low speed wind tunnel using a,

(i) Pitot tube alone aligned with the flow direction. (ii) Pitot tube aligned with the flow direction with static pressure measurement at an appropriate

position on the tunnel wall. (iii) Pitot tube aligned with the flow direction along with barometer pressure reading of the outside

ambient. (iv) Pitot static tube alone aligned with the flow direction.

Considering the above statements, which of the following options is correct? a) (i) only b) (i) & (ii) c) (ii) & (iv) d) (i), (iii) & (iv)

19) An ideal fluid is a

a) One which obeys Newton’s law of viscosity. b) Frictionless and incompressible. c) Very viscous. d) Frictionless and compressible


20) The Joukowski airfoil is studied in aerodynamics because

a) It is used in many aircrafts. b) It is easily transformed into circle mathematically c) It has simple geometry d) It has the highest lift curve slope among all airfoils

21) A turbulent boundary layer remains attached over a longer distance on the upper surface of an airfoil than

does a laminar boundary layer, because a) The turbulent boundary layer is more energetic and hence can overcome the adverse pressure gradient

better b) The laminar boundary layer develops more skin friction and hence slows down more rapidly c) Turbulence causes the effective coefficient of viscosity to reduce, resulting in less loss of momentum in

the boundary layer d) The turbulent boundary layer is thicker, hence the velocity gradients in it are smaller, therefore viscous

losses are less.

22) Which one of the following statements is NOT TRUE for a supersonic flow? a) Over a gradual expansion, entropy remains constant b) Over a sharp expansion corner, entropy can increase c) Over a gradual compression, entropy can remain constant d) Over a sharp compression corner, entropy increases

23) The Critical Mach number of an airfoil is attained when

a) the freestream Mach number is sonic. b) the freestream Mach number is supersonic. c) the Mach number somewhere on the airfoil is unity. d) the Mach number everywhere on the airfoil is supersonic

24) With increase in airfoil thickness, the critical Mach number for an airfoil is likely to

a) decrease. b) increase. c) remain unchanged. d) be undefined

25) Which of the following statement is NOT TRUE across an oblique shock wave?

a) Static temperature increases, total temperature remains constant. b) Static pressure increases, static temperature increases. c) Static temperature increases, total pressure decreases. d) Static pressure increases, total temperature decreases

26) For a completely subsonic isentropic flow through a convergent nozzle, which of the following statement is

TRUE?


a) Pressure at the nozzle exit > back pressure. b) Pressure at the nozzle exit < back pressure. c) Pressure at the nozzle exit = back pressure. d) Pressure at the nozzle exit = total pressure.

27) In a closed-circuit supersonic wind tunnel, the convergent-divergent (C-D) nozzle and test section are

followed by a C-D diffuser to swallow the starting shock. Here, we should have the a) diffuser throat larger than the nozzle throat and the shock located just at the diffuser throat. b) diffuser throat larger than the nozzle throat and the shock located downstream of the diffuser throat. c) diffuser throat of the same size as the nozzle throat and the shock located just at the diffuser throat. d) diffuser throat of the same size as the nozzle throat and the shock located downstream of the diffuser

throat.

28) An impulsive launch of a rocket minimizes the loss of burn-out velocity due to a) aerodynamic drag force only b) gravitational force only c) both aerodynamic drag and gravitational forces d) reaction jet control force

29) Combustion in gas turbine engines is ideally represented as the following process:

a) Adiabatic b) Isentropic c) Isobaric d) Isochoric

30) The pressure ratio in any one stage of a jet engine compressor is limited by

a) Entry stagnation temperature in that stage b) entry Mach number in that stage c) Pressure gradient induced separation in that stage d) mass flow rate in that stage

31) Thermodynamic cycle on which the jet engine operates can be

a) open Rankine cycle only b) either open or closed Rankine cycle c) open Brayton cycle only d) either open or closed Brayton cycle

32) Propulsion efficiency of a jet engine is

a) directly proportional to both the thrust power and the air mass flow rate b) inversely proportional to both the thrust power and the air mass flow rate c) directly proportional to the thrust power and inversely proportional to the air mass flow rate d) inversely proportional to the thrust power and directly proportional to the air mass flow rate


33) Match the appropriate engine (in right column) with the corresponding aircraft (in left column) for most efficient performance of the engine. a. Low speed transport aircraft i. Ramjet b. High subsonic civilian aircraft ii. Turboprop c. Supersonic fighter aircraft iii. Turbojet d. Hypersonic aircraft iv. Turbofan

a) a – iv, b – iii, c – i, d – ii b) a – ii, b – i, c – iii, d – iv c) a – i, b – ii, c – iv, d – iii d) a – ii, b – iv, c – iii, d – i

34) For a given chamber pressure, the thrust of a rocket engine is highest when

a) the rocket is operating at its design altitude. b) the rocket is operating in vacuum. c) the rocket is operating at sea-level. d) there is a normal shock in the rocket nozzle.

35) The Poisson’s ratio, ν of most aircraft grade metallic alloys has values in the range:

a) −1 ≤ν ≤0 b) 0 ≤ν ≤0.2 c) 0.2 ≤ν ≤0.4 d) 0.4 ≤ν ≤0.5

36) In a semi-monocoque construction of an aircraft wing, the skin and spar webs are the primary carriers of

a) shear stresses due to an aerodynamic moment component alone. b) normal (bending) stresses due to aerodynamic forces. c) shear stresses due to aerodynamic forces alone. d) shear stresses due to aerodynamic forces and a moment component

37) Buckling of the fuselage skin can be delayed by

a) increasing internal pressure. b) placing stiffeners farther apart. c) reducing skin thickness. d) placing stiffeners farther and decreasing internal pressure

38) An Euler-Bernoulli beam in bending is assumed to satisfy

a) both plane stress as well as plane strain conditions b) plane strain condition but not plane stress condition c) plane stress condition but not plane strain condition d) neither plane strain condition nor plane stress condition

39) A statically indeterminate frame structure has

a) same number of joint degrees of freedom as the number of equilibrium equations


b) number of joint degrees of freedom greater than the number of equilibrium equations c) number of joint degrees of freedom less than the number of equilibrium equations d) All of the above

40) A material can return to normal after it has been deformed due to its elasticity.

a) True b) False c) Cannot determine d) Partially correct

41) Which of the following instruments are works on the basis of pitot-static system?

a) air speed indicator b) altimeter c) vertical speed indicator d) Dturn and slip indicator

42) Poisson's ratio is defined as the ratio of

a) longitudinal stress and longitudinal strain b) longitudinal stress and lateral stress c) lateral stress and longitudinal stress d) lateral stress and lateral strain

43) Hooke's law holds good up to

a) Yield point b) limit of proportionality c) breaking point d) elastic limit

44) The maximum strain energy that can be stored in a body is known as

a) impact energy b) Resilience c) proof resilience d) modulus of resilience

45) Which of the following statement is NOT TRUE across an oblique shock wave?

a) Static temperature increases, total temperature remains constant. b) Static pressure increases, static temperature increases. c) Static temperature increases, total pressure decreases. d) Static pressure increases, total temperature decreases.

46) The aerodynamic centre of a supersonic aerofoil, with chord c, is located at

a) The leading edge b) 0.25c c) 0.5c d) 0.75c

47) Concept of aerodynamic centre is

a) Point at which moment independent of angle of attack


b) Point at which net moment is zero c) Point at which net force acts d) Point at which net forces are zero

48) The drag divergence mach number of an airfoil.

a) is a fixed number for a given airfoil b) is always higher than Mcr c) is equal to Mcr at zero angle of attack d) is the Mach number at which a shock wave first appears on the airfoil.

49) An aircraft in trimmed condition has zero pitching moment at

a) Its aerodynamic centre. b) Its centre of gravity. c) 25% of its mean aerodynamic chord. d) 50% of its wing root chord

50) Which of the following statements are correct as per drag polar?

1) Take off of a subsonic aircraft is mostly affected by lift dependent drag. 2) While cruising a supersonic aircraft is mostly affected by wave drag. a) Only 1 is correct b) Only 2 is correct c) Both 1 &2 are correct d) Both 1 & 2 are wrong

Syllabus

Module 1

AERODYNAMICS: Conservation laws of mass, momentum and energy – Elementary flows and their combinations - Thin airfoil theory - Lifting line theory – Boundary layer thicknesses – Compression waves and Expansion waves - Critical Mach number, Drag Divergence Mach number, Shock Stall, Supercritical Airfoil Sections, Transonic area rule – Shock expansion theory – Aerodynamic heating. Module 2

AIRCRAFT STRUCTURES: Plane truss analysis – Strain energy - Energy theorems - Ductile and brittle materials – Theories of failure - Thermal stresses – Creep & Fatigue - Bending of symmetric and unsymmetric beams - Thin walled beams - Bredt - Batho theory - Bending of thin plates – Loads on an aircraft - Bending moment distribution over the aircraft - Complete tension field beam, Semi-tension field beam theory. Module 3

AIRCRAFT PROPULSION SYSTEMS: Piston engines – Gas turbine engines – Thrust augmentation – Inlets and Nozzles - Compressors and turbines – Ram jet engine – Thrust vector control - Cryogenic engines - Air augmented rockets - Pulse rocket motors - Solid and liquid propellant rockets - Hybrid rocket propulsion - Electric propulsion - Nuclear rocket propulsion - Solar sail.


Module 4

FLIGHT MECHANICS: Measurement of speed - Streamlined and bluff bodies- Forces acting on aircraft – types of Drag -Straight and level flight - Gliding and Climbing flight- Range and Endurance - Lift, drag and L/D ratio devices - Take-off and Landing performance, Turning performance - V-n diagram - Static and dynamic stability - Aerodynamic balancing - Aircraft equations of motion- Stability derivatives. Module 5

AVIONICS SYSTEMS AND INSTRUMENTS: Avionics subsystems - Aircraft cockpit displays – Communication and Navigation systems - Pitot-Static instruments and Gyroscopic instruments – Fly by Wire and Fibre Optic control systems. Text and Reference Books:

1. Anderson, J.D., "Fundamentals of Aerodynamics", McGraw Hill Book Co., 1999

2. Anderson, J. D, "Modern Compressible Flow", McGraw-Hill & Co., 2002

3. Timoshenko and Gere, "Mechanics of Materials", Tata McGraw Hill, 1993.

4. Megson T M G, "Aircraft Structures for Engineering students" Elsevier , 2007

5. Hill, P.G. & Peterson, C.R. “Mechanics & Thermodynamics of Propulsion” Addison – Wesley Longman

INC, 1999.

6. Sutton, G.P., “Rocket Propulsion Elements”, John Wiley & Sons Inc., New York, 5th Edition, 1993.

7. Perkins C.D., &Hage, R.E. Airplane performance, stability and control, Wiley Toppan, 1974

8. Collinson.R.P.G. "Introduction to Avionics", Chapman and Hall, 1996.

9. Mekinley, J.L. and Bent, R.D., “Aircraft Power Plants”, McGraw-Hill, 1993.


AOL332 AIRFRAME PRODUCTION AND MAINTENANCE LAB

CATEGORY L T P CREDIT PCC 0 0 3 2

Preamble: Aim of this course is to provide a hands-on training in airframe maintenance and repair such as welding, riveting, composite preparation, carpentry work, patchwork, sheet metal works and lathe works. Prerequisite: Aircraft General Engineering and Maintenance Practices. Course Outcomes: After the completion of the course the student will be able to

CO 1 Understand the basic concepts of carpentry works CO 2 Understand the principle and working procedure of different welding setup CO 3 Understand the manufacturing method of composite laminates CO 4 Understand the repairing procedure of aircraft fabric and rivets CO 5 Understand the bending and flaring procedure of aircraft tubes CO 6 Understand the forming procedure of aircraft sheet metals CO 7 Understand the splicing and swaging procedure of aircraft cables CO 8 Understand the basic concepts of lathe work. Mapping of course outcomes with program outcomes

PO 1


PO 11

PO 12

CO 1 3 3 2 1 CO 2 3 3 2 1 CO 3 3 3 2 1 CO 4 3 3 2 1 CO 5 3 3 2 1 CO 6 3 3 2 1 CO 7 3 3 2 1 CO 8 3 3 2 1 Assessment Pattern

Mark distribution

Total Marks CIE ESE ESE Duration 150 75 75 2.5 hours Continuous Internal Evaluation Pattern: Attendance : 15 marks Continuous Assessment Test (2 numbers) : 30 marks Assignment/Quiz/Course project : 30 marks End Semester Examination Pattern: The following guidelines should be followed regarding award of marks (a) Preliminary work : 15 Marks (b) Implementing the work/Conducting the experiment : 10 Marks (c) Performance, result and inference (usage of equipment’s and troubleshooting) : 25 Marks (d) Viva : 20 Marks


(e) Record : 5 Marks General instructions: Practical examination to be conducted immediately after the second series test covering entire syllabus given below. Evaluation is a serious process that is to be conducted under the equal responsibility of both the internal and external examiners. The number of candidates evaluated per day should not exceed 20. Students shall be allowed for the University examination only on submitting the duly certified record. The external examiner shall endorse the record. Course Level Assessment Questions


1. Make a single scarf joint in wood by gluing method.

2. Make a double scarf joint in wood by gluing method.


1. Patch repair by using TIG welding.

2. Patch repair by using MIG welding.

3. Patch repair by using PLASMA welding.

4. Make a single & double V joints by arc welding.


1. Prepare the glass epoxy composite laminate.

2. Determine the elastic constants of given composite laminates.


1. Patch repair in fabric sheet material.

2. Make a riveted joint in aluminium sheet.


1. Make a simple bend in given aluminium tube.

2. Make a single and double flare in given aluminium tube.


1. Make a simple bend in given aluminium sheet metal.


1. Join the two cable ends by using splicing method.

2. Make an aircraft cable swage.



1. Make the part shown in the sketch from a mild steel rod on a Lathe.

2. Make a hexagonal head and the slot shown in the sketch on the specimen.

LIST OF EXPERIMENTS

1. Aircraft wood gluing - single scarf joint

2. Aircraft wood gluing - double scarf joint

3. Welded single & double V-joints

4. TIG welding practice of basic joints

5. MIG welding practice of basic joints

6. PLASMA welding practice of basic joints

7. Preparation of glass epoxy of composite laminates and specimens

8. Determination of elastic constants of composite specimens

9. Fabric Patch repair

10. Riveted patch repair

11. Tube bending and flaring

12. Sheet metal forming

13. Cable splicing & swaging

14. Plain Turning operation on Lathe

15. Plain Milling Exercise



Reference Books:

1. Kroes, Watkins, Delp “Aircraft Maintenance & Repair”, Mc Graw Hill, New York 1993. 2. “Airframe & Powerplant Mechanics” – Airframe Hand Book, FAA Handbook. 3. “Aviation Maintenance Technician Hand Book” – Airframe Vol -I and II, FAA Handbook.

AOD334 MINI PROJECT CATEGORY L T P CREDIT Year of Introduction PWS 0 0 3 2 2019

Preamble:This course strengthen the understanding of student’s fundamentals through effective application of theoretical concepts.

Prerequisite: Nil

Course Outcomes:After the completion of the course the student will be able to

CO 1 To develop skills in doing literature survey. CO 2 To develop technical presentation and report preparation skills. CO 3 To apply engineering knowledge in practical problem solving CO 4 To foster innovation in design of products, processes or systems CO 5 To develop creative thinking in finding viable solutions to engineering problems


PO 1

PO 2

PO 3

PO 4

PO 5

PO 6

PO 7

PO 8

PO 9

PO 10

PO 11

PO 12

CO 1 3 2 1 1 CO 2 3 3 1 1 1 CO 3 3 3 1 1 1 CO 4 3 3 1 1 1 CO 5 3 3 1 1 1

Assessment Pattern

Bloom’s Category Continuous Assessment Test

End Semester Examination

Remember 5 5 Understand 20 20 Apply 50 50 Analyse Evaluate Create

Mark distribution

Total Marks

CIE ESE ESE Duration

150 75 75 3 hours



Attendance : 10 marks Guide : 15 marks Project report : 10 marks Evaluation by committee : 40 marks End Semester Examination Pattern:The progress of the mini project is evaluated based on a minimum of two reviews. The review committee may be constituted by the Head of the Department. A project report is required at the end of the semester. The product has to be demonstrated for its full design specifications. Innovative design concepts, reliability considerations, aesthetics/ergonomic aspects taken care of in the project shall be given due weight. The internal evaluation will be made based on the product, the report and a viva-voce examination, conducted by a 3 member committee appointed by Head of the Department comprising HoD or a senior faculty member, Academic coordinator for that program, project guide/coordinator.



SEMESTER VI PROGRAM ELECTIVE I


AOT312 ELASTIC ANALYSIS OF PLATES AND SHELLS

CATEGORY L T P CREDIT PEC 2 1 0 3

Preamble: To understand the basic concept, mathematical modeling, behavior and analysis of plate and shellstructures.

Prerequisite: AIRCRAFT STRUCTURES II


CO1 Apply differential equations for the calculation of response of two-dimensional problems.

