micro air vehicles seminar1

8/8/2019 Micro Air Vehicles Seminar1

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MICRO AIR VEHICLES

MOHAMED RINJU P M

ROLL NO:27209

WHAT ARE MAVS(QAV¶S)?

Multi functional, militarily capable, small flight

vehicles.

size should be less than15cms. Reynolds's no < 10^5.

For a Primarily intended and developed for

defence applications.

WHY MAV¶S? WHY NOT

SOMETHING BIGGER?

Keeps security personnel out of harms byproviding situational awareness right down toplatoon level.

Direct connectivity

Can be individually controlled

Can be used for a wide range of new

missions _ (even unthought-of before)

APPLICATIONS

Reconnaissance

Surveillance

Defence applications

Weather forecast

Wildlife study

&photography

Crowd control

Targeting

Border surveillance

Traffic monitoring

Tracking criminals &illegal activities

Biochemical sensing

inspection of pipes

OVER THE HILL

RECONNAISSANCE

MOTHER BIRD APPROACH

Tracking of chemicals

MAIN SUB SYSTEMS

1. FLIGHT CONTROL

2. PROPULSION SYSTEM

3. COMMUNICATION SYSTEM

4. GUIDANCE&NAVIGATION

MAV flight regime compared with

existing flight vehicles

FLIGHT

CONTROL&AERODYNAMICS

Reynolds's no:= inertia force/viscous force

Low Reynolds's no: flights may have lift to drag ratio of 5

to 10.

The best aspect ratios usually lie between 1&2

Angle of attack should be 5-12° for good endurance.

If angle of attack <5, low aerodynamic efficiency

Endurance=J/power requirement

For optimal endurance the mav should fly at7°

ACTIVE OR PASSIVE CONTROL

Use strategies using MEMS

Create &install tiny sensors

miniature actuators Flow character controlled by sensor arrays

Flexible membranes or micro flaps to affect

the flow as required Micro motors piezoelectric devices magneto

elastic ribbons

WING DESIGN AND

FABRICATION

Types of wings

wing shapes Composite materials,

Carbon fibres

carbon fibre-balsawood sandwitches are commonly used

Inflatable wing

Distend (fill) with air or gas

Application in UAV, military

To stow the wings

Can be launched from gun or aircraft

Advantages of aircrafts with

inflatable wings

Can be packed to 1/10 of original size

Low mass

Low power requirements High reusability

It can be steered, accelerated, anddecelerated in level flight.

High stability and control High lift and slow landing speed

Experiment on inflatable wing

Experiment conductedusing I 2000

It was launched from

800-1000 feet Inflatable wings comes

out in 1\3 sec

Successfully controlled

the launch,flight andlanding

Controlling of wing

by using piezoelectricby using piezoelectricmaterialmaterial

actuator can be quartz and substrate can be

aluminum or steel

inflatable wings has smooth surface so low

value of skin friction

I-2000 & X-24A

Both have inflatable

I-2000 is UAV

X-24A is manned

Disadvantages

They are not self powered

Cannot launch from ground

There are chances of air bag buckling

PROPULSION SYSTEM

Propulsion system alone consumes 90% of totalpower

Lithium alkaline batteries

IC engines Reciprocating chemical muscle

Lithium battery that recharges using solar energy and fuel cells are also future prospects

Self consuming systems

COMMUNICATION SYSTEM

A video/still camera,

various sensors,

micro processors, Transducers

& an omni directional antennae

GUIDANCE AND NAVIGATION

A combination of GPS+inertial sensing isideal

Geographical information system toprovide a map terrain for infrastructurewould be great

Pressure sensors

MAV SYSTEM INTEGRATION

REFERENCES

Research paper ³Death by a thousand cuts´micro air vehicles in the service of air force missions- by ARTHUR F HUBER,II LT COL USAF

http://mil.ufl.edu/~nechyba

2. Davis, W.R., "Micro UAV," Presentation to 23rd Annual AUVSI Symposium, 15-19 July, 1996.

Research paper by James M. McMichael Program Manager Defense Advanced Research ProjectsAgency

and Col. Michael S. Francis, USAF (Ret.) formerly of Defense Airborne Reconnaissance Office

