ds-900 series lightflyer 1a · 2019. 10. 29. · cruise speed range weight take-off distance price...
TRANSCRIPT
![Page 1: DS-900 Series Lightflyer 1A · 2019. 10. 29. · Cruise Speed Range Weight Take-off Distance Price Coyote II 92 kts 365 nm 1320 lbs 370 $39,000 Denney Kiox 109 kts 682 nm 1200 lbs](https://reader036.vdocuments.us/reader036/viewer/2022071514/6136a9380ad5d20676482ac2/html5/thumbnails/1.jpg)
DS-900 Series Lightflyer
1A
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Overview
´ Team Members
´ Motivation
´ Mission Specifications
´ Mission Profile
´ Similar Aircraft
2A
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Overview
3A
´ Weight and Balance Analysis
´ Stability and Control Analysis
´ Three View Drawing
´ Market Analysis
´ Conclusions and Recommendations
´ Questions
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Team Members and Responsibilities
´ Design Team Leader – Cassidy Luedtke
´ Weight and Balance – Cassidy Luedtke
´ Stability and Control – Cassidy Luedtke
´ Aerodynamics – Mac McCaleb
´ Propulsion – Kevin Garcia
´ CAD Design – Kevin Garcia
´ Structures and Landing Gear – Michael LaBarbera 4A
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Motivation
´ Light Sport Aviation
´ Created in 2004 to fill gap between ULA and GA
´ Lower requirements to become a pilot
´ Low-Cost to Purchase, Affordable to Fly
´ Safe and Easy to Fly
´ Focus on stability
´ Emergency safety systems
´ Small, Lightweight, Portable Design 5A
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Mission Cassidy Luedtke
6A
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Mission Specifications
´ Two Person Enclosed Cockpit
´ Fit on Trailer No Longer than 30 Feet in Length.
´ Redundant Safety Systems in Case of Emergency
´ Cost per Aircraft Less than $25,000
´ Gross Weight Less than 900 lbs
7A
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Mission Specifications
´ Take-off distance of not more than 200 feet
´ Operating altitude capability of 6,000 feet (MSL)
´ Cruise at an airspeed of 50 knots or greater
´ Endurance capability of at least 2 hours
8A
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Mission Weight Analysis Cassidy Luedtke
9A
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Mission Weight Estimates
𝑊↓𝐸 = 𝑊↓𝑇𝑂 − 𝑊↓𝑡𝑓𝑜 − 𝑊↓𝑐𝑟𝑒𝑤 − 𝑊↓𝑓𝑢𝑒𝑙 − 𝑊↓𝑃𝐿
Categories Weight (lbs) 𝑊↓𝑇𝑂 900 𝑊↓𝑡𝑓𝑜 14 𝑊↓𝑐𝑟𝑒𝑤 360 𝑊↓𝑓𝑢𝑒𝑙 78 𝑊↓𝑃𝐿 10 𝑊↓𝐸 438
10A
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Take-off Weight Sensitivities Cassidy Luedtke
11A
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Weight Sensitivity Summary
Empty Weight Sensitivity: 𝜕𝑊↓𝑇𝑂 /𝜕𝑊↓𝐸 1.545
L/D Sensitivity: 𝜕𝑊↓𝑇𝑂 /𝜕𝐿/𝐷 -98.60 lbs.