CO2 Understand the behavior of plates and analytical techniques

CO3 Construct the mathematical models of structural systems. CO4 Solve the two-dimensional structural engineering problems CO5 Understand the bending theories of cylindrical shells with and without edge beams


PO1 PO2 PO3 PO4 PO5 PO6 PO7 PO8 PO9 PO10 PO11 P12 CO1 3 2 - CO2 3 2 CO3 3 2 CO4 3 2 CO5 3 2

Assessment Pattern



Mark distribution






Assignment/Quiz/Course project : 15marks

End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14marks. Course Level Assessment Questions


1. Derive the differential equation governing the plate. Sate various assumptions involved 2. a) Obtain the expression for deflection in case of uniformly loaded rectangular plates with

clamped edges. b) What are the merits and demerits of plates? Course Outcome 2 (CO2)

1. Derive the governing differential equation of Bending of long thin rectangular plate to a cylindrical surface

2. Explain Kirchhoff plate theory

Course Outcome 3(CO3): 1. Obtain the expression for deflection in case of uniformly loaded circular plates with clamped edges. 2. a) Using the Navier solution obtain general equation for a rectangular plate subjected to

hydrostatic pressure b) Obtain the modified equation in case of a plate subjected to in plane forces.


1. Briefly describe the structural behavior of thin shell. 2. Explain

a) Annular Plates b) Levy’s Solution of Plates c) Analysis of Conical Shells

Course Outcome 5 (CO5): 1. a) How do you classify shells into long and short shells as per various theories

b) Write boundary conditions for simply supported cylindrical shells with the edge conditions.

i) Single shell without edge beam


ii) single shell with edge beam

2. Explain the general theory of cylindrical shell loaded symmetrically with respect to its axis.

Model Question Paper QP CODE: Reg No .:_______________

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY SIXTH SEMESTER B. TECH DEGREE EXAMINATION, MONTH

& YEAR

Course Code: AOT312

ELASTIC ANALYSIS OF PLATES AND SHELLS


PART A



1. Define flexural rigidity of the plate.

2. What is average curvature of the surface at a point

3. Define synclastic.

4. Define anticlastic.

5. What issurface traction?

6. Write the Levy’s equation.

7. What is membrane theory?

8. Write the hypergeometrical series.

9. Explain the difference between homogeneous and nonhomogeneous boundary conditions.

10. What is hyperbolic paraboloid of revolution?

PART B



Module -1

11. Derive the differential equation governing the plate. Sate various assumptions involved (14)


(or)

12. a) Obtain the expression for deflection in case of uniformly loaded rectangular plates with clamped

edges. (14)

b) What are the merits and demerits of plates?

Module -2

13. Derive the governing differential equation of Bending of long thin rectangular plate to a cylindrical

surface (14)

(or)

14. Explain Kirchhoff plate theory (14)

Module -3 15. a) Using the Navier solution obtain general equation for a rectangular plate subjected to

hydrostatic pressure

(7)

b) Obtain the modified equation in case of a plate subjected to in plane forces. (7)

(or)

16. Derive expressions for deflection, shear force and bending moment for a circular plate with simply supported boundary conditions subjected to uniformly distributed loading (14)

Module -4

17. a) How do you classify shells into long and short shells as per various theories (6)

b) A simply supported circular cylindrical shell with free longitudinal edges is spanning 22m and

radius of 10m and semicircular angle of 35 degrees. The edge beam has width of 300mm and

depth of 1500mm. Determine stress resultants for NX N0 Nx0 under self-weight using membrane

theory. If there is an edge beam what is the maximum longitudinal force developed in the edge

beam. (8)

(or)

18. a) How do you classify shells into long and short shells as per various theories (7) b) Write boundary conditions for simply supported cylindrical shells with the edge conditions or the end shells in a multiple group of shells. (7)

Module -5

19. a) Derive Shorer’s differential equation (7)

b) Give solutions to Shorer’s differential equations (7)


(or)

20. Design a cylindrical shell roof considering beam and arch action to cover a parking place 40 meters

wide and 160 meters long. Superimposed load due to waterproofing cover and occasional live

loads may be taken as 350 kg/m2 of the surface of the shell. Slope at the ends may be taken as 40.

Thickness of the shell may be taken as 110mm.Dimensions of the edge beam may be assumed as

300mm by 1500 mm. Shell may be divided into four parts for arch action. Use M20 and Fe250

steel. Show the design details clearly.

(14)


SYLLABUS

MODULE 1

Governing differential equations of thin rectangular Plates with various boundary conditions (Fixed, clamped, simply supported…etc.) and loadings (Distributed loads, shear loads, pressure loads...etc.).

MODULE 2

Bending of long thin rectangular plate to a cylindrical surface, Kirchhoff plate theory, Introduction to orthotropic plates. Plate with hole.

MODULE 3

Circular plates with various boundary conditions (Fixed, clamped, simply supported…etc.)and loadings(Distributed loads, shear loads, pressure loads...etc.). Numerical methods for solution of plates, Navier's, Levy’s solutions.

MODULE 4

General shell geometry, classifications, stress resultants, equilibrium equation, Membrane theory for family of Shells (Parabolic, Catenary, Cycloid, Circular, hyperbolic).

MODULE 5

Classical bending theories of cylindrical shells with and without edge beams such asapproximate analysis ofcylindrical shells. Shorer’s differential equation for cylindrical shell

Texts and References:

1. Timoshenko, S., &Woinowsky-Krieger, S. (1959). Theory of plates and shells (Vol. 2, p. 120).

New York: McGraw-hill.

2. Szilard, R. (1974). Theory and analysis of plates.

3. Novozhilov, V. V. (1959). The theory of thin shells. P. Noordhoff.

4. Ramaswamy, G. S. (1968). Design and construction of concrete shell roofs. McGraw-Hill.

5. Chandrashekhara, K. (2001). Theory of plates. Universities press.


Course Contents and Lecture Schedule No Topic No. of Lectures 1 Module 1

1.1 Governing differential equations of thin rectangular Plates with various boundary conditions (Fixed, clamped, simply supported…etc.)

4

1.2 Loadings (Distributed loads, shear loads, pressure loads...etc.). 2 2 Module 2

2.1 Bending of long thin rectangular plate to a cylindrical surface 3 2.2 Kirchhoff plate theory 2 2.3 Introduction to orthotropic plates 2 2.4 Plate with hole 1 3 Module 3

3.1 Circular plates with various boundary conditions (Fixed, clamped, simply supported…etc.) 2

3.2 Loadings (Distributed loads, shear loads, pressure loads...etc.) 2 3.3 Numerical methods for solution of plates 1 3.4 Navier's solution 1 3.5 Levy’s solutions 1 4 Module 4

4.1 General shell geometry 2

4.2 Classifications , stress resultants 2 4.3 Equilibrium equation 1 4.4 Membrane theory for family of Shells (Parabolic, Catenary, Cycloid, Circular,

hyperbolic) 2

5 Module 5 5.1 Classical bending theories of cylindrical shells with and without edge beams 2 5.2 Approximate analysis of cylindrical shells 3 5.3 Shorer’s differential equation for cylindrical shell 2


AOT322 SPACE SCIENCE AND SPACE ENVIRONMENT CATEGORY L T P CREDIT PEC 2 1 0 3

Preamble: The course is meant to give the learners an introduction to space science and space environments. Course Outcomes: After the completion of the course the student will be able to CO 1 Understand the basic physics of plasma. CO 2 Basics of Magneto hydrodynamics and Einstein field equations. CO 3 Explain Sun’s interior structure, physics of solar wind. CO 4 Understand the different layers of space environment. CO 5 Analyse the consequences of magnetic reconnection for Earth's magnetosphere. Mapping of course outcomes with program outcomes PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO 10 PO 11 PO 12 CO 1 3 CO 2 3 CO 3 3 2 CO 4 3 2 2 CO 5 3 Assessment Pattern Bloom’s Category Continuous Assessment Tests End Semester Examination

1 2 Remember 20 20 20 Understand 20 20 30 Apply 10 10 50 Analyse Evaluate Create Mark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks.




1. State the importance of the magnetic field in space.

2. Discuss the Stochastic processes in plasma in detail.

3. Understand the concept of Adiabatic invariants.


1. Define terms like magnetic pressure, diamagnetic drift, phase velocity etc.

2. Discuss Maxwell’s equations, Ohm’s law and Einstein field equation.

3. General dispersion relation.


1. Understand the solar properties and process happening in the solar core.

2. Discuss Transport of energy from core.

3. Explain elementary theories related to dynamo.


1. Explain in detail about earth’s magnetic field.

2. Discuss earth’s atmosphere and its thermal structure.

3. Understand the concepts of diffusion.


1. Explain the Interaction of the solar wind with the terrestrial magnetic field.

2. Define high-latitude electrodynamics and convection electric field.

3. Explain the importance and applications of space weather.



QP CODE: Reg No: --------------------------

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY B.TECH DEGREE EXAMINATION

MONTH & YEAR

Course Code: AOT322

SPACE SCIENCE AND SPACE ENVIRONMENT


PART A



1. Why is space dominated by plasmas?

2. Explain the role of magnetic field in space.

3. What is magnetic pressure?

4. Define the term Debye shielding.

5. What is Solar wind?

6. Define Lorentz force.

7. What is the difference between Geographic and Geomagnetic coordinates?

8. Define Solar radiation.

9. Define Magnetic diffusion and Magnetic connection.

10. What is the importance of Space weather?

PART B



Module 1

11. Briefly explain phase-space distribution function. (14)

12. a) Write a short note on Uniform and Non-uniform magnetic fields, (6)

b)Explain about Adiabatic invariants. (8)


Module 2 13. a) Explain Einstein field equation and compare with Newtonian gravitation. (10)

b) Define phase velocity and group velocity. (4)

14. Explain Maxwell’s equations in vacuum for the electromagnetic fields. (14)

Module 3

15. 15. Briefly explain the structure of Solar interior with suitable diagrams. (14)

16. a) Explain the solar dynamo mechanism using schematics. (9)

b) What is Sunspot Number and Solar Cycle? (5)

Module 4

17. a) In detail diagrammatically explain Earth’s standard atmosphere. (8)

b) Derive the barometric altitude formula and list down the assumptions. (6)

18. a) Write short notes on,

i. Molecular Diffusion.

ii. Eddy Diffusion.

iii. Diffusive equilibrium.

iv. Ionization profile. (8)

b) Explain the composition profile of Stratosphere and Mesosphere. (6)

Module 5

19. a) Schematically explain the interaction of solar wind with the bow shock and magnetopause. (8)

b) Write a short note on Magnetospheric current systems. (6)

20. a) Briefly explain the Axford-Hines and the Dungey models of plasma convection. (8)

b) Explain Geomagnetic activity indices. (6)


Syllabus

Module 1

Introduction to plasma, gaseous plasma, Quasi-neutrality, Collisions of charged particles, Plasma oscillations, Non-classical plasmas. Dynamics of a charged particle: The key role of the magnetic field, Basic charge motion in constant and uniform fields, Non-uniform magnetic field, Adiabatic invariants. Stochastic processes in a plasma: The velocity distributions, moments of distribution functions, collisions and transport, electrical conductivity, diffusion, motion in magnetic fields in the presence of collisions. Module 2

Introduction to magneto hydrodynamics (MHD), magnetic pressure, diamagnetic drift, The generalized ohm’s law. Einstein field equation-Einstein tensor-comparison with Newtonian gravitation. Maxwell’s equations and the wave equation: basic concepts, phase velocity, wave packet and group velocity, Refractive index, The general dispersion relation, Debye shielding. Module 3

Basic solar properties, Source of sun’s energy, Nuclear reactions in the solar core, Black body radiation and the solar spectrum, The solar disc and Sunspots, magnetic fields, Solar wind, Solar rotation and the solar cycle chromosphere and corona. Transport of energy from core, Convective energy transfer. Elements of dynamo theory and Solar kinematic dynamos, Concentrating and expelling the magnetic field, Lorentz force restriction on dynamo action, Basic physics of magnetic flux tubes. Module 4

Introduction to earth’s atmosphere, elements of earth’s magnetic field, difference between geographic and geomagnetic coordinates,barometric altitude formula. The terrestrial upper atmosphere: Diffusion, molecular diffusion, eddy diffusion, diffusive equilibrium, maximum diffusion velocities, thermal structure, thermosphere, the exosphere. The Ionosphere; solar radiation and production of ionization, Ionization profile, Ion composition and chemistry. Module 5

Interaction of the solar wind with the terrestrial magnetic field, the bow shock and the magnetopause, The magnetospheric cavity, magnetospheric current systems, The ring current, field-aligned currents, Plasma convection in the magnetosphere-models, Magnetic diffusion and magnetic reconnection, Convection electric field and high-latitude electrodynamics, Ionospheric convection velocities, aurorae, space weather, magnetic activity and substorms, magnetic storms, geomagnetic activity indices, importance and applications of space weather. Text Books


1. Gombosi, T. I., “Physics of the Space Environment”, Cambridge University Press, 1998.

2. Ioannis A. Daglis and Volker Bothmer, “Space Weather: Physics and Effects”, Springer, 2007.

Reference Books

1. Kellenrode, M-B, Space Physics, An Introduction to Plasmas and Particles in the Heliosphere and Magnetospheres, Springer, 2000.

2. James R. Wertz, David F. Everett, Jeffery J. Puschell, “Space Mission Engineering: The New SMAD”, Microcosm Press, 2015.

3. Delores J. Knipp, “Understanding Space Weather and the Physics Behind It”, McGraw Hill, 2004.


No

Modules No. of

Lectures 1 Module: 1

1.1 Introduction to plasma, gaseous plasma, Quasi-neutrality, Collisions of charged particles, Plasma oscillations, Non-classical plasmas.

2

1.2

Dynamics of a charged particle: The key role of the magnetic field, Basic charge motion in constant and uniform fields, Non-uniform magnetic field.

3

1.3

Adiabatic invariants, Stochastic processes in a plasma: The velocity distributions, moments of distribution functions, collisions and transport of electrical conductivity, diffusion etc.

2

2 Module: 2

2.1 Introduction to magnetohydrodynamics (MHD), magnetic pressure, diamagnetic drift, The generalized ohms law, phase velocity and group velocity.

2

2.2

Einstein field equation-Einstein tensor-comparison with Newtonian gravitation Maxwell’s equations and the wave equation: basic concepts.

2

2.3 The general dispersion relation, Debye shielding. 3 3 Module: 3

3.1 Basic solar properties, Source of sun’s energy, Nuclear reactions in the solar core, Black body radiation and the solar spectrum.

2

3.2

The solar disc and Sunspots, magnetic fields, Solar wind, Solar rotation and the solar cycle chromosphere and corona. Transport of energy from core, convective energy transfer.

2

3.3

Elements of dynamo theory & Solar kinematic dynamos, Concentrating and expelling the magnetic field.

2

3.4 Lorentz force restriction on dynamo action, basics of magnetic flux tubes. 1

4 Module: 4

4.1 Introduction to Earth’s magnetic Field, Elements of earth’s magnetic field, Difference between geographic and geomagnetic coordinates.

2

4.2

The Terrestrial Upper Atmosphere: Diffusion, Molecular diffusion, Eddy diffusion, Diffusive equilibrium, Maximum diffusion velocities,

2

4.3

Thermal Structure, thermosphere, the exosphere. The Ionosphere; solar radiation and production of ionization, Ionization profile and chemistry.

3


5 Module: 5

5.1 Interaction of the solar wind with the terrestrial magnetic field, the bow shock and the magnetopause, The magnetospheric cavity, magnetospheric current systems, the ring current, field-aligned currents,

3

5.2 Plasma convection in the magnetosphere, Magnetic diffusion & magnetic reconnection, Convection electric field and high-latitude electrodynamics, 2

5.3 Ionospheric convection velocities, aurorae, space weather, magnetic activity and substorms, magnetic storms, geomagnetic activity indices, importance and applications of space weather.

4


AOT332 NUMERICAL PROGRAMMING CATEGORY L T P CREDIT

PEC 2 1 0 3

Preamble: The course is meant to give the learners an introduction to advanced mathematics as well as basic computer programing.

Prerequisite: Nil

Course Outcomes:After the completion of the course the student will be able to CO 1 Explain the fundamental concepts of vector spaces and problem discretization methods. CO 2 Solve ODE boundary value problems and pde’s using various methods. CO 3 Solve system of linear algebraic equations. CO 4 Form system of nonlinear algebraic equations and there solutions. CO 5 Solve ODE initial value problems using various methods and system ODE’s.

Mapping of course outcomes with program outcomes PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO

10 PO 11

PO 12

CO 1 3 2 1 1 CO 2 3 3 1 1 1 CO 3 3 3 1 1 1 CO 4 3 3 1 1 1 CO 5 3 3 1 1 1



Mark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours

Continuous Internal Evaluation Pattern: Attendance : 10 marks


Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks

End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks.



1. Given vector x = 0:0.1:10; Write program scripts to plot sin(x) * cos(x) in two ways:(i) Plot them using a single plot command;(ii) Plot sin(x) first, and then plot cos(x) without erasing the previous figure.Sine should be plotted as solid blue line, and cos as dashed red line and Sine *cos as green line.

2. Explain if and for statements in Matlab3. The sequence Xn of numbers is defined by the recurrence relation

𝑿𝑿𝒏𝒏 = 𝑿𝑿𝒏𝒏−𝟏𝟏 − 𝑿𝑿𝒏𝒏−𝟐𝟐 + 𝑿𝑿𝒏𝒏−𝟑𝟑

with seed values 𝑿𝑿𝟏𝟏 = 𝟑𝟑,𝑿𝑿𝟐𝟐 = 𝟏𝟏𝟏𝟏,𝑿𝑿𝟑𝟑 = 𝟏𝟏𝟏𝟏

Write a matlab programme to show the numbers less than 750 using user defined function. Use following data for defining user function: Function name: New_Sequence Input: 750 Output: Terms


1. Write a well-commented MATLAB function program mypm.m that inputs a matrix and a tolerance,applies the power method until the scalar residual is less than the tolerance, and outputs theestimated eigenvalue and eigenvector, the number of steps, and the scalar residual.