MICRO AERIAL VEHICLE DEVELOPMENT: DESIGN, COMPONENTS, FABRICATION, ANDFLIGHT-TESTINGResearch paper by Gabriel Torres and Thomas J. Mueller

117 Hessert Center, University of Notre Dame

Notre Dame, IN 46556

DESIGN AND DEVELOPMENT OF A MICRO AIR VEHICLE

CONCEPT: PROJECT BIDULE

Mr T. Spoerry1, Dr K.C. Wong School of Aerospace, Mechanical and Mechatronic Engineering

University of Sydney

NSW 2006

Aerodynamics for engineers:-John J. Bertin

Mechanics of flight :-A.C Kermode

Inflatable wing on aircraft article :-new scientist june 2001

www. nasa explores. COM\aerodynamics\inflatable wing Miller, Jay,, The X-Planes, Aero fax, Arlington, Texas, 1988

morphing of inflatable wing for UAV David Cardigan* and TimSmith

ILC Dover, Frederica, DE 19946

Innovative Wing Design Could Soar in Martian Skies by benianntova

I nflatable wing for high lift john H gleen research centre Ohio

www.nastech.com/mechtech www.spaceref.com/newtech www.nasa.gov/aerodynamics www.nasa.gov/multimeadia

BACK REFERENCES

Mueller, T. J., "Low Reynolds Number Vehicles", AGARDograph No. 288, 1985

Lissaman, P. B. S., "Low-Reynolds-Number Airfoils", Annual Review of Fluid Mechanics, Vol. 15, 1983, pp. 223-239

Burgart, M., Miller, J., and Murphy, L., "Design of a Micro Air Vehicle for the 2000 MAV Competition", internal progress report, University of Notre Dame, 2000

ernet, 14 December 2000, available from http://defence-data.com/f2000/

pagefa1006.htm.

Air Force 2 ²A New Thrust in DERA Micro Air Vehicle Development,³ 24 July 2000, n.p.: On-line.

Int 0 25 , August 1996, n.p.; On-line. Internet, 18 December 2000, available from

http://www.au.af.mil/au/2025/index2.htm.

Air Force Doctrine Document (AFDD) 1, Air Force Basic Doctrine, September 1997. Air Force Scientific Advisory Board, N ew World Vistas Air and Space Power for the 21st

Century Summary Volume, 1995, n.p.; On-line. Internet, 4 December 2000, available

from http://www.sab.hq.af.mil/Archives/1995/NWV/vistas.htm.

Ashley, Steven, ²Palm-size Spy Plane,³ Mechanical Engineering , February 1998, n.p.;

On-line. Internet, 16 November 2000, available at http://www.memagazine.org/

backissues/february98/features/palmsize/palmsize.html.

Ashley, Steven, ²Turbines on a Dime,³ Mechanical Engineering , October 1997, n.p.; On-

line. Internet, 16 November 2000, available at http://www.memagazine.org/

backissues/october 97 /features/turbdime/ turbdime.html.

Barrows, Geoffrey L.,²Optic Flow Sensors for MAV Navigation,³ Proceedings of the

Conference on Fixed, Flapping and Rotary Vehicles at Very Low Reynolds N umbers,

5-7 June 2 000 , University of N otre Dame, ed. Thomas J. Mueller, 13 pages. Brendley, Keith W. and Randall Steeb, Military A pplications of Microelectromechanical

Systems, RAND Report MR-175-OSD/AF /A. Santa Monica, CA: RAND, 1993.

Carroll, Bruce,²MEMS for Micro Air Vehicles,³ Project Summaries, n.p.; On-line.

Internet, 24 August 2000, available from http://www.darpa.mil/MTO/MEMS/

Projects/individual_66.html.

Carroll, S.,²US Navy, DARPA Develop IMINT/EW Payloads for Mini-UAVs,³ Journal

of Electronic Defense 21, no. 9 (September 1998): 30-32.

Chandler, Jerome Greer, ²Micro Planes,³ Popular Science 252, no. 1 (January 1998): 54-

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