12A
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Performance Constraint Analysis Cassidy Luedtke
13A
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Design Space
14A
0.00
0.05
0.10
0.15
0.20
0.25
0 2 4 6 8 10 12 14 16
P/W
(h
p/l
b)
W/S (lb/ft²)
Take-off
Climb
Stall
Cruise
Landing
Design Point
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Aircraft Configuration Cassidy Luedtke
15A
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Aircraft Configuration
16A
´ Tricycle Landing Gear
´ High Wing
´ 3 Blade Propeller
´ Tractor Engine Layout
´ Enclosed Cockpit with Side by Side Seats
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Similar Aircraft Kevin Garcia
17A
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Coyote II
18A
Pros:
Foldable Wings
Cost
Cons:
Range
Weight
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Pros:
Foldable Wings
Range
Cruise Speed
Cons:
Range
Cost
Weight
Denney Kitfox
19A
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Pros:
Low Weight
High Power
Tricycle Gear
Cons:
Non-Folding Wings
Range
Cost
Aerosport C42 Ikarus
20A
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Similar Aircraft Summary
21A
Aircra&CruiseSpeed Range Weight
Take-offDistance Price
CoyoteII 92kts 365nm 1320lbs 3706 $39,000
DenneyKi<ox 109kts 682nm 1200lbs 3806 $42,000
Ikarus 86kts 405nm 992lbs 4706 $52,000
DS-900Ligh<lyer 90kts 375nm 900lbs 2006 $25,000
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Propulsion Layout and Design Kevin Garcia
22A
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Propulsion Layout
´ Internal Combustion
´ 4-Stroke
´ Firewall Mounted
´ Tractor Configuration
23A
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Aero Swiss Engines 750 Turbo-Charged
24A
´ 4-Stroke
´ 2-Cylinder
´ 750cc Displacement
´ Turbo Charged
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Aero Swiss Engines 750 Turbo-Charged
25A
´ High Power to Weight Ratio
´ TBO 2000 hrs
´ Low Cost
´ Performance Compensation at Higher Altitudes
´ Compact Design
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ASE 750 TC Performance Analysis
26A
´ 138 SHP @ 7500 rpm
´ Peak Horsepower for 5 Minutes
´ Cruise 65 SHP @ 4750 rpm
´ 3.5 GPH @ Cruise
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Propeller Selection and Sizing
27A
´ 3 – Bladed
´ Composite
´ Gear Reduction
´ Ground Adjustable Pitch
´ Standard Spinner
´ Conservative Ground Clearance
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Wing Layout and Design Mac McCaleb
28A
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Wing Design and Layout
29A
´ 𝑊/𝑆 = 7.25 𝑙𝑏/𝑓𝑡↑2
´ S = 124 𝑓𝑡↑2
´ AR = 7.3
´ Span = 30.125 ft and Chord 4.125 ft
´ Flaps Occupy 50% Span and 30% Chord
´ Use Flaperons for Weight Savings and Efficiency
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Airfoil Selections
30A
-1.500
-1.000
-0.500
0.000
0.500
1.000
1.500
2.000
-20 -15 -10 -5 0 5 10 15 20
Cd
Cl
NACA 63(3)-618
0.0000
0.0020
0.0040
0.0060
0.0080
0.0100
0.0120
0.0140
0.0160
-1.2 -0.8 -0.4 0 0.4 0.8 1.2 1.6
Cd
Cl
NACA 63(3)-618
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Airfoil Selections
31A
-1.4
-1.2
-1