2. Write your own code to perform LU decomposition. Given the following set of equations:

10𝑥𝑥1 + 2𝑥𝑥2 − 𝑥𝑥3 = 64 3𝑥𝑥1 − 5𝑥𝑥2 + 2𝑥𝑥3 = 74 −𝑥𝑥1 + 𝑥𝑥2 + 6𝑥𝑥3 = 21

3. Write generalised MATLAB program to implement QR method until it converges. Use the followingbuilt in command

[𝑄𝑄 𝑅𝑅] = 𝑞𝑞𝑎𝑎 (𝐴𝐴) Course Outcome 3 (CO3):

1. Use Simpson’s 1/3rd Rule to solve the following integral:


��log(𝑥𝑥3) 𝑑𝑑𝑥𝑥6

0

2. Consider the equation.

𝑥𝑥 = 𝐴𝐴 𝑐𝑐(−2𝑎𝑎+∅)

Write a MATLAB script to estimate the values of parameters A and .

t 0 1 2 3 4 5 6 7 8 9 10

x 5.2 8.3 9.9 7.1 1.2 4.1 8.2 9.4 6.3 0.8 5.0

Solve the problem using Matrix method.

3. Use the trapezoidal rule, with step-size of ℎ = 0.2 to obtain the following integral:

� 5𝑥𝑥 𝑐𝑐𝑙𝑙𝑙𝑙(𝑥𝑥) 𝑑𝑑𝑥𝑥10

6


1. Write a matlab program to solve the following ODE using RK-2 method:

𝑑𝑑𝑥𝑥𝑑𝑑𝑎𝑎

= 𝑥𝑥 𝑐𝑐𝑥𝑥 , 𝑐𝑐(0) = 0

2. Write the following 2nd order differential equation as a system of first order, linear differential

equations.

6𝑐𝑐′′ − 3𝑐𝑐′ + 9𝑐𝑐 = 0 𝑐𝑐(0) = 5, 𝑐𝑐′(0) = 7 3. Write a matlab program to solve the following ODE using RK-4 method:

𝑑𝑑𝑐𝑐𝑑𝑑𝑎𝑎

= 𝑐𝑐2sin(𝑐𝑐) , 𝑐𝑐(0) = 2


Explain relaxation method for nonlinear finite difference

1. Explain finite difference scheme for elliptical PDE’s2. Explain solution instability for explicit method’s


QP CODE: Reg No: --------------------------

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY SIXTH SEMESTER B.TECH DEGREE EXAMINATION

MONTH & YEAR

Course Code: AOT332

NUMERICAL PROGRAMMING



PART A



1. What are the condition statements in Matlab?

2. Write the matlab code for 2D plot.

3. Discuss the accuracy of newton’s method.

4. Define Eigen value and Eigen vectors?

5. Compare polynomial and spline interpolation.

6. Explain Gaussian Quadrature method.

7. Explain the degree of accuracy of Runge-kutta method.

8. Differentiate between linear and non-linear ODE.

9. What is finite difference method?

10. What are the insulated boundary conditions?

PART B



Module 1

11. a) Write a MATLAB code for solving nonlinear equation 𝒇𝒇(𝒙𝒙) = 𝟏𝟏 using Newton-Raphson method. The function and derivative are given below:

𝒇𝒇(𝒙𝒙) = 𝟒𝟒𝟏𝟏𝒙𝒙𝟏𝟏.𝟏𝟏 + 𝟖𝟖𝟖𝟖𝟏𝟏𝒙𝒙 + 𝟑𝟑𝟏𝟏𝟏𝟏𝟏𝟏𝟏𝟏

𝒇𝒇′(𝒙𝒙) = 𝟔𝟔𝟏𝟏𝒙𝒙𝟏𝟏.𝟏𝟏 + 𝟖𝟖𝟖𝟖𝟏𝟏

Also include scripts to calculate the relative approximation error in each steps:

𝜺𝜺(𝒊𝒊) = �𝒙𝒙(𝒊𝒊) − 𝒙𝒙(𝒊𝒊)

𝒙𝒙(𝒊𝒊) �

(7) c) One needs to calculate cube root of a number: = √𝒂𝒂𝟑𝟑 . Write a function myCubeRoot (a,

tol) that takes aas the input and returns solution x accurate to a desired tolerance oftolerance. The cube root is computed iteratively using the formula:

𝒙𝒙𝒏𝒏𝒏𝒏𝒏𝒏 =𝟏𝟏𝟐𝟐�𝒙𝒙 +

𝒂𝒂𝒙𝒙𝟐𝟐�

The initial guess for starting the code is 𝒙𝒙 = 𝒂𝒂𝟐𝟐 . (7)


12. Find errors in the following code fragments and rewrite it after underlining each correction.(14)

a) 𝑥𝑥 = 9,𝑐𝑐 = 5𝑧𝑧 = 𝑥𝑥 × 𝑐𝑐 display(z)

b) If err<tol

Stop; End

c) Plot(t,u)

xdisply (‘time’) ydisply (‘velocity’) title(Graph)

d) function (f) = factorial [n] % factorial (N) returns the factorial of n.

f = prod(1:n); % Compute a factorial value end

e) A=[1 3 5] ;

B=[5 7 2] ; % our aim is to make a 2 × 3 matrix C using A and B

C= [A, B]; (14)

Module 2

13. Consider a two-degree of freedom system shown below

a) Derive the equations of motion of the system. (Let assume displacements of masses 150kgand 50kg are x1 and x2 respectively. Write a matlab programme to find natural frequenciesand mode shapes.

(7)


b) Write matlab script to find displacements of masses between 0 to 10 seconds. You can usefollowing relations (Bold letters indicates matrices):

𝑿𝑿(𝑎𝑎) = 𝐶𝐶1𝑽𝑽𝟏𝟏cos(𝜔𝜔1𝑎𝑎) + 𝐶𝐶2𝑽𝑽𝟏𝟏sin(𝜔𝜔1𝑎𝑎) + 𝐶𝐶3𝑽𝑽𝟐𝟐cos(𝜔𝜔2𝑎𝑎)+𝐶𝐶3𝑽𝑽𝟐𝟐sin(𝜔𝜔2𝑎𝑎)

Initial displacement, (𝟏𝟏) = �10� , Initial velocity, �̇�𝑿(𝟏𝟏) = �21�

�𝐶𝐶1𝐶𝐶2� = 𝑽𝑽−1𝑿𝑿(𝟏𝟏), �𝐶𝐶3

𝐶𝐶4� = 𝑽𝑽−1�̇�𝑿(𝟏𝟏),

Where 𝑽𝑽is Eigen vectors (2×2 matrix) (7)

14. A company produces Transistors, Resistors, and Computer Chips, which are built usingmaterials C, Z and G. Each transistor requires 4 of material–C, 1 of material–Z and 2 ofmaterial-G. Likewise the number of materials of each type required in making transistors,resistors and chips is given in the following table:

C Z G Transistors 4 1 2 Resistors 3 3 1 Computer chips 2 1 3

If the total amount of materials used today are 960 units of C, 510 units of Z, and 610 units of G, find the number of transistors, resisters and computer chips manufactures in this production run. You will need to set up the system of equations for this production run, and write a matlab program to solve it using a method of your choice.

(14) Module 3

15. The following model can be used to predict the growth rate of bacteria per day:

µ =𝐾𝐾𝑚𝑚𝑎𝑎𝑥𝑥 𝐶𝐶2

𝐾𝐾𝑠𝑠 + 𝐶𝐶2

Where, C represents concentration of oxygen in mg/l. The following table denotes the experimental data associated with the model:

C (mg/l) 0.5 1 1.5 2 2.5 3 3.5 4

µ 1.10 3.34 5.29 6.66 7.58 8.81 8.60 8.89

Using lsqnonlin with initial guess of [1; 1] to compute the values of 𝐾𝐾𝑚𝑚𝑎𝑎𝑥𝑥 and 𝐾𝐾𝑠𝑠. (Write

algorithm in flow chart) (14)


16. a) Use the trapezoidal rule, with step-size of ℎ = 0.2 to obtain the following integral:

∫ 0.2𝑥𝑥 ln(𝑥𝑥) 𝑑𝑑𝑥𝑥32 (7)

b) Use Simpson’s 1/3rd Rule to solve the following integral:∫ 𝑐𝑐𝑥𝑥2 𝑑𝑑𝑥𝑥2

0 (7)

Module 4

17. Write a matlab program to solve the following ODE using RK-2 Ralston’s method:

𝑉𝑉 − 𝐼𝐼𝑅𝑅 − 𝐿𝐿𝑑𝑑𝐼𝐼𝑑𝑑𝑎𝑎

= 0

For inductance L = 2, resistance R = 2.5 and voltage V = 5. The initial value for this ODE is given by current I (0) = 0. Using step-size ℎ = 0.25, obtain the value of current I at time 2.

The Ralston’s method is given by:

𝑐𝑐𝑖𝑖+1 = 𝑐𝑐𝑖𝑖 + ℎ �𝑘𝑘1

3+

2𝑘𝑘2

3�

𝑘𝑘1 = 𝑓𝑓(𝑎𝑎𝑖𝑖 ,𝑐𝑐𝑖𝑖)𝑘𝑘1 = 𝑓𝑓 �𝑎𝑎𝑖𝑖 + 3ℎ4

,𝑐𝑐𝑖𝑖 + 3ℎ4𝑘𝑘1� (14)

18. Consider a system represented by the following ODE:

𝑚𝑚𝑑𝑑2𝑐𝑐𝑑𝑑𝑎𝑎2 + 𝑐𝑐

𝑑𝑑𝑐𝑐𝑑𝑑𝑎𝑎

+ 𝑘𝑘𝑥𝑥 = 0

Write a matlab program to solve the ODE using ode45. (initial conditions are x (0) = 𝑋𝑋0 and x’ (0) =𝑉𝑉0.)(14)

Module 5

19. Consider the following system of PDE’s :

𝜕𝜕𝑢𝑢1

𝜕𝜕𝑎𝑎= 0.024

𝜕𝜕2𝑢𝑢1

𝜕𝜕𝑥𝑥2 − 𝐹𝐹(𝑢𝑢1 − 𝑢𝑢2)

𝜕𝜕𝑢𝑢2

𝜕𝜕𝑎𝑎= 0.170

𝜕𝜕2𝑢𝑢2

𝜕𝜕𝑥𝑥2 + 𝐹𝐹(𝑢𝑢1 − 𝑢𝑢2)

Where, 𝐹𝐹(𝑐𝑐) = 𝑐𝑐2.15𝑐𝑐 − 𝑐𝑐−0.577𝑐𝑐

This equation holds on an interval 0 ≤ x ≤ 1 for times t ≥ 0.

The PDE satisfies the initial conditions, 𝑢𝑢1(𝑥𝑥, 0) = 0 &𝑢𝑢2(𝑥𝑥, 0) = 1


And boundary conditions: 𝜕𝜕𝑢𝑢1𝜕𝜕𝑎𝑎

(0, 𝑎𝑎) = 0 𝑢𝑢2(0, 𝑎𝑎) = 0

𝜕𝜕𝑢𝑢2

𝜕𝜕𝑎𝑎(𝑐𝑐, 𝑎𝑎) = 0 𝑢𝑢2(𝑐𝑐, 𝑎𝑎) = 1

Convert this system of PDE’s and associated conditions into a standard form expected by pdepe solver. Also write the algorithm to solve it.

(14)

20. A transfer system defined by an equation,

𝜋𝜋2 𝜕𝜕𝑇𝑇𝜕𝜕𝑎𝑎

= 𝜕𝜕𝜕𝜕𝑥𝑥

�𝜕𝜕𝑇𝑇𝜕𝜕𝑥𝑥�

This equation holds on an interval 0 ≤ x ≤ 1 for times t ≥ 0. The PDE satisfies the initial condition:

𝑇𝑇(𝑥𝑥, 0) = sin(𝜋𝜋𝑥𝑥) and boundary conditions:

𝑇𝑇(0, 𝑎𝑎) = 0 & 𝜋𝜋𝑐𝑐−𝑎𝑎 +𝜕𝜕𝑇𝑇(1, 𝑎𝑎)𝜕𝜕𝑥𝑥

= 0

Write a matlab code to plot T(x,t) for time 0 sec to 1 sec. (14)

Syllabus

Module 1

Matlab as calculator and Solving Equations - Vectors, Functions, and Plots in Matlab-Matlab Programs. Newton’s Method and Loops. Controlling Error and Conditional Statements. The Bisection Method and Locating Roots - Secant Methods – Computations.

Module 2

Linear Algebra - Matrices and Matrix Operations in Matlab. Introduction to Linear Systems - Accuracy, Condition Numbers and Pivoting LU Decomposition - Nonlinear Systems - Newton’s Method . Eigenvalues and Eigenvectors - Application of Eigenvectors: Vibrational Modes

Module 3

Functions and Data - Polynomial and Spline Interpolation. Least Squares Fitting: Noisy Data - Integration: Left, Right and Trapezoid Rules. Midpoint and Simpson’s Rules - Plotting Functions of Two Variables. Double Integrals for Rectangles - Double Integrals for Non-rectangles - Gaussian Quadrature.

Module 4

Differential Equations - Reduction of Higher Order Equations to Systems. Euler Methods - Higher Order


Methods. Multi-step Methods. ODE Boundary Value Problems and Finite Differences. Finite Difference Method – Nonlinear ODE and numerical optimization.

Module 5

Finite Difference Method - Parabolic PDEs. Explicit Method - Solution Instability for the Explicit Method - Implicit Methods. Insulated Boundary Conditions - Finite Difference Method for Elliptic PDEs. Convection-Diffusion Equations - Determining Internal Node Values. Numerical methods for partial differential equations – Engineering applications.

Text Books

1. Erwin Kreyszig, Advanced Engineering Mathematics, 8th Edition, Wiley2. Philips, G. M., Taylor. J.;

2. John J. Mathews and Kurtis D. Fink, Numerical Methods using Matlab, 4th Edition, Pearson Prentice

Hall.

Reference Books

1. Phillips G.M.M. and Peter J. Taylor, Theory and Applications of Numerical Analysis, 2nd Edition, b

Elsevier Science & Technology Books.

2. Todd Young and Martin J. Mohlenkamp, Introduction to Numerical Methods and Matlab Programming

for Engineers, Department of Mathematics Ohio University Athens, OH 45701

Course Contents and Lecture Schedule No Topic No. of Lectures 1 Module 1 7

1.1 Matlab as calculator and Solving Equations - Vectors, Functions, and Plots in Matlab-Matlab Programs.

2

1.2 Newton’s Method and Loops 1 1.3 Controlling Error and Conditional Statements 2 1.4 The Bisection Method and Locating Roots - Secant Methods –

Computations, 2

2 Module 2 7 2.1 Linear Algebra - Matrices and Matrix Operations in Matlab 1 2.2 Introduction to Linear Systems - Accuracy, Condition Numbers and

Pivoting 2

2.3 LU Decomposition - Nonlinear Systems - Newton’s Method 2 2.4 Eigenvalues and Eigenvectors - Application of Eigenvectors:

Vibrational Modes 2

3 Module 3 7 3.1 Functions and Data - Polynomial and Spline Interpolation 1 3.2 Least Squares Fitting: Noisy Data - Integration: Left, Right and

Trapezoid Rules 2


3.3 Midpoint and Simpson’s Rules - Plotting Functions of Two Variables 2 3.4 Double Integrals for Rectangles - Double Integrals for Non-rectangles

- Gaussian Quadrature2

4 Module 4 7 4.1 Differential Equations - Reduction of Higher Order Equations to

Systems 1

4.2 Euler Methods - Higher Order Methods 2 4.3 Multi-step Methods 1 4.4 ODE Boundary Value Problems and Finite Differences 1 4.5 Finite Difference Method – Nonlinear ODE and numerical

optimization 2

5 Module 5 7 5.1 Finite Difference Method - Parabolic PDEs 1 5.2 Explicit Method - Solution Instability for the Explicit Method - Implicit

Methods 1

5.3 Insulated Boundary Conditions - Finite Difference Method for Elliptic PDEs

1

5.4 Convection-Diffusion Equations - Determining Internal Node Values 2 5.6 numerical methods for partial differential equations – Engineering

applications 2


AOT342 DESIGN OF AEROSPACE STRUCTURES

CATEGORY L T P CREDIT

PEC 2 1 0 3

Preamble: This course provides knowledge on how to design an aerospace structure.

Prerequisite: Aerodynamics-I, Aircraft Structures-I


CO1 Understand the different Phases of Aircraft Design. Also Carry out preliminary design of Aircraft’s Maximum Take-off Weight Estimation.

CO2 Design a wing structure by proper airfoil selection with suitable taper ratio and twist

CO3 Design a propulsion system

CO4 Design a landing gear structure and subsystems CO5 Understand the effect of temperature in changing the properties of materials used for re-entry

vehicles.


PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO 10 PO 11 PO 12 CO1 3 2 1 CO2 3 2 1 CO3 3 2 1 CO4 3 2 1 CO5 3 2 1




Assignment/Quiz/Course project : 15marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks.



1. Explain the Conceptual design of an Aircraft

2. Draw the design wheel and explain the process.



1. Explain the Wings with various taper ratios: (a) Rectangle (λ = 1); (b) Trapezoid 0 < λ < 1

(straight tapered); and (c) Triangle (delta) λ = 0

2. Explain the Significance of Lift and Load Distributions in wing design


1. Explain the Functional Analysis and Design Requirements of propulsion systems.

2. Design a propulsion system for a low-wing, T-tail, transport aircraft to carry eight passengers for a range

of 4000 km with the following characteristics:mTO = 7000 kg, S = 29m2, CDo = 0.028, AR = 8, e = 0.92

The aircraft must be capable of cruising with a maximum cruising speed of 320 KTAS at 20 000 ft

altitude. For this problem, you need to discuss and determine the Propeller Diameter.


1. Explain the different types of landing gear configuration

2. A GA aircraft with a mass of 5000 kg has a tricycle landing gear configuration. The wheel base and wheel

track are 10.2m and 1.8m respectively, and the distance between the main gear and the aircraft cg is 0.84 m.

Determine the static load on each gear. What percentage of the aircraft weight is carried by the nose gear?


1. What are the materials used in re-entry vehicles.

2. Explain the various stages of creep and their influence in the functional life of the materials.


Model Question Paper

QP CODE:

Reg No .:_______________

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY SIXTH SEMESTER

B. TECH DEGREE EXAMINATION, MONTH & YEAR

Course Code:AO342

DESIGN OF AEROSPACE STRUCTURES


PART A



1. Write the different Phases of Aircraft Design.

2. Write the formulae for MTOW

3. Explain the nomenclature of NACA 4 Series & 6 series airfoil with example.

4. Draw a graph for the effect of AR on Cl vs Angle of attack.

5. Define Propulsive Efficiency.

6. Draw the flowchart of Air vehicle engines classification.

7. Draw the wheel base and wheel track for a tri-cycle landing gear.

8. What is Tip back angle requirements?

9. Define creep curve.

10. Explain strain rate.

PART B



Module -1

11. Explain the following four elements of MTOW


1. Payload weight (WPL) 2. Crew weight (WC). 3. Fuel weight (Wf) 4. Empty weight (WE). (14)

(or)

12. Explain the three phases of Aircraft Design. (14)

Module -2

13. Explain the two ways to determine the wing airfoil section. (14)

(or)

14. Explain the Airfoil Selection Criteria. (14)

Module -3

15. Explain the general guidelines for Engine location with suitable diagram. (14)

(or)

16. A light GA aircraft with a cruising speed of 130 knot at 15 000 ft employs a 180-hp piston engine. Aregular two-blade metal prop is going to be used. Assume that the engine power is kept constant upto the cruising altitude by using a turbocharger.

1. Estimate the propeller diameter for this engine.2. What would be the propeller rotational speed (in rpm) for this cruising flight? (14)

Module -4

17. Explain the Functional Analysis and Design Requirements for landing gear structure with flow chart. (14)

(or)

18. A pilot of the jet aircraft shown in Figure below is going to take off with 12 deg of fuselage angle ofattack. Determine if the aircraft rear fuselage will hit the ground during take-off rotation. If yes, whatmust be the main gear height to achieve a clearance of 30 cm? (14)


Module -5

19. Explain the various stages of creep and their influence in the functional life of the materials.

(14)

(or)

20. Describe the effects of components due to be effect of stress, temperature and strain rates.

(14)

SYLLABUS

MODULE 1 Introduction to design, Phases of Aircraft Design - Conceptual design, Preliminary Design & Detail Design; Maximum Take-off Weight Estimation-Weight Build-up, Payload Weigh, Crew weight, Fuel Weight, Empty Weight. Wing Area and sizing

MODULE 2

General features of an airfoil, Characteristic graphs of an Airfoil, Airfoil Selection Criteria, NACA Airfoils- Four, Five & 6-Series NACA Airfoils. Aspect Ratio – effect of AR on Cl vs Angle of attack. Taper Ratio – effect of taper ration on lift distribution. Twist angles -geometric twist, Aerodynamic twist. Lifting-Line theory

MODULE 3

Aircraft Engine Classification- Piston-prop Propulsion system, Turbojet Engine, Turbofan Engine, Turboprop Engine, Turboshaft Engine, Rocket Engine. Selection of Engine type- absolute ceiling and Flight Mach number, Propulsive efficiency, Specific fuel consumption, Engine weight, Passenger Appeal, Noise & vibration, Engine maintainability, Engine size. Engine Location- General guidelines, Twin-Jet Engine: Under-Wing versus Rear Fuselage. Propeller Sizing (Numerical Problem)

MODULE 4

Landing gear configuration. Landing gear height- Aircraft general Ground clearance Requirement, Take-off Rotation Ground Clearance Requirement, Wheel base, Wheel track – Overturn angle requirements, Structural integrity. Tip back & Tip forward angle requirements (Numerical Problem). Landing gear subsystem- Tire sizing, Shock Absorber, Strut sizing, Landing gear retraction System.

MODULE 5

High Temperature materials, Iron base, Nickel base, Cobalt base super alloys and their properties. Factors influencing functional life of components at elevated. Definition of creep curve. Various stages of creep, metallurgical factors influencing various stages. Effect of stress, temperatures and strain rate.

Texts and References:

1. Sadraey, M. H., Aircraft Design: A Systems Engineering Approach, Wiley (2012).


2. Raymer, D. P., Aircraft Design: A Conceptual Approach, 4th ed., AIAA Edu. Series (2006).

3. Bruhn, E. F., Analysis and Design of Flight Vehicle Structures, 2nd ed., Jacobs Publishing Inc. (1973).

4. Niu, M. C.Y., Airframe Structural Design, 2nd ed., Hongkong Conmilit Press Ltd.(2002). 5. Courtney T .H, “Mechanical Behaviour of Materials”, McGraw-Hill, USA, 1990.). 6. Hertzberg R.W., “Deformation and Fracture Mechanics of Engineering materials”,4thEdition, John

Wiley, USA, 1996. 7. Raj. R., “Flow and Fracture at Elevated Temperatures”, American Society for Metals, USA, 1985

Course Contents and Lecture Schedule No Topic No. of Lectures 1 MODULE 1 1.1 Introduction to design, Phases of Aircraft Design - Conceptual design,

Preliminary Design & Detail Design 2

1.2 Maximum Take-off Weight Estimation-Weight Build-up, Payload Weigh, Crew weight, Fuel Weight, Empty Weight

2

1.3 Wing Area and sizing 2 2 MODULE 2 2.1 General features of an airfoil, Characteristic graphs of an Airfoil, Airfoil

Selection Criteria, NACA Airfoils- Four, Five & 6-Series NACA Airfoils

1

2.2 Aspect Ratio – effect of AR on Cl vs Angle of attack. 1 2.3 Taper Ratio – effect of taper ration on lift distribution 2 2.4 Twist angles -geometric twist, Aerodynamic twist. 2 2.5 Lifting-Line theory 2 3 MODULE 3 3.1 Aircraft Engine Classification- Piston-prop Propulsion system, Turbojet

Engine, Turbofan Engine, Turboprop Engine, Turboshaft Engine, Rocket Engine

1

3.2 Selection of Engine type- absolute ceiling and Flight Mach number 2 3.3 Propulsive efficiency, Specific fuel consumption, Engine weight,

Passenger Appeal, Noise & vibration, Engine maintainability, Engine size

2

3.4 Engine Location- General guidelines, Twin-Jet Engine: Under-Wing versus Rear Fuselage

2

3.5 Propeller Sizing (Numerical Problem) 2 4 MODULE 4 4.1 Landing gear configuration. 1 4.2 Landing gear height- Aircraft general Ground clearance Requirement,

Take-off Rotation Ground Clearance Requirement, Wheel base, Wheel track – Overturn angle requirements, Structural integrity. Tip back & Tip forward angle requirements (Numerical Problem)

3

4.3 Landing gear subsystem- Tire sizing, Shock Absorber, Strut sizing, Landing gear retraction System

2

5 MODULE 5 5.1 High Temperature materials, Iron base, Nickel base, Cobalt base super

alloys and their properties 1


5.2 Factors influencing functional life of components at elevated temperatures.

1

5.3 Definition of creep curve. 1 5.4 Various stages of creep, metallurgical factors influencing various

stages. 1

5.5 Effect of stress, temperatures and strain rate. 2


AOT 352 AERO ACOUSTICS CATEGORY L T P CREDIT

PEC 2 1 0 3 Preamble: This course provides knowledge of stresses, strains and deformations in components due to various loads. It helps in assessing the stresses and deformations through mathematical models of beams, twisting bars or combinations of both. Also helps to design prismatic components using failure criteria. Prerequisite: Nil

Course Outcomes:After the completion of the course the student will be able to

CO 1 Understand acoustics definitions and plane wave solutions in time and frequency domain

CO 2 Explain importance of Lighthill’s analogy and lighthill’s equation in turbulence acoustic field. CO 3 Apply acoustic concepts in duct, cavity and mufflers to reduce noise

CO 4 Explain different types of noise generation in aircraft. CO 5 Understand different sound measuring instruments and their working.


PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO 10 PO 11 PO 12 CO 1 3 1 2 CO 2 3 1 1 1 2 CO 3 3 1 1 2 CO 4 3 2 CO 5 3 2 Assessment Pattern


Remember 10 10 20 Understand 10 10 20 Apply 30 30 60 Analyse Evaluate Create Mark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks




1. Explain De-Alembert’s solution for plane wave equation.

2. Derive harmonic solution from De-Alembert’s solution

3. Derive the expression for particle velocity and acceleration for a plane wave


1. Derive acoustic wave equation by considering viscosity of fluids

2. Derive harmonic frequencies for the reflection of sound in both end open pipe..


1. Explain reflection and absorptive types of muffler with neat sketch..

2. Explain sound generation by turbulence.

3. Discuss about noise absorption materials.


1. With neat figures, explain subsonic and supersonic jet noises

2. Explain the noise generation in combustion chamber of an aircraft engine


1. Explain different scales for noise control in environment.

2. Describe the working of a sound level meter with neat diagram.

3. Explain different techniques to measure the sound power using a microphone.



QP CODE: Reg No: --------------------------


MONTH & YEAR

Course Code: AOT352

AEROACOSUTICS


PART A



1. Explain acoustic intensity and impedance.

2. Draw the characteristic curve for forward moving wave and backward moving wave.

3. Write governing equations of fluid mechanics in tensor form

4. Write the issues related to computational aero acoustics

5. Draw the schematic diagram of a typical Reactive muffler.

6. Enumerate the properties of acoustic materials.

7. Explain Entropy noise.

8. What is acoustic liners? Why it is used in turbofan engines

9. How is the decibel scale different than the phon scale?

10. Write the classification of hearing loss indexes?

PART B Answer any one full question from each module.

(Each question carries 14 Marks) Module 1

11. (a)Derive 3 governing equations for acoustic wave propagation. Hence convert these 3 equations into a single equation with one unknown. (8)

(b) Derive an expression for the sound energy density of a harmonic plane acoustic wave.

(6)


12. (a) Prove that the speed of sound in air is proportional to the square root of the absolute temperature. (7)

(b) Show that the ratio of the acoustic powers of two sounds in decibels is equal to the difference of their power levels. (7)

Module 2

13. (a)Derive Lighthill’s equation and explain Lighthill’s analogy (10)

(b) Explain monopoles, dipoles and quadrapole sources. (4)

14. Solve the initial value problem

𝝏𝝏𝝏𝝏𝝏𝝏𝝏𝝏

+𝝏𝝏𝝏𝝏𝝏𝝏𝒙𝒙

= 𝟏𝟏

𝝏𝝏 = 𝟏𝟏 𝝏𝝏 = 𝟏𝟏.𝟏𝟏 𝒏𝒏𝒙𝒙𝒆𝒆 �−(𝒍𝒍𝒏𝒏𝟐𝟐) �𝒙𝒙𝟑𝟑�𝟐𝟐�

Give numerical solution at t = 100 over -20 ≤ x ≤450. State the size of Δtused. (14)

Module 3

15.Derive an expression of acoustic energy in aircraft interiors. Also discuss the different mode shapes. (14)

16.(a) What is muffler? Explain different types of mufflers. (7)

(b) Explain how noise suppression devices reduce the turbo-machinery noise (7)

Module 4

17. (a) Explain different types of helicopter rotor noises. (8) (b) Explain direct combustion noise and indirect combustion noise with figure. (6)

18.Explain how acoustic waves and entropy waves are generated in aircraft combustion chambers. (14)

Module 5

19.(a) Explain the impact of noise levels on humans (7)


(b) What is intensity probe? Explain any 3 types of intensity probe. (7)

20.(a) Explain any two sound measuring instruments? (7)

(b) Explain how noise can control by path alterations. (7)

Syllabus

Module 1

Basic acoustic terminology and definitions - Plane waves and harmonic solution - velocity of sound in fluids - relationship between wave lengths, particle velocities, acceleration.Acoustic energy density and intensity - acoustic impedance associated with fluid flows.Logarithmic decibel scales – acoustic reference standards and noise regulations Module 2

Conservation laws and governing equations of fluid mechanics - Lighthill’s analogy and derivation of Lighthill’s equation. Noise generated from flow turbulence – sound generation in subsonic and supersonic fluid flow over solid and flexible boundaries. Sound radiation from simple sources like monopole, dipole and quadrapoles. Brief introduction to computational aero acoustics. Module 3

Duct acoustics sound fields in ducts and wave guides – property of duct modes. Cavity noise- turbo-machinery noise and buzz-saw noise - noise suppression devices like mufflers and plenum chambers. Noise insulation and absorption – Acoustic materials. Module 4

Various sources of noise in an aircraft - noise produced by engine, propellers, fans, combustion chambers,- helicopter rotor noise – noise generated by subsonic and supersonic jets and rocket exhausts. Noise produced by boundary layers on external surfaces- like fins and stabilizers or from sonic boom. Module 5

Impact of noise levels on humans and environment. Phone and Sone scales. Perceived noise levels and noise number index - hearing loss index. Aircraft noise regulations near airports – important noise measurements and common instruments. Noise control by source modification, transmission path alterations and receiver protection. Text Books

1. M.E. Goldstein, Aero acoustics, 1st Edition, Mc Graw Hill Publications, 1976

2. R.J. Peters, B.J. Smith and Margret Hollins, - Acoustics and Noise Control, Routledge Publications, London, 2011.


Reference Books 1. Tarit. K. Bose, Aerodynamic Noise – An introduction for physicists and engineers, Springer Publications,

2013 ISBN:9781461450191

2. Blackstock, David T, Fundamentals of physical acoustics. John Wiley & Sons, 20003. S.Jose, Sudhi Mary Kurian, Mechanics of Solids, Pentagon, 2015

3. Reynolds D. D., Engineering Principles of Acoustics, Allyn and Bacon Inc., Boston, 1981


No Topic No. of Lectures 1 Module 1 7

1.1 Basic acoustic terminology and definitions 1 1.2 Plane waves and harmonic solution 1 1.3 velocity of sound in fluids - relationship between wave lengths, particle

velocities, acceleration 2

1.4 Acoustic energy density and intensity - acoustic impedance associated with fluid flows

2

1.5 Logarithmic decibel scales – acoustic reference standards and noise regulations

1

2 Module 2 7 2.1 Conservation laws and governing equations of fluid mechanics 1 2.2 Lighthill’s analogy and derivation of Lighthill’s equation. 1 2.3 Noise generated from flow turbulence – sound generation in subsonic

and supersonic fluid flow over solid and flexible boundaries. 1

2.4 Sound radiation from simple sources like monopole, dipole and quadrapoles.

2

2.5 Brief introduction to computational aero acoustics 2 3 Module 3 7

3.1 Duct acoustics sound fields in ducts and wave guides – property of duct modes.

2

3.2 Cavity noise- turbo-machinery noise and buzz-saw noise. 1 3.3 Noise suppression devices like mufflers and plenum chambers. 2 3.4 Noise insulation and absorption – Acoustic materials. 2 4 Module 4 7

4.1 Various sources of noise in an aircraft - noise produced by engine, propellers, fans, combustion chambers, helicopter rotor noise.

2

4.2 Noise generated by subsonic and supersonic jets and rocket exhausts. 2 4.3 Noise produced by boundary layers on external surfaces- like fins and

stabilizers or from sonic boom. 3

5 Module 5 7 5.1 Impact of noise levels on humans and environment. 1 5.2 Phone and Sone scales. Perceived noise levels and noise number index -

hearing loss index. 2


5.3 Aircraft noise regulations near airports – important noise measurements and common instruments.

2

5.4 Noise control by source modification, transmission path alterations and receiver protection.

2


AOT362 FUNDAMENTALS OF COMBUSTION CATEGORY L T P CREDIT

PEC 2 1 0 3

Preamble: The course is meant to give the learners an introduction to combustion science.


CO 1 Understand the basic thermodynamics of combustion. CO 2 Basics of Ignition and flammability. CO 3 Explain types of flames and stability. CO 4 Understand the basics of solid and liquid propellent combustion. CO 5 Analyse the consequences of combustion process on environment.


Assessment Pattern



Mark distribution

Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can

PO 1


PO 11

PO 12

CO 1 3 CO 2 3 CO 3 3 2 CO 4 3 2 2 CO 5 3


have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions


1. State the importance of the heat of formation, heat of reaction in combustion.

2. Determine the equilibrium constants and equilibrium composition.

3. Understand the Arrhenius Law and activation energy.


1. Define terms like ignition and flammability.

2. Determine the self-ignition temperature.

3. Explain factors affecting flammability limits.


1. Understand the different types of flames.

2. Discuss the empirical equations for laminar and turbulent flame velocities.

3. Explain mechanisms of flame stabilization.


1. Discuss the process of solid propellant combustion.

2. Discuss the process of liquid propellant combustion.

3.Understand the types of combustion instabilities in rockets.