-0.8
-0.6
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
-18 -16 -14 -12 -10 -8 -6 -4 -2 0 2 4 6 8 10 12 14 16 18 20
Cl a
nd
CL
Alpha
NACA 63(3) - 618
0
0.01
0.02
0.03
0.04
0.05
0.06
0.07
0.08
0.09
0.1
-1.5 -1 -0.5 0 0.5 1 1.5
CD
CL
NACA 63(3) - 618
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High Lift Devices
32A
Device ∆𝜶↓𝑪↓𝑳↓𝒎𝒂𝒙 (Degrees)
∆𝑪↓𝑳↓𝒎𝒂𝒙 ∆𝑪↓𝑫↓𝒎𝒊𝒏
Leading Edge Slot
9 0.481 0.0088
Slotted Flap (δ=0)
0 0 0.0012
Slotted Flap (δ=10)
-0.4 0.175 0.01
Slotted Flap (δ=20)
-1 0.35 0.035
Slotted Flap (δ=30)
-1.8 0.525 0.076
δ= deflection angle in degrees
Reference Theory of Wing Sections/ Nicolai/Carichner
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High Lift Device Effects
33A -1.5
-1.3
-1.1
-0.9
-0.7
-0.5
-0.3
-0.1
0.1
0.3
0.5
0.7
0.9
1.1
1.3
1.5
1.7
1.9
2.1
2.3
-20 -16 -12 -8 -4 0 4 8 12 16 20 24
CL
Alpha
NACA 63(3) - 618
Plain
0Deg Flap/LE Slot
10Deg Flap/LE Slot
20Deg Flap/LE Slot
30Deg Flap/LE Slot
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Empennage Layout and Design Mac McCaleb
34A
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Airfoil Selections
35A
-2.00
-1.50
-1.00
-0.50
0.00
0.50
1.00
1.50
2.00
-20 -15 -10 -5 0 5 10 15 20
Cl
Alpha
NACA 0012
0
0.002
0.004
0.006
0.008
0.01
0.012
0.014
0.016
0.018
-1.50 -1.00 -0.50 0.00 0.50 1.00 1.50
Cd
Cl
NACA 0012
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Airfoil Selections
36A
-2
-1.5
-1
-0.5
0
0.5
1
1.5
2
-20 -15 -10 -5 0 5 10 15 20
Cland
CL
Alpha
NACA0012Wing
Airfoil
0
0.01
0.02
0.03
0.04
0.05
0.06
0.07
0.08
0.09
0.1
-1.5 -1 -0.5 0 0.5 1 1.5
CD
CL
NACA0012
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´ 𝑉↓𝐻𝑇 = 𝑆↓𝐻𝑇 𝑋↓𝐻𝑇 /𝑆𝑐 = 0.7
´ 𝑋↓𝐻𝑇 = 16 ft
´ 𝑆↓𝐻𝑇 = 22.5 𝑓𝑡↑2
´ AR= 2.5
´ Span = 7.5 ft and Chord = 3 ft
´ Elevator Chord is 50% of the
Horizontal Tail Chord
Horizontal Tail Sizing
37A
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Vertical Tail Sizing
´ 𝑉↓𝑉𝑇 = 𝑆↓𝐻𝑇 𝑋↓𝐻𝑇 /𝑆𝑐 = 0.0575
´ 𝑋↓𝑉𝑇 = 14.5 ft
´ 𝑆↓𝑉𝑇 = 13.4 𝑓𝑡↑2
´ AR= 2.4
´ Height = 4 ft and Chord = 3.75 ft
´ Rudder Area is 50% of the Area
of the Vertical Tail
38A
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Aircraft Performance Mac McCaleb
39A
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Drag Build-up
´ 𝐶↓𝐷↓0 = 𝑐↓𝑓𝑒 (𝑆↓𝑤𝑒𝑡 /𝑆↓𝑟𝑒𝑓 ) = 0.02365
´ 𝑐↓𝑓𝑒 = 0.0055
´ 𝑆↓𝑤𝑒𝑡 = 533.2854 𝑓𝑡↑2
´ 𝑆↓𝑟𝑒𝑓 = 123.75 𝑓𝑡↑2
40A Reference: Raymer
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Drag Polar
41A
0
100
200
300
400
500
600
0 20 40 60 80 100 120
Dra
g (
Lbs.
)
Velocity (KTAS)
Aircraft Drag Polar – Sea Level
Total Drag SL
Parasite Drag SL
Induced Drag SL
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Power
42A
0
20
40
60
80
100
120
140
160
180
200
0 20 40 60 80 100 120 140
Pow
er (
Hp
)
Velocity (KTAS)
Power Available vs. Power Required Pa at SL, 6k, and 10k ft. Pr at SL
Pr at 6k ft.
Pr at 10k ft.
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Cockpit Layout and Design Michael LaBarbera
43A
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Cockpit Layout
44A
´ Side-by-Side Seating
´ 42 in Cockpit Width
´ Bucket Seats
´ Joystick Flight Controls
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Field of