1. Explain the drawbacks of combustion products.

2. Discuss the mechanisms for NOx and soot formation.

3. Explain the emissions and their control.


QP CODE: Reg No: --------------------------

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY B.TECH DEGREE EXAMINATION

MONTH & YEAR

Course Code: AOT362

FUNDAMENTALS OF COMBUSTION



PART A



1. What is bond energy?

2. Explain activation energy.

3. What do you mean by self-ignition? Give an example.

4. Define the term flame quenching.

5. What do you understand by laminar flame?

6. Write down the empirical relation for turbulent flame velocity.

7. List any three propellent combinations for; solid and liquid propellants.

8. Define bulk and wave mode instability.

9. Explain different types of emissions.

10. How temperature and residence time influence the formation of pollutants?

PART B



Module 1

11.a) Calculate the standard heat of formation of n-butane (g) C4H10 at 298 K. (9) b) Explain the term adiabatic flame temperature and equilibrium constant. (5)

12.a) Define order and molecularity of a reaction. What is half-life? (5) b)A second order reaction involving reactants with initial concentration 0.05 mol/l is found to

be 25 percent complete in 150 s. Calculate. i. The reaction rate constant ii. The half-life of reaction

iii. The time taken it would take for the reaction to be 25% complete if the initial concentration was 0.005 mol/l (9)

Module 2

13. a) What is flammability? Elaborate on the factors affecting flammability. (4)


b) What is meant by quenching diameter? Drive an expression for the same. (10)

14. a) Explain the factors affecting minimum ignition energy. (7)

b) Explain the phenomenon of forced ignition. (7)

Module 3

15. a) Explain the differences between premixed flames and diffusion flames with

examples. (7) b) Explain the structure of a laminar flame. How is it different from a turbulent

flame? (7)

16. a) What is flame stabilisation? Explain any two methods for flame stabilisation. (7)

b) What is the difference between self-ignition and forced ignition?

Explain the thermal theory of ignition. (7)

Module 4

17. a) Explain the combustion process in a solid motor. (7) b) Write a short note on acoustic instability. (7)

18. a) Discuss the various combustion zones in liquid propellent combustion. (7)

b) Why is it difficult to have a supersonic combustion?How supersonic combustion can be attained effectively. (7)

Module 5

19. a) Write a short note on various methods to control emission. (7)

b) Discuss the relationship between NOx and soot formation. (7)

20. a) Explain the various mechanisms for NOx formation. (7)

b) What are the impacts on environment due to combustion products? (7)


Syllabus

Module 1

Thermodynamics of reacting mixtures – bond energy, heat of formation, heat of reaction, adiabatic flame temperature – entropy changes for reacting mixtures – chemical equilibrium –equilibrium criteria – evaluation of equilibrium constants and equilibrium composition. Elements of chemical kinetics – Law of mass action – order and molecularity of reaction – rate equation – Arrhenius Law – activation energy – collision theory of reaction rates – transition state theory – general theory of chain reactions – combustion of CO and hydrogen. Module 2

Ignition and flammability – methods of ignition – self and forced ignition – thermal theory of ignition – determination of self-ignition temperature and experimental results – energy required for ignition- limits of inflammability – factors affecting flammability limits – flame quenching – effects of variables on flame quenching. Module 3

Flame propagation – factors affecting flame speed – premixed and diffusion flames, physical structure and comparison – characteristics of laminar and turbulent flames – theory of laminar flame propagation – empirical equations for laminar and turbulent flame velocities. Flame stabilization -stability diagrams for open flames – mechanisms of flame stabilization, critical boundary velocity gradient – stabilization by eddies – bluff body stabilization – effects of variables on stability limits. Module 4

Combustion in rockets – solid motors, physical and chemical processes, ignition process, combustion instability; liquid propellant combustion, combustion process, combustion zones, combustion instability, supersonic combustion. Module 5

Emissions, negative effects of combustion products, pollution formation - parameters controlling formation of pollutants, CO oxidation, mechanisms for NOx formation and controlling, soot formation, relation between nitrogen oxide and soot formation, oxides of sulphur, emissions and their control. Text Books

1. D. P. Mishra, “Fundamentals of Combustion”, Prentice Hall of India, New Delhi, 2008. 2. Sara McAllister l Jyh-Yuan Chen A. Carlos Fernandez-Pello “Fundamentals of Combustion Processes”,

Springer, 2011. 3. George P. Sutton and Oscar Biblarz “Rocket Propulsion Elements”,9th edition, Wiley 2017

Reference Books 1. Kuo K.K. “Principles of Combustion” John Wiley and Sons, 2005. 2. Strehlow R A., “Fundamentals of combustion” McGraw Hill Book Company, 1984.



No

Modules No. of

Lectures 1 Module: 1

1.1 Thermodynamics of reacting mixtures – bond energy, heat of formation, heat of reaction, adiabatic flame temperature – entropy changes for reacting mixtures.

2

1.2

Chemical equilibrium –equilibrium criteria – evaluation of equilibrium constants and equilibrium composition.

2

1.3

Elements of chemical kinetics – Law of mass action – order and molecularity of reaction – rate equation – Arrhenius Law – activation energy.

2

1.4

Collision theory of reaction rates – transition state theory – general theory of chain reactions – combustion of CO and hydrogen.

2

2 Module: 2

2.1 Ignition and flammability – methods of ignition – self ignition – thermal theory of ignition.

2

2.2

Determination of self-ignition temperature and experimental results – energy required for ignition.

2

2.3 Limits of inflammability – factors affecting flammability limits – flame quenching – effects of variables on flame quenching.

3

3 Module: 3

3.1 Flame propagation – factors affecting flame speed – premixed and diffusion flames, physical structure and comparison –

2

3.2

Characteristics of laminar and turbulent flames – theory of laminar flame propagation – empirical equations for laminar and turbulent flame velocities.

2

3.3

Flame stabilization -stability diagrams for open flames – mechanisms of flame stabilization,

2

3.4

Critical boundary velocity gradient – stabilization by eddies – bluff body stabilization – effects of variables on stability limits.

2

4 Module: 4

4.1 Solid motor combustion, physical and chemical processes, ignition process, combustion instability;

2

4.2

Liquid propellant combustion, combustion process, combustion zones, combustion instability, supersonic combustion.

3

5 Module: 5

5.1 Emissions, negative effects of combustion products, pollution formation - parameters controlling formation of pollutants,

2

5.2

CO oxidation, mechanisms for NOx formation and controlling, soot formation,

2

5.3

Relation between nitrogen oxide and soot formation, oxides of sulphur, emissions and their control.

3


AOT372 NON-DESTRUCTIVE TESTING


PEC 2 1 0 3

Preamble: To understand the basic principles, techniques, equipment, applications and limitations of NDT methods

Prerequisite: Nil


CO1 To introduce the basic principles, techniques, equipment, applications and limitations of NDT methods such as Visual, Penetrant Testing, Magnetic Particle Testing, Ultrasonic Testing, Radiography, Eddy Current.

CO2 To enable selection of appropriate NDT methods.

CO3 To identify advantages and limitations of nondestructive testing methods CO4 To make aware the developments and future trends in NDT. CO5 Able to differentiate various defect types and select the appropriate NDT

methods for the specimen. Mapping of course outcomes with program outcomes PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO 10 PO 11 PO 12

CO1 3 1 1 CO2 3 1 1

CO3 3 1 1

CO4 3 1 1

CO5 3 1 1 Mark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours


Attendance : 10 marks


Assignment/Quiz/Course project : 15 marks


End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14marks. Course Level Assessment Questions


1. Write the two advanced methods of visual inspections.

2. What are the visual inspection aids? Highlight the use of Borescope in visual testing.

3. How to evaluate the penetrant test indications? Explain about the false indications and suggest

some precautions to avoid false indications.


1. How can you interpret the MPI and explain the indications during the magnetic particle testing

procedure?

2. Which method you prefer to use to magnetize the complex geometry? And explain the procedure in detail with suitable examples and diagrams.

3. Explain the direct and indirect methods of magnetism.

Course Outcome 3(CO3)

1. Explain different types of sound waves and mode conversion.

2. Explain types of scanning methods in Ultrasonic testing.

3. Discuss the advantages, limitations & variables of Ultrasonic testing.


1. Explain the types of films used in radiography.

2. Explain in detail about the personal safety & radiation protections should take for radiographic

procedure.


1. Which method is best for inspection in pipe line of refinery? Why?

2. Explain all the aspects in detail how ECT is used for hardness measurement, conductivity

measurement, coating thickness measurement and defect detection.


Model Question Paper

QP CODE: Reg No .:_______________

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY SIXTH SEMESTER B. TECH DEGREE EXAMINATION, MONTH

& YEAR

Course Code: AOT372 NON-DESTRUCTIVE TESTING


PART A



1. Explain importance of NDT over Destructive Testing methods.

2. What is dwell time?

3. Explain the principle of MPT & its limitations

4. Draw the hysteresis curve for ferromagnetic material

5. Write the types of scanning methods in Ultrasonic testing.

6. Why coplant is used in ultrasonic testing? Write its advantages and disadvantages.

7. What is the importance of penetrameter used in Radiography testing.

8. Differentiate X-rays and γ rays.

9. State the laws used for Eddy current testing.

10. Which method is best for Insitu inspection in pipe line of refinery? Why?

PART B



Module -1

11. a) Explain the principle of borescope and fiberscope with neat diagram? (10)

b) Discuss the factors which affect visual testing method. (4)

(or)

12. a) Explain the procedure of Post emulsifier method with suitable flow charts and diagrams. (10)


b) Discuss on fluorescent LPT method and its sensitivity. (4)

Module -2 13. a) Derive Define the following (10)

i) Permeability.

ii) Flux density.

iii) Coersive force.

iv) residual magnetism

v) Retentivity

b) What are the instruments used to measure the effectiveness of the demagnetizing sequence? (14)

(or)

14.Which NDT technique would you recommend for testing ferromagnetic components for open-to-

surface and also for sub surface discontinuities? Explain in brief the principle and working of the test you

have recommended.

(14)

Module -3

15. a) Classify Ultrasonic inspection methods. Explain through transmission technique. (7)

b) Discuss the advantages, limitations & variables of Ultrasonic testing. (7)

(or)

16. a) Explain different types of sound waves and mode conversion. (5)

b)With neat sketch explain different probes and probe methods used in UT. (5)

c) explain the Pulse echo technique of U.T. (4)

Module -4

17. a) Explain the following Radiographic technique with suitable diagrams (9)

i. SWSI

ii. DWSI

iii. DWDI

b) What are the factors should be consider to choose the radiographic film? (5)

(or)

18. a) What are the requirements should meet to design a type of radiographic film. (4) b) Explain the following: (10)

i. Fluoroscopy ii. Micro radiography


iii. Enlargement radiography iv. High speed or flash radiography v. Auto radiography

vi. Electron transmission radiography vii. Electron emission radiography

viii. Neutron radiography ix. Proton radiography x. Stereo radiography

Module -5

19. a) What are different types of test coils used in E.C.T. Explain their typical applications (10)

b) Explain the principle of Eddy current testing & its applications. (4)

(or)

20. a) How ECT is used for conductivity measurements? Explain in detail with suitable examples. (7)

b) Explain all the aspects in detail how ECT is used for hardness measurement, conductivity

measurement, coating thickness measurement and defect detection. (7)

AERONAUTICAL ENGINEERINGSYLLABUS

MODULE 1

Introduction to NDT, Comparison between destructive and NDT, Importance of NDT, Scope of NDT, difficulties of NDT, future progress in NDT, economics aspects of NDT. Visual Inspection - tools, applications and limitations - Fundamentals of visual testing: vision, lighting, material attributes, environmental factors. visual perception, direct and indirect methods mirrors, magnifiers, boroscopes, fibroscopes, closed circuit television, light sources special lighting, a system, computer enhanced system Liquid Penetrant Inspection: principles, properties required for a good penetrants and developers - Types of penetrants and developers, advantages and limitations of various methods of LPI - LPI technique/ test procedure interpretation and evaluation of penetrant test indications, false indication and safety precaution required in LPI, applications, advantages and limitations

MODULE 2

Magnetic Particle Inspection (MPI)- Principles of MPI, basic physics of magnetism, permeability, flux density, cohesive force, magnetizing force, rentivity, residual magnetism Methods of magnetization, magnetization techniques such as head shot technique, cold shot technique, central conductor testing, magnetization using products using yokes Direct and indirect method of magnetization, continuous testing of MPI, residual technique of MPI, system sensitivity, checking devices in MPI

MODULE 3

Ultrasonic Testing (UT): principle, types of waves, frequency, velocity, wavelength, reflection, divergence, attenuation, mode conversion in ultrasonic UT testing methods contact testing and immersion testing, normal beam and straight beam testing, angle beam testing, dual crystal probe, ultrasonic testing techniques resonance testing, through transmission technique, pulse echo testing technique, instruments used UT, accessories such as transducers, types, frequencies, and sizes commonly used Reference blocks with artificially created defects, calibration of equipment, Applications, advantages, limitations, A, B and C scan - Time of Flight Diffraction (TOFD).

MODULE 4

Radiography Testing (RT): Principle, electromagnetic radiation sources: X-ray source, production of X-rays, high energy X-ray source, gamma ray source - Properties of X-rays and gamma rays Inspection techniques like SWSI, DWSI, DWDI, panoramic exposure, real time radiography, films used in industrial radiography, types of film, speed of films, qualities of film screens used in radiography, quality of a good radiograph, film processing, interpretation, evaluation of test results, safety aspects required in radiography applications, advantages and limitations of RT

MODULE 5

Eddy Current Testing (ECT) - Principle, physics aspects of ECT like conductivity, permeability, resistivity, inductance, inductive reactance, impedance Field factor and lift of effect, edge effect, end effect, impedance plane diagram in brief, depth of penetration of ECT, relation between frequency and depth of penetration in ECT equipments and accessories, various application of ECT such as conductivity measurement, hardness measurement, defect detection coating thickness

AERONAUTICAL ENGINEERINGmeasurement, advantages and limitations of eddy current testing

Texts and References

1. Baldev Raj, Practical Non – Destructive Testing, Narosa Publishing House ,1997 2. Hull B. and V.John, Non-Destructive Testing, Macmillan,1988 3. Krautkramer, Josef and Hebert Krautkramer, Ultrasonic Testing of Materials, Springer

Verlag, 1990


No Topic No. of Lectures 1 MODULE 1

1.1 Introduction to NDT, Comparison between destructive and NDT, Importance of NDT, Scope of NDT, difficulties of NDT, future progress in NDT, economics aspects of NDT.

1

1.2 Visual Inspection - tools, applications and limitations - Fundamentals of visual testing: vision, lighting, material attributes, environmental factors. visual perception, direct and indirect methods mirrors, magnifiers, boroscopes, fibroscopes, closed circuit television, light sources special lighting, a systems, computer enhanced system

2

1.3 Liquid Penetrant Inspection: principles, properties required for a good penetrants and developers - Types of penetrants and developers 2

1.4 advantages and limitations of various methods of LPI - LPI technique/ test procedure 2

1.5 interpretation and evaluation of penetrant test indications, false indication and safety precaution required in LPI, applications, advantages and limitations

2

2 MODULE 2 2.1 Magnetic Particle Inspection (MPI)- Principles of MPI, basic physics of

magnetism, permeability, flux density, cohesive force, magnetizing force, rentivity, residual magnetism

2

2.2 Methods of magnetization, magnetization techniques such as head shot technique, cold shot technique, central conductor testing, magnetization using products using yokes

2

2.3 direct and indirect method of magnetization, continuous testing of MPI, residual technique of MPI, system sensitivity, checking devices in MPI 2

3 MODULE 3 3.1 Ultrasonic Testing (UT): principle, types of waves, frequency, velocity,

wavelength, reflection, divergence, attenuation, mode conversion in ultrasonic UT testing methods

2

3.2 contact testing and immersion testing, normal beam and straight beam testing, angle beam testing, dual crystal probe, ultrasonic testing techniques

2

3.3 resonance testing, through transmission technique, pulse echo testing technique, instruments used UT, accessories such as transducers, types, frequencies, and sizes commonly used

2

3.4 Reference blocks with artificially created defects, calibration of equipment, Applications, advantages, limitations, A, B and C scan - Time of Flight Diffraction (TOFD).

1

4 MODULE 4

AERONAUTICAL ENGINEERING4.1 Radiography Testing (RT): Principle, electromagnetic radiation sources:

X-ray source, production of X-rays, high energy X-ray source, gamma ray source - Properties of X-rays and gamma rays

2

4.2 Inspection techniques like SWSI, DWSI, DWDI, panoramic exposure, real time radiography, films used in industrial radiography, types of film, speed of films, qualities of film

2

4.3 screens used in radiography, quality of a good radiograph, film processing, interpretation, evaluation of test results, safety aspects required in radiography

2

4.4 Applications, advantages and limitations of RT 1 5 MODULE 5

5.1 Eddy Current Testing (ECT) - Principle, physics aspects of ECT like conductivity, permeability, resistivity, inductance, inductive reactance, impedance

1

5.2 Field factor and lift of effect, edge effect, end effect, impedance plane diagram in brief, depth of penetration of ECT, relation between frequency and depth of penetration in ECT equipments and accessories,

2

5.3 Various application of ECT such as conductivity measurement, hardness measurement, defect detection coating thickness measurement, 2

5.4 Advantages and limitations of eddy current testing 1


SEMESTER VI MINOR


AOT382 EXPERIMENTAL AERODYNAMICS AND FLOW

VISUALIZATION


VAC 3 1 0 4

Preamble: Objective of this course is to study the electronics applications into aviation field and

various systems with instruments used for successful flight.

Prerequisite: Nil Course Outcomes: After the completion of the course the student will be able to CO 1 Understand the behaviour of subsonic and supersonic wind tunnels. CO 2 Understand the lift and drag coefficient calculation for pressure and velocity distributions

over the surfaces. CO 3 Understand the various velocity, pressure and temperature measurement techniques. CO 4 Understand the boundary layer effects and heating problems. CO 5 Understand the various flow visualization techniques. Mapping of course outcomes with program outcomes PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO

10 PO 11

PO 12

CO 1 3 2 1 - - - - - - - - - CO 2 3 2 1 - - - - - - - - - CO 3 3 2 1 - - - - - - - - - CO 4 3 2 1 - - - - - - - - - CO 5 3 2 1 - - - - - - - - - Assessment Pattern Bloom’s Category Continuous Assessment Tests End Semester Examination

1 2 Remember 15 15 30 Understand 35 35 70 Apply Analyse Evaluate Create Mark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks

AERONAUTICAL ENGINEERINGAssignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions Course Outcome 1 (CO1): 1. Write a short note on ultrasonic flow meters?

2. What is wake survey? Explain its significances.

Course Outcome 2 (CO2): 1. Explain about turbulence factor and its importance.

2. How running time is calculated in supersonic wind tunnel?

Course Outcome 3(CO3): 1. Explain how wall shear stress is used in the estimation of Cd?

2. Explain the heating requirements in hypersonic wind tunnels.

Course Outcome 4 (CO4): 1. Write a short note on pressure transducers and rotameters.

2. Explain how the test section average velocity is estimated using traversing rakes.

Course Outcome 5 (CO5): 1. What is the Pitot - static tube correction for subsonic and supersonic Mach numbers?

2. Explain the preliminary estimation of nozzle area ratios and mass flow for a given test section size and Mach number.

AERONAUTICAL ENGINEERINGModel Question paper

QP CODE: Reg No: _______________

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY SIXTH SEMESTER B. TECH DEGREE

EXAMINATION, MONTH & YEAR

Course Code: AOT382 EXPERIMENTAL AERODYNAMICS AND FLOW VISUALIZATION


PART A



1. Write a short note on ultrasonic flow meters?

2. What is wake survey? Explain its significances.

3. Explain about turbulence factor and its importance.

4. How running time is calculated in supersonic wind tunnel?

5. Explain how wall shear stress is used in the estimation of Cd?

6. Explain the heating requirements in hypersonic wind tunnels.

7. Write a short note on pressure transducers and rotameters.

8. Explain how the test section average velocity is estimated using traversing rakes.

9. What is the Pitot - static tube correction for subsonic and supersonic Mach numbers?

10. Explain the preliminary estimation of nozzle area ratios and mass flow for a given test section size and Mach number.

PART B

Answer one full question from each module,


Module – 1

11. Explain in detail, how the energy ratio and power required is estimated in a low speed wind

tunnel. (14)

AERONAUTICAL ENGINEERING12. Explain in detail, the storage tank requirements of supersonic wind tunnel. (14)

Module – 2

13. Explain the procedure of obtaining CL and CD on aerofoil from the pressure distribution

obtained from wind tunnel testing. (14)

14. Write down spanwise load distribution for different taper ratios of wings and its estimation.

(14)

Module – 3

15. Discuss the Mach number estimation in test section by pressure measurement.(14 marks)

16. Explain starting problem and starting loads in high speed wind tunnel. (14)

Module – 4

17. Explain in detail, the use of hot wire anemometer and laser Doppler anemometer for turbulence

and velocity measurements. (14)

18. Discuss in detail, the use of the thermocouples and laser pyrometers for measurement of static and total temperatures. (14)

Module – 5

19. Explain about the Hele-Shaw apparatus and Interferometer flow visualization techniques. (14)

20. Explain about the Schlieren system and Shadowgraph flow visualization techniques. (14)

AERONAUTICAL ENGINEERINGSyllabus

Module 1 Subsonic and supersonic wind tunnel:- Low speed wind tunnels - Estimation of energy ratio and power required supersonic wind tunnels - Calculation of running time and storage tank requirements – Shock tunnel. Module 2 Pressure and velocity distributions:- Estimation of flow angularity and turbulence factor - Calculation of CL and CD on aero foils from pressure distribution - CD from wake survey - Test section average velocity using traversing rakes - Span wise load distribution for different taper ratios of wing. Module 3 Pressure, velocity and temperature measurements: - Mach number estimation in test section by pressure measurement and using a wedge - Hot wire anemometer and laser Doppler anemometer for turbulence and velocity measurements - Use of thermocouples and pyrometers for measurement of static and total temperatures - Use of pressure transducers, Rotameters and ultrasonic flow meters. Module 4 Boundary layer effects and heating problems: - Pitot-static tube correction for subsonic and supersonic Mach numbers - Boundary layer effects -Velocity profile on a flat plate by momentum-integral method - Calculation of CD from wall shear stress - Heating requirements in hypersonic wind tunnels - Re-entry problems. Module 5 Principles of Flow Visualization – Hele-Shaw apparatus - Interferometer – Fringe-Displacement method – Schlieren system – Shadowgraph. Text Books: 1. Pope. A and Goin. L, “High speed wind tunnel testing”, John Wiley, 1985

2. Rae W.H and Pope. A, “Low speed wind tunnel testing”, John Wiley Publication, 1984

3. Rathakrishnan. E, “Instrumentation, Measurement and Experiments in Fluids”, CRC Press, London,

2007

References Books: 1. Bradsaw, Experimental Fluid Mechanics, Pergamon, Oxford, 1970

2. Edward R. C. Miles, Supersonic Aerodynamics, Dover, New York, 1950

3. Lecture course on Advanced Flow Diagnostic Techniques 17-19 September 2008 NAL, Bangalore.

AERONAUTICAL ENGINEERING Course Contents and Lecture Schedule

No Topic No. of Lectures 1 Module 1 – SUBSONIC AND SUPERSONIC WINDTUNNEL

1.1 Low speed wind tunnels 2 1.2 Estimation of energy ratio and power required supersonic wind tunnels 2 1.3 Calculation of running time and storage tank requirements 2 1.4 Shock tunnel 1 2 Module 2 – PRESSURE AND VELOCITY DISTRIBUTIONS

2.1 Estimation of flow angularity and turbulence factor 2 2.2 Calculation of CL and CD on aero foils from pressure distribution 2 2.3 CD from wake survey 2 2.4 Test section average velocity using traversing rakes 2 2.5 Span wise load distribution for different taper ratios of wing. 2 3 Module 3 - PRESSURE, VELOCITY AND TEMPERATURE MEASUREMENTS

3.1 Mach number estimation in test section by pressure measurement and using a wedge 3

3.2 Hot wire anemometer and laser Doppler anemometer for turbulence and velocity measurements 2

3.3 Use of thermocouples and pyrometers for measurement of static and total temperatures 2

3.4 Use of pressure transducers, Rotameters and ultrasonic flow meters. 3 4 Module 4 - BOUNDARY LAYER EFFECTS AND HEATING PROBLEMS

4.1 Pitot-static tube correction for subsonic and supersonic Mach numbers 3

4.2 Boundary layer effects -Velocity profile on a flat plate by momentum-integral method

3

4.3 Calculation of CD from wall shear stress 2 4.4 Heating requirements in hypersonic wind tunnels - Re-entry problems. 2 5 Module 5-FLOW VISUALIZATION METHODS

5.1 Principles of Flow Visualization: Hele-Shaw apparatus, 2 5.2 Interferometer, Fringe-Displacement method 3 5.3 Schlieren system, Shadowgraph. 3

AERONAUTICAL ENGINEERINGAOT384 ROCKET PROPULSION

CATEGORY L T P CREDIT PCC 3 1 0 4

Preamble: The course is meant to give the learners an introduction to high speed aerodynamics Prerequisite: Course Outcomes:After the completion of the course the student will be able to CO 1 Understand the basic concepts of operating characteristics of rockets and able to solve

basic problems CO 2 Understand the basic concepts and operating characteristics of solid propellant rocket

motor and able to solve basic problems CO 3 Understand the basic concepts and operating characteristics of liquid propulsion system

and able to solve basic problems CO 4 Understand the basic concepts and operating characteristics of hybrid rockets and different

kind of nozzles applied to rocket propulsion and able to solve basic problems CO 5 Understand the basic concepts of other than chemical rockets. Mapping of course outcomes with program outcomes PO


10 PO 11

PO 12

CO 1 2 2 CO 2 3 3 1 CO 3 3 3 1 CO 4 3 2 1 CO 5 3 Assessment Pattern Bloom’s Category Continuous Assessment Tests End Semester Examination

1 2 Remember 10 10 10 Understand 20 20 20 Apply 20 20 70 Analyse Evaluate Create Mark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours

AERONAUTICAL ENGINEERINGContinuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions Course Outcome 1 (CO1): 1. Derive an expression for coefficient of thrust? 2. Derive an expression for characteristic velocity, effective exhaust velocity and jet velocity? 3. Discuss the effect of molecular weight of jet velocity? Course Outcome 2 (CO2): 1. How the particle sizes affect the burning rate? 2. Discuss the effect of chamber pressure on burning rate? 3. Discuss the how a desired thrust program can be achieved by desired thrust program? Course Outcome 3 (CO3): 1. What are the different types of cooling system adopted for liquid propulsion system? Explain? 2. Explain the different types of injectors? 3. Explain the function of turbo pump feed system? Course Outcome 4 (CO4): 1. Is the regenerative cooling systems adaptable in a hybrid rocket explain? 2. Explain the working of an inverse hybrid rockets? 3. Why the conical nozzles are not suitable for liquid engine explain? Course Outcome 5 (CO5): 1. Explain the working of a fission rocket engine. 2. Explain the working of electrical propulsion system 3. Explain how the solar energy can be used for propulsion?


QP CODE: Reg No: -------------------------- APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY SIXTH SEMESTER B.TECH DEGREE EXAMINATION

MONTH & YEAR

Course Code: AOT384

ROCKET PROPULSION Max.Marks:100 Duration: 3 Hours

PART A


1. Write thrust equation, explain the effect of trust with altitude according to this

equation?

2. What is specific impulse and deduce total impulse?

3. Explain what is progressive regressive and neutral burning propellant grain?

4. Write the demerits of solid propellants?

5. Explain what is regenerative cooling system in liquid engines?

6. Explain why a high pressure injection system is needed for injection of fuel and oxidizer?

7. Explain why the conical nozzles are suitable for solid booster?

8. Explain the effect of particle size in burning rate and how the desired thrust program is obtained different particle size?

9. Why the solar rockets important for space propulsion?

10. What are the different sources of nuclear energy used for rocket propulsion?

PART B


Module 1

11. A rocket engine develops a thrust of 9KN while consuming 3.5kg/sec of propellants having an energy content of 20MJ/kg. When the vehicle velocity is 400m/sec, determine specific impulse, specific propellant consumption, effective exhaust velocity, thrust power, and overall efficiency (14) 12. a) Derive an expression for coefficient of thrust and mass flow coefficient? (8)

AERONAUTICAL ENGINEERING b) Derive an expression for internal efficiency, propulsive efficiency and overall efficiency

(6)

Module 2

13. The characteristics of a propellant with a mass flow rate of 0.25kg/sec for a gas generator are as follows. Burn rate at 7MPa = 4mm/sec, Burning time = 120sec, Chamber pressure = 5MPa, Pressure exponent = 0.5, Propellant specific gravity = 1.65.Determine the size of an end burning cylindrical grain nozzle (14) 14. Explain the working of a solid propellant rocket motor with suitable sketch? What are the different types of ignition system used in solid propellants explain with sketches

(14)

Module 3

15. Sketch and explain a bi-propellant liquid propulsion system? (7) 16. a) Sketch and explain the working of a turbo pump feed system (8) b) Sketch and explain different types of ignition system used in liquid engines (7)

Module 4

17.A convergent divergent nozzle of area ratio of 3.5 is expanded to an atmosphere of 1bar

288K. Find the total pressure, temperature, density, exit Mach number, jet velocity, throat

static pressure, temperature and velocity of air at throat for optimum expansion

(14)

18. a) Sketch and explain the working of a hybrid rockets (8) b) Explain the contour nozzles are suitable for liquid engines? What are the problems associated with contour nozzles in a solid propellant rockets (6)

Module 5

19 Sketch and explain the working of fission and fusion nuclear rockets? (14)

20. Sketch and explain working of electric propulsion system (14)


Module 1

Fundamentals of rockets, basic principles and thrust equation, specific impulse, total impulse, exhaust velocity, characteristic velocity, thrust coefficient and mass flow coefficient, design parameters for rocket engine, energy flow and efficiencies, (Basic numerical calculations) Module 2

Solid propellant rocket motor:- General features, solid propellants, double bas propellant, composite propellant, desirable properties and its demerits, combustion of solid propellant, burning rate, regressive, neutral and progressive, restricted and unrestricted burning, ignition. (Basic numerical calculations). Module 3

Liquid propellant rocket engines:-. Comparison with other propulsion system, disadvantages of liquid engines, liquid propellants, monopropellant, bi-propellant, selection of bi-propellant combination, pressure and turbo pump feed system, ignition of propellants, cooling system, regenerate cooling. Module 4

Hybrid rocket engines, inverse hybrid rocket engines, comparisons and its limitations, types of nozzles used for rocket application, effect of back pressure on nozzles, over expanded under expanded and optimum expanded nozzles, effect of altitude on nozzle performance. (Basic numerical calculations). Module 5

Other non-air breath propulsion systems:- Nuclear rockets, electric rocket engines, electro thermal propulsion, electrostatic propulsion, solar thermal rocket, solar sail. Text Books

1. George P Sutton,Rocket Propulsion Elements”



1. S M Yahya, Gas Tables for Compressible Flow Calculations, New Age International Publishing, 201

Reference Books

1. Hill and Peterson, Non Air Breath Propulsion

2. P Balachandran , Modern Compressible flow”

AERONAUTICAL ENGINEERINGCourse Contents and Lecture Schedule

No Module No. of Lectures 1 Module1 1.1 Fundamentals of rockets, basic principles and thrust equation,

specific impulse, total impulse, exhaust velocity, 2

1.2 characteristic velocity, thrust coefficient and mass flow coefficient, 3 1.3 design parameters for rocket engine, energy flow and efficiencies, 3 2 Module2 2.1 Solid propellant rocket motor:- General features, solid

propellants, double bas propellant, composite propellant, 3

2.2 desirable properties and its demerits, combustion of solid propellant, burning rate,

3

2.3 regressive, neutral and progressive, restricted and unrestricted burning, ignition

3

3 Module 3 3.1 Liquid propellant rocket engines:-. Comparison with other

propulsion system, disadvantages of liquid engines, 3

3.2 liquid propellants, monopropellant, bi-propellant, selection of bi-propellant combination,

4

3.3 Pressure feed system and turbo pump feed system, ignition of propellants, cooling system, regenerate cooling.

4

4 Module4 4.2 types of nozzles used for rocket application, effect of back pressure

on nozzles, 4

4.3 over expanded under expanded and optimum expanded nozzles, effect of altitude on nozzle performance

4

5 Module5 5.1 Other non-air breath propulsion systems:- Nuclear rockets,

electric rocket engines, 3

5.2 electro thermal propulsion, electrostatic propulsion, 3 5.3 solar thermal rocket, solar sail, plasma propulsion 3

AERONAUTICAL ENGINEERINGAOT386 STRUCTURAL DYNAMICS AND AEROELASTICITY


Preamble: Basic aim of this course is to study the dynamic behaviour of different structural components and the interaction of aerodynamic, elastic and inertia forces. Prerequisite: Engineering Mechanics, Strength of Materials, Aircraft Structures and Flight Mechanics. Course Outcomes:After the completion of the course the student will be able to CO 1 Understand the concepts of structural dynamics CO 2 Determine the natural frequency for free and forced vibration CO 3 Understand the vibrational concepts of several degrees of freedom systems CO 4 Apply the approximate methods to find the natural frequency CO 5 Understand the concepts of aeroelasticity Mapping of course outcomes with program outcomes PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO

10 PO 11

PO 12

CO 1 3 2 1 - - - - - - - - - CO 2 3 2 1 - - - - - - - - - CO 3 3 2 1 - - - - - - - - - CO 4 3 2 1 - - - - - - - - - CO 5 3 2 1 - - - - - - - - - Assessment Pattern Bloom’s Category Continuous Assessment Tests End Semester Examination

1 2 Remember Understand 25 25 60 Apply 25 25 40 Analyse Evaluate Create Mark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks

AERONAUTICAL ENGINEERING End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions Course Outcome 1 (CO1): 1. What is resonance? 2. Define simple harmonic motion. 3. Define D' Alembert's principle. Course Outcome 2 (CO2): 1. Differentiate simple and compound pendulum. 2. Write the equation of motion for free and forced vibration. 3. Draw and explain the multi degrees of freedom system. Course Outcome 3(CO3): 1. What are the principle modes of vibration? 2. Define Orthogonality principle. 3. Write short note on influence coefficients. Course Outcome 4 (CO4): 1. Derive the equation of motion for longitudinal vibration of bars. 2. Differentiate between boundary and initial conditions. 3. Define Rayleigh’s principle? Course Outcome 5 (CO5): 1. Describe the different types of flutter? 2. How to prevent the aero elastic instabilities? 3. What is aileron control reversal?


QP CODE: Reg No: _______________


SIXTH SEMESTER B.TECH DEGREE EXAMINATION, MONTH & YEAR Course Code: AOT386

STRUCTURAL DYNAMICS AND AEROELASTICITY Max. Marks: 100 Duration: 3 hours

PART A



1. What is simple harmonic motion?

2. Explain the term natural frequency.

3. What is an Eigen value problems?

4. Differentiate between free and forced vibration.

5. Define normal modes of vibration.

6. What are the influence coefficients?

7. State the equation of motion for longitudinal vibration of bar.

8. Write short note on Dunkerley's method.

9. When the wing is said to be torsionally divergence?

10. What is critical aileron-reversal speed?

PART B

Answer one full question from each module (Each question carries 14 marks)

Module – 1

11. (i) Find the natural frequency of the system shown in figure. Take k = 2x105 N/m and m = 20 kg. (10)


(ii) Explain the parts of a vibration system with neat diagram. (4)

12. (i) Derive the equation of motion for single spring-mass system in vertical position using Newton’s method. (8)

(ii) Explain single, two and multi degree of freedom systems with neat diagram. (6)

Module – 2

13. A thin semi-circular cylinder of radius r and mass m slides on the horizontal surface without slipping. Determine the natural frequency by Rayleigh’s method. (14)

14. Find the natural frequency of the system shown by Energy method. (14)

Module – 3

15. Find the fundamental natural frequency and the corresponding mode shape for the system shown for k1 = k2 = k3 and m1 = m2 = m3. (14)


16. Derive the equation of motion for n degree of freedom system using Orthogonality principle.

(14)

Module – 4

17. Determine the normal functions in transverse vibration for a simply supported beam of length l and uniform cross section. (14)

18. Find the natural frequency of the following system by using Stodola’s method. Take E = 1.96x1011 and I = 4x10-7. (14)

Module – 5

19. Derive an expression for the aileron control reversal speed for a 2-D wing with aileron attached. (14)

20. Using Collar’s triangle, explain various aeroelastic phenomena in detail. (14)


Module 1

INTRODUCTION – Newton’s Law of Motion – Generalised Coordinates – Kinetic Energy – Potential Energy – Degree of Freedom System – Lagrange’s Equation of Motion – Simple Harmonic Motion – D’ Alembert’s Principle – Mechanical System – Spring Combinations Module 2

PRINCIPLES OF DYNAMICS – Free and Forced Vibrations of the System with Single Degree of Freedom – Simple and Compound Pendulum – Support Excitation Module 3

MODES OF VIBRATION – Principle Modes – Principle Coordinates – Equation of Motion for Two and Multi Degrees of Freedom Systems – Orthogonality Condition – Influence Coefficients – Eigen Value Problems Module 4

APPROXIMATE METHODS – Rayleigh’s Method – Stodola Method – Matrix Iteration Method – Dunkerley’s Method – Longitudinal, Lateral and Torsional Vibrations. Module 5

AEROELASTICITY – Aero Elasticity Concepts – Collar’s Triangle – Aeroelastic Instabilities – Wing Divergence – Aileron Reversal – Flutter Text Books

1. Bruce K Donaldson, “Introduction to Structural Dynamics”, Cambridge University Press, New York, 2006.

2. V P Singh, “Mechanical Vibrations”, Dhanpat Rai & Co (P) Ltd 3. Tse. F.S., Morse, I.F., Hinkle, R.T., “Mechanical Vibrations”, – Prentice Hall, New York, 1984. 4. Fung Y.C., “An Introduction to the Theory of Aeroelasticity” – John Wiley & Sons, New York,

1995.

Reference Books

1. Timoshenko S., “Vibration Problems in Engineering”– John Wiley and Sons, New York, 1993. 2. Bisplinghoff R.L., Ashley H and Hoffman R.L., “Aeroelasticity” – Addision Wesley Publication,

New York, 1983. 3. Thomson W T, “Theory of Vibration with Application” - CBS Publishers, 1990.

AERONAUTICAL ENGINEERINGCourse Contents and Lecture Schedule

No Topic No. of Lectures 1 Module 1 -INTRODUCTION

1.1 Newton’s Law of Motion – Generalised Coordinates 1 1.2 Kinetic Energy – Potential Energy 1 1.3 Degree of Freedom System 1 1.4 Lagrange’s Equation of Motion 1 1.5 Simple Harmonic Motion – Mechanical System 2 1.6 D’ Alembert’s Principle 1 1.7 Spring Combinations 1

2 Module 2 - PRINCIPLES OF DYNAMICS

2.1 Free Vibration of the System with Single Degree of Freedom 4 2.2 Forced Vibration of the System with Single Degree of Freedom 4 2.3 Simple and Compound Pendulum 2 2.4 Support Excitation 2

3 Module 3 - MODES OF VIBRATION

3.1 Principle Modes – Principle Coordinates 1 3.2 Equation of Motion for Two Degrees of Freedom Systems 2 3.3 Equation of Motion for Multi Degrees of Freedom Systems 2 3.4 Orthogonality Condition – Influence Coefficients 1 3.5 Eigen Value Problems 2

4 Module 4 - APPROXIMATE METHODS

4.1 Rayleigh’s Method 1 4.2 Stodola Method 1 4.3 Matrix Iteration Method 1 4.4 Dunkerley’s Method 1 4.5 Longitudinal Vibration 2 4.6 Lateral Vibration 2 4.7 Torsional Vibration 2

5 Module 5 - AEROELASTICITY

5.1 Aero Elasticity Concepts 1 5.2 Collar’s Triangle 1 5.3 Aero Elastic Instabilities 1 5.4 Wing Divergence 1 5.5 Aileron Reversal 2 5.6 Flutter 1


SEMESTER VI HONOURS

AERONAUTICAL ENGINEERINGAOT394

RAREFIED GAS DYNAMICS AND INTERPLANETARY SPACE TRAVEL


Preamble: The course is meant to give the learners an introduction to high speed aerodynamics. Prerequisite: Course Outcomes: After the completion of the course the student will be able to CO 1 Explain and use basic theorems and effect of low density on re-entry vehicles. CO 2 Understand the concepts of kinetic theory and fluid behaviour in microscopic level. CO 3 Able to determine different types of orbit and able to solve complex problems. CO 4 Apply the theories and positioning the objects it trajectory and transfer orbits, able to solve

complex problems. CO 5 Apply the concepts orbital maneuverer and design the interplanetary trajectories and able

to solve complex problems. Mapping of course outcomes with program outcomes PO


10 PO 11

PO 12

CO 1 2 CO 2 3 3 1 1 CO 3 3 3 2 1 CO 4 3 3 2 1 CO 5 3 3 2 Assessment Pattern Bloom’s Category Continuous Assessment Tests End Semester Examination

1 2 Remember 10 10 10 Understand 20 20 20 Apply 20 20 70 Analyse Evaluate Create Mark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks

AERONAUTICAL ENGINEERINGAssignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions Course Outcome 1 (CO1): 1. Derive Euler equation for a three dimensional Flow field and derive Bernoulli equation. .

2. Explain Barotropic flow, Kelvin’s theorem, streamline, irrotational flows .

3. Explain Green’s lemma, Circulation and Vorticity, Stoke’s theorem.

Course Outcome 2 (CO2): 1. Derive mathematical expression for stream function, potential function and equipotential line.

2. Trace stream lines and equipotential lines of the effective body for the combination of a source

and a sink equal strength in a free stream.

3. Prove that the stream function and equipotential lines are orthogonal to each other.

Course Outcome 3(CO3): 1. Find the complex velocity of a line source?

2. Transform a circular cylinder in to a flat plate at an angle of attack α?

3. Write notes on Modified Joukowski’s transformation .

Course Outcome 4 (CO4): 1. Demonstrate Biot and Savert law, bound vortex and trailing vortex, horse shoe vortex.

2. Derive an expression for Cl, Cd according to thin aerofoil theory?.

3. An airplane having an elliptical wing all up weight is 100000N, span 20m, having a wing area

50cm2 flying at an altitude of where the density ratio 0.6 at a speed of 360Km/hr. If the lift drag ratio

is 10, estimate the parasite drag coefficient of the airplane?

Course Outcome 5 (CO5): 1. Derive an expression for thrust produced by a propeller disc according to momentum theory.

2. An airscrew is required to produce a thrust of 4000 N at a flight speed of 120m/s at sea level. If

the diameter is 2.5 m, estimate the minimum power that must be supplied on the basis of Froude’s

AERONAUTICAL ENGINEERINGtheory

3. Explain the characteristics of turbulent flow.


QP CODE: Reg No: -------------------------- APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY SIXTH SEMESTER B.TECH DEGREE EXAMINATION

MONTH & YEAR

Course Code: AOT394

RAREFIED GAS DYNAMICS AND INTERPLANETARY SPACE TRAVEL

Duration: 3 Hours Max.Marks:100

PART A



1. Explain KnudsenNo and what is its significance?

2. Why the shock wave do not exist at very low temperature flows?

3. Explain how the counting of number of microstates for a given macro state?

4. Sketch and explain the microstate?

5. Explain the orbital elements?

6. Derive an expression for Lagrange cofficients?

7. Explain briefly why Hohmann transfer is the energy efficient transfer?

8. At what condition the bi-elliptical transfer is preferred?

9. Derive an expression for velocity change for interplanetary transfer?

10. Explain the condition for sphere of influence?

PART B



Module 1

11. Derive Rayleigh relation for shock wave (14)

12. A normal shock wave moves into a still air at 800m/s. The air ahead of the shockwave

AERONAUTICAL ENGINEERINGare at 101325 Pa, 288K. Find the velocity of the air after passage of the shockwave?

(14)

Module 2

13. Derive an expression for perfect gas equation of state, collision frequency and mean freepath according to kinetic theory of gasses?

(14)

14. Derive an expression for entropy of a chemically reacting gas in terms of Boltzmann’sconstant and partition function (14)

Module 3

15. An earth’s satellite moves in the x-y plane of an inertial frame with origin at the earth’scenter. Relative to the frame, the position and velocity of the satellite at time t0 arer0 =8182.4i – 6865.9j (km), v0 = 0.47572i+8.8116j (km/s). Calculate the position and velocityvector after the satellite has travelled through a true anomaly of 120deg?

(14)

16. A geocentric trajectory has a perigee velocity of 15km/s and a perigee altitude of 300km.Find the radius when the true anomaly is 100 deg and the position and speed three hours later

(14) Module 4

17. A space craft is in a 480km by 800km earth orbit. Find the increment in velocity required at perigee to place a space craft in a 480km 16000km transfer orbit and the change in velocity required to establish a circular orbit of 16000km

(14) 18. a) With a single v-delta maneuver the earth orbit of a satellite is to be changed from a circle of

radius 15000km to a coplanar ellipse with perigee altitude of 500km and apogee radius of22000km. calculate the magnitude of v-delta and change in flight path angle?

(8) b) Derive an expression for the change in velocity required for bi-elliptic Hohmann transfer?

(6)

Module 5

19. Calculate the minimum wait time for initiating a return trip from Mars to earth. The semi majoraxis of earth =149*106 km, semi major axis of Mars =227.9*106 km and gravitational parameter ofsun is 132.71*1011 km3/sec2 (14)

20. Estimate the v-delta required for a Hohmann transfer from earth to Mercury, assuming a150km circular parking orbit at earth and a 150km circular capture orbit at Mercury.Furthermore, assume that the planets have coplanar circular orbits with radii equal to the semimajor axis are semi major axis of earth =149*106 km, semi major axis of Mercury =57.91*106 (14)


Module 1

Governing Equations, non-dimensional parameter, Shock Waves, Unsteady 1-D flow Governing equations, speed of sound Review of shock relations, Rankine-Hugoniot and Rayleigh relations for shock waves Shock Interaction: Regular vs. Irregular reflections, Hysteresis Phenomenon Moving normal shock Small perturbation approximation, Wave equation, Riemann invariants Unsteady waves interactions Module 2

Basics kinetic theory Molecular Model Micro and Macroscopic Properties Binary Collisions Kinematics Dynamics and post-collision properties Molecular force field models Statistical Gas Properties Position and Velocity Distribution Functions Boltzmann Equation and Maxwellian Distribution Function Module 3

Fundamental concepts of orbital mechanics, different types of orbits and trajectories orbital elements, Perifocal frame, Lagrange coefficients and points, coordinate transformation, transformation between geocentric equatorial and Perifocal frames, earths oblateness,(Numerical problems) Module 4

Orbital position as function of time – Elliptical, Parabolic and hyperbolic trajectories, Gibbs method of orbit determination from three position vector, Lamberts problem, orbit determination, Orbit determination by Gauss’s method, Orbital manoeuvres :- Hohmann Transfer and non Hohmann transfer, Chase and phasing maneuverer ,(Numerical problems) Module 5

Inter planetary trajectories:- Interplanetary Hohmann transfers, rendezvous opportunities, sphere of influence, method of patched conic section, planetary departure, planetary rendezvous, planetary flyby, non-Hohmann interplanetary trajectories, (Numerical problems) Text Books

1. W. W. Liou and Y. Fang, Micro fluid Mechanics, McGraw-Hill, New York, 2005.


3. J W Cornelisse, H F R Schoyer, K F Wakker Rocket Propulsion and Spaceflight dynamics


1. Rathakrishnan E, Gas Tables, Orient Blackswan Private Limited - New Delhi (2013)

2. S M Yahya, Gas Tables for Compressible Flow Calculations, New Age International

Publishing, 2011

AERONAUTICAL ENGINEERINGReference Books

1. Lecture notes of Prof.J B Young on “Molecular Thermodynamics”, Cambridge University Press.

2. The DSMC Method,G.A.Bird, Create Space publisher,1stedition,2013, ISBN/EAN13: 1492112909/9781492112907.

3. Bate R R, Muller D, and White J E, Fundamentals of Astrodynamics. 4. Bond V R and Allman M C Modern Astrodynamics Fundamentals and Perturbation

method. 5. Boulet D L Method of Orbit Determination for microcomputer.


No Module No. of Lectures 1 Module1 1.1 Governing Equations, non-dimensional parameter, Shock Waves,

Unsteady 1-D flow Governing equations, speed of sound Review of shock relations, ,

3

1.2 Rankine-Hugoniot and Rayleigh relations for shock waves Shock Interaction: Regular vs. Irregular reflections

3

1.3 Hysteresis Phenomenon Moving normal shock Small perturbation approximation, Wave equation, Riemann invariants Unsteady waves interactions

4

2 Module 2 2.1 Basics kinetic theory Molecular Model Micro and Macroscopic

Properties Binary Collisions 3

2.2 Kinematics Dynamics and post-collision properties Molecular force field models Statistical Gas Properties

3

2.3 Stage Position and Velocity Distribution Functions Boltzmann Equation and Maxwellian Distribution Function

3

3 Module 3 3.1 Fundamental concepts of orbital mechanics, different types of orbits

and trajectories orbital elements, 3

3.2 Perifocal frame, Lagrange coefficients and points, coordinate transformation,

3

3.3 transformation between geocentric equatorial and Perifocal frames, earths oblateness,(Numerical problems)

4

4 Module 4 4.2 Lamberts problem, orbit determination, Orbit determination by

Gauss’s method, Orbital maneuvers:- Hohmann Transfer and non Hohmann transfer,

4

4.3 Chase and phasing maneuverer ,(Numerical problems) 3 5 Module 5 5.1 Inter planetary trajectories:- Interplanetary Hohmann transfers,

rendezvous opportunities, 3

5.2 sphere of influence, method of patched conic section, planetary departure, planetary rendezvous, planetary flyby,

3

5.3 non-Hohmann interplanetary trajectories, (Numerical problems) 3

AERONAUTICAL ENGINEERINGAOT396 ADVANCED PROPULSION SYSTEMS


Preamble: The course is meant to give the students a deep knowledge in propulsion. Prerequisite: Nil Course Outcomes: After the completion of the course the student will be able to CO 1 Recall the fundamentals and introduction to hypersonic flows. CO 2 Deep knowledge in scramjet. CO 3 Study about different types of electric thrusters. CO 4 Better understanding of nuclear powered engines. CO 5 Application of micropropulsion systems. Mapping of course outcomes with program outcomes PO


10 PO 11

PO 12

CO 1 3 2 1 CO 2 3 2 1 CO 3 3 2 1 CO 4 3 2 1 CO 5 3 2 1 Assessment Pattern Bloom’s Category Continuous Assessment Tests End Semester Examination

1 2 Remember 10 10 10 Understand 20 20 20 Apply 20 20 70 Analyse Evaluate Create Mark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks

AERONAUTICAL ENGINEERINGEnd Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions Course Outcome 1 (CO1):

1. Why do many aircrafts operate at an altitude around 36,000 feet? 2. A ramjet has a constant diameter combustion chamber followed by a nozzle whose throat

diameter is 0.94 times the chamber diameter. Air enters the combustion chamber with T0 = 1450K and M = 0.3. How high may the temperature rise in the combustion chamber without necessarily changing the chamber inlet conditions? For simplicity, negelect frictional losses in the chamber and nozzles and assume that the working fluid has specific heat ratio γ =1.333.

3. What are thermally and chemically equilibrium and frozen flows? Course Outcome 2 (CO2)

1. Briefly explain Scramjet propulsion. Explain the formation of thermal throat in a scram jet engine.

2. Explain the role of scramjet engine in space plane applications. Also explain the current problems in hypersonic scramjet engine.

3. Enumerate the hypersonic scramjet engine methods of analysis. Course Outcome 3(CO3):

1. Explain working principle of geometries of Hall thrusters with neat sketch and its advantages and disadvantages?

2. Nitrogen is heated in an arcjet from 300 to 7350 K at 1 atm and dissociates almost entirely to atomic nitrogen. One third of the electrical power supplied is loss to the arc chamber walls. The heated N then expands in a nozzle of area ratio A/A* =100 to vacuum. Assuming frozen flow and negligible effects of friction and heat transfer, estimate the specific impulse and the thrust- to power ratio. Take γ = 5/3.

3. Applications of electrical propulsion in space missions. Course Outcome 4 (CO4):

1. Explain the operation of a nuclear fission propulsion system and the problems associated with the design of such engine.

2. Write short notes of the following: (i) Calculating criticality of a nuclear fission reactor (ii)Operating principle of LACE.

3. What is the use of Reflector in nuclear fission rocket?

AERONAUTICAL ENGINEERINGCourse Outcome 5 (CO5):

1. What are the components of chemical Micropropulsion systems? 2. Comment on the topic, Micropropulsion systems used for cuestas and small satellites. 3. Explain MEMS based fluid handling system for electric propulsion.


QP CODE: Reg No: --------------------------


MONTH & YEAR Course Code: AOT396

ADVANCED PROPULSION SYSTEMS Duration: 3 Hours Max.Marks:100

PART A


1. What is propellant less propulsion?

2. Schematic of a pulsed plasma thruster.

3. Does combustion instabilities occur in SCRAMJET?

4. State the advantages of scramjet engines in military and civil applications.

5. Why micro propulsion is nowadays been used in nanosatellites?

6. What are the advantages of electrical propulsion engines (thrusters) over chemical rocket engines?

7. A rocket takes off from Earth and reaches a speed of 100m/s in 10.0 s. If the exhaust speed is 1500 m/s and the mass of fuel burned is 100 kg, what was the initial mass of the rocket?

8. Explain why ram jets are not self-started?

9. Explain the re-entry body design considerations.

10. The downstream Mach number, in the case of an oblique shock may or may not be less than unity. Explain the statement.

PART B


Module 1

11. A supersonic flow initially at Mach number 2 and with static properties of 0.98 bar and 370 K is expanded around a 100 sharp corner. Find the downstream Mach number and downstream properties. Also, construct a schematic of the expansion fan.

AERONAUTICAL ENGINEERING (14) 12. A ramjet is flying at Mach 1.818 at an altitude 16.750 km altitude (Pa = 9.122 kPa, Ta= - 56.50 C = 216.5 K., sonic speed, a = 295 m/s). The flow is assumed to enter the intake of the ramjet through a normal shock standing at the intake face. No pre-entry loss or friction loss inside the engine is assumed to exist. Combustion delivery temperature is 1280 K. and the fuel –air ratio is 1:40. The area at the intake face is A1 = 0.0929 m2 and at the Combustion chamber, A3 = 0.1858 m2 Calculate : i) Mass flow rate through the engine ii) Throat area in the nozzle, A5 iii) Combustion related pressure drop in the combustion chamber iv) If the nozzle expands only in a convergent nozzle – find the thrust produced v) Calculate the propulsive efficiencies for (iv) and (v) vi) Calculate TSFC in both the cases vii) If the nozzle expands to ambient pressure – find the thrust produced (14)

Module 2

13. A scramjet powered aircraft flys at Mach 5 at 16.75 km where Ta=216.67 K and Pa=9.122 kPa. The intake has a shock structure of two oblique shocks with both deflection angles δ =100. By burning hydrogen fuel (Q=120,900 kJ/kg), the temp is raised to 2000 K. The fuel air ratio =0.025. The nozzle expansion ratio is A5/A4 = 5.0. The inlet and the exit areas are A1=A5= 0.2 m2. If cp= 1.51 kJ/kg.K ; ηcc= 0.8 Calculate : i) Mach number at combustion chamber inlet ii) Exhaust jet velocity iii) Overall efficiency (14) 14. (a)Write short notes on the following: (i) Thermal Throat (ii) Function of Isolator in scramjet engine. (6) (b) Explain with neat diagrams hypersonic intakes and supersonic combustors. (8)

Module 3

15. a) Explain in detail the electrical propulsion systems and different types of electrical thrusters. (6)

b) An electrostatic rocket is to use heavy particles with charge-to-mass ratio of 500 C/Kg to produce a specific impulse of 3000 s. What acceleration voltage would be necessary? (8)

16. a) Write short notes on: (i) Application of Electric Propulsion (ii) Break through propulsion (8) b) With neat sketches briefly explain the working of plasma jet and resiojet rocket engines. (6)

Module 4

17. Explain in detail the nuclear thermal rocket engines. (14)

AERONAUTICAL ENGINEERING18. Write short notes on: (a) Nuclear fission (8) (b) Ensuring Sustainable Chain Reaction in Nuclear Propulsion (6)

Module 5

19.(a) Briefly explain Micropropulsion. (6) (b)Write short notes on the following: (i) Types of space tethers (ii) MEMS technology (8) 20. Explain in detail the chemical Micropropulsion thrusters. Syllabus

Module 1

Fundamental Working characteristics and its performance of turboprop, turbofan turbojet and ramjet engines – combined cycle engine: turbo-ramjet, Air turbo rocket- ejector ramjet: principles, operation- hypersonic flows: governing equations, hypersonic relations- hypersonic boundary layer theory- high temperature viscous flows and solution strategies- equilibrium and non-equilibrium flows- comparative study of shock wave through nozzles. Module 2

Hypersonic airbreathing engine performance - Scramjet propulsion - Thermodynamics Closed Cycle Analysis - Maximum Allowable Compression Temperature - Required Burner Entry Mach Number - First Law Analysis - Thermodynamics Process Assumptions - Thermodynamics Process Analyses - First Law Analysis Results - Stream Thrust Analysis - Compression Components - Typical Compression Components Configurations - Compression Components Analysis Overview - Influence of Boundary Layer Friction - Burner Entry Pressure - Leading-Edge Oblique Shock Wave Geometry. Scramjet performance numerical. Module 3

Introduction to electric propulsion - important equations- types of electric propulsion: resistojet, arc jet, Ion, Hall Effect, pulsed plasma (PPT) for micro-spacecraft, solar electric propulsion - Electrostatic thrusters - electromagnetic thrusters-electrospray propulsion-colloid thrusters - applications to space missions- Photon rocket, beamed energy propulsion, solar, magnetic sails. Module 4

Nuclear propulsion history, Power, thrust, energy. Nuclear fission- basics, sustainable chain reaction, neutron leakage, control, reflection, prompt and delayed neutrons, thermal stability. Principles and fuel elements. The nuclear thermal rocket engine, start-up and shutdown. Development status of nuclear engines, alternative reactor types, safety issues in nuclear propelled missions- nuclear technology in space.

Module 5

Micropropulsion- application of MEMS- chemical and electric propulsion: principle, thrusters,

AERONAUTICAL ENGINEERINGdescription – propellantless propulsion- Nanosatellites: Introduction, application of Micropropulsion in nanosatellites. Text Books

1. Rocket Propulsion Elements 8 th ed., G. P. Sutton and O. Biblarz, John Wiley & Sons, 2001

2. Hypersonic Air breathing Propulsion, by: Heiser, W.H., Pratt, D. T., AIAA Education Series, 1994, ISBN 978-1-56347-035-6.


1. Rathakrishnan E, Gas Tables, Orient Blackswan Private Limited - New Delhi (2013)

2. S M Yahya, Gas Tables for Compressible Flow Calculations, New Age International

Publishing, 2011

Reference Books

1. Element of Propulsion, Gas turbine and rockets, J. Mattingly, AIAA Education Series, 2006, ISBN-10: 1-56347-779-3

2. Mechanics and Thermodynamics of Propulsion, P. Hill and C.R. Peterson, Prentice Hall, 1991, ISBN: 0201146592”

3. Modern Compressible Flow with Historical Perspective, J. Anderson, McGrawHill, 2002, ISBN10: 0072424435.

4. Physics of Electric Propulsion, Robert Jahn, McGraw-Hill, 1968. Course Contents and Lecture Schedule

No Module No. of Lectures 1 Module1

1.1 Fundamental Working characteristics and its performance of turboprop, turbofan turbojet and ramjet engines.

3

1.2 Combined cycle engine: turbo-ramjet, Air turbo rocket- ejector ramjet, there operations and working.(Ramjet numerical)

3

1.3 Hypersonic flows: governing equations, hypersonic relations- hypersonic boundary layer theory- high temperature viscous flows and solution strategies- equilibrium flows: thermal, chemical, global and non-equilibrium flows-comparative study of shock waves through nozzles

4

2 Module 2 2.1 Principle of scramjet- Thermodynamics Closed Cycle Analysis -

Maximum Allowable Compression Temperature - Required Burner Entry Mach Number.

3

2.2 First Law Analysis - Thermodynamics Process Assumptions - Thermodynamics Process Analyses - First Law Analysis Results - Stream Thrust Analysis.

3

AERONAUTICAL ENGINEERING2.3 Compression Components - Typical Compression Components

Configurations - Influence of Boundary Layer Friction - Burner Entry Pressure - Leading-Edge Oblique Shock Wave Geometry. (Scramjet performance numerical).

4

3 Module 3 3.1 Introduction to electric propulsion - important equations. 3 3.2 Types of electric propulsion: resistojet, arcjet, Ion, hall effect, pulsed

plasma (PPT) for micro-spacecraft, solar electric propulsion - Electrostatic thrusters - electromagnetic thrusters-electrospray propulsion-colloid thrusters.

3

3.3 Applications to space missions- Photon rocket, beamed energy propulsion, solar, magnetic sails.

3

4 Module 4 4.2 Principles and fuel elements. The nuclear thermal rocket engine, start-

up and shutdown. 4

4.3 Development status of nuclear engines, alternative reactor types, safety issues in nuclear propelled missions- nuclear technology in space.

4

5 Module: 5 5.1 Micro propulsion- application of MEMS- chemical propulsion: solid

micro-thrusters, micro mono propellant thruster, micro bipropellant thrusters, cold gas thrusters- electric propulsion: micro ion thrusters, low power hall thruster.

4

5.2 Propellantless propulsion- Nano satellites: Introduction, application of micro propulsion in Nano satellites.

4

AERONAUTICAL ENGINEERING AOT 398

COMPUTATIONAL STRUCTURAL MECHANICS


VAC 3 1 0 4

Preamble: The primary focus of this course is on the teaching of state-of-the-art numerical methods for the analysis of the linear and nonlinear continuum response of materials. The range of material behaviour considered in this course includes: linear and finite deformation elasticity, inelasticity and dynamics. Numerical formulation and algorithms include: variational formulation and variational constitutive updates, finite element discretization, error estimation, time integration algorithms and convergence analysis Prerequisite: Nil Course Outcomes: After the completion of the course the student will be able to CO 1 Derive weak form of a differential equations. CO 2 Solve 1D structural problems using FEM. CO 3 Solve 2D & 3D elasticity problems using FEM. CO 4 Explain the formulation of isoparametric finite element models and implement in a

MATLAB program. CO 5 Solve dynamic problems using FEM and implement in a MATLAB program. Mapping of course outcomes with program outcomes PO 1 PO 2 PO 3 PO 4 PO 5 PO 6 PO 7 PO 8 PO 9 PO

10 PO 11

PO 12

CO 1 3 1 CO 2 3 3 CO 3 3 3 CO 4 3 2 1 2 1 CO 5 3 2 1 2 1 Assessment Pattern Bloom’s Category Continuous Assessment Tests End Semester Examination


AERONAUTICAL ENGINEERINGMark distribution Total Marks CIE ESE ESE Duration 150 50 100 3 hours Continuous Internal Evaluation Pattern: Attendance : 10 marks Continuous Assessment Test (2 numbers) : 25 marks Assignment/Quiz/Course project : 15 marks End Semester Examination Pattern: There will be two parts; Part A and Part B. Part A contain 10 questions with 2 questions from each module, having 3 marks for each question. Students should answer all questions. Part B contains 2 questions from each module of which student should answer any one. Each question can have maximum 2 sub-divisions and carry 14 marks. Course Level Assessment Questions Course Outcome 1 (CO1):

1. Explain strong and weak forms of a differential equation. 2. What are the strengths of finite element method? 3. Explain C0 and C1 continuity.


1. Explain shape function 2. What are the different types of elements in FEM.? 3. What are the differences between Euler Bernoulli beam and Timoshenko beam?


1. Explain the convergence requirements of FEM. 2. Explain patch test. 3. Write the differences between Kirchhoff and Mindlin plate elements


1. What are the modelling issues in FEM.? 2. Write the properties of rectangular elements 3. Explain volumetric locking


1. Explain nonlinear dynamic analysis. 2. Explain time stepping method. 3. Write a MATLAB programming to find natural frequency for a N degree of freedom system.


QP CODE: Reg No: --------------------------


MONTH & YEAR

Course Code: AOT398

COMPUTATIONAL STRUCTURAL MECHANICS


PART A



1. What are the different numerical methods?

2. Discuss the classification of beam theories.

3. Explain shape functions using examples.

4. Define Eigen value and Eigen vectors?

5. Write stress versus strain law for 2D elasticity.

6. Explain patch test.

7. Explain shear locking.

8. Write the features of isoparametric quadrilateral elements.

9. What is non-linear dynamic analysis?

10. Write different transient analysis numerical techniques.

PART B



Module 1

11. a) Derive differential equation to obtain displacements for an axially loaded elastic bar (7) b) Derive weak formulation for the above differential equation. (7)

12. Compare diffent types of numerical methods for solving ODE’s and PDE’s. (14)

Module 2

13. Derive shape function and stiffness matrix for 1D linear bar element. (14)

AERONAUTICAL ENGINEERING14. Explain the term Timoshenko Beam Theory and briefly explain the stiffness formulation for

such element. (14)

Module 3

15. Derive the equations of equilibrium in case of a three dimensional stress system. (14)

16. Explain the term mindlin’s C0 continuity plate elements and briefly explain stiffness matrix formulation for such elements. (14)

Module 4

17. Consider two dimensional elasticity problem with 4 node quadrilateral elements. Write a FE programme structure for pre-processing. (14)

18. a) What are the modelling issues in finite element modelling?

b) What is volumetric locking? c) Explain isoparametric quadrilateral elements?

Module 5

19. Derive the equilibrium equation for dynamic finite element analysis for linear system. (14) 20. Explain the solutions for non-linear dynamic analysis using explicit integration method and

implicit integration method. (14)

Syllabus

Module 1

Introduction to computer simulation techniques and numerical methods (Finite element method, Finite difference method and Finite volume method). Weighed residuals, Continuity conditions at interfaces, Functional, Variational operator, Weighted integral and weak formulation. Module 2

Finite-element method for 1D potential problems – shape functions, element stiffness matrix. Triangular elements. Assemblage of global stiffness matrix, boundary conditions, solutions. Euler-Bernoulli and Timoshenko beam elements. Module 3

Theory of elasticity – Stress versus strain laws, Boundary conditions. Finite elements for two- and three-dimensional elasticity. Kirchhoff and Mindlin plate elements. Finite element modelling and performance. Convergence requirements. Patch test. Module 4

Introduction to programming finite element analysis using MATLAB. Programming finite element stress analysis using MATLAB. Modelling issues in finite element method. Element quality for stress analysis, shear locking and volumetric locking. Rectangular elements. Introduction to Isoparametric representation & isoparametric quadrilateral elements.

AERONAUTICAL ENGINEERINGModule 5 Linear and nonlinear dynamic analysis. Model and transient analysis. Time stepping methods. Programming linear and non-linear dynamic analysis using MATLAB. Text Books

1. Logan, D. L. (2011), “A First Course in the Finite Element Method”, 5th edition

2. Cook, R. D., et. al, (2002), “Concepts and Applications of Finite Element Analysis”, Wiley, 4th

edition

Reference Books

1. Bathe, K. J. (1996), “Finite Element Procedures”, Prentice Hall.

2. Todd Young and Martin J. Mohlenkamp, Introduction to Numerical Methods and Matlab

Programming for Engineers, Department of Mathematics Ohio University Athens, OH 45701

3. Zienkiewicz, O.C. and Taylor, R.L. (2000), “The Finite Element Method”, Volumes 1&2, 5th

edition, Butterworth-Heinemann.


No Topic No. of Lectures 1 Module 1 Total: 9

1.1 Introduction to computer simulation techniques and numerical methods

2

1.2 Weighed residuals 1 1.3 Continuity conditions at interfaces 1 1.4 Functional, Variational operator 2 1.5 Weighted integral and weak formulation 3 2 Module 2 Total: 9

2.1 Finite-element method for 1D potential problems – shape functions, element stiffness matrix

2

2.2 Triangular elements. Assemblage of global stiffness matrix, boundary conditions, solutions.

3

2.3 Euler-Bernoulli beam elements. 2 2.4 Timoshenko beam elements 2 3 Module 3 Total: 9

3.1 Theory of elasticity – Stress versus strain laws, Boundary conditions. 2 3.2 Finite elements for two- and three-dimensional elasticity. 2 3.3 Kirchhoff and Mindlin plate elements. 3 3.4 Finite element modelling and performance. Convergence

requirements. Patch test. 2

4 Module 4 Total: 10 4.1 Introduction to programming finite element analysis using MATLAB. 3 4.2 Programming finite element stress analysis using MATLAB. 3

AERONAUTICAL ENGINEERING4.3 Modelling issues in finite element method. Element quality for stress

analysis, shear locking and volumetric locking 2

4.4 Rectangular elements. 1 4.5 Introduction to Isoparametric representation & isoparametric

quadrilateral elements. 1

5 Module 5 Total: 8 5.1 Linear and nonlinear dynamic analysis. 3 5.2 Model and transient analysis. Time stepping methods. 2 5.3 Programming linear and non-linear dynamic analysis using MATLAB. 3

semester v - ktu.edu.in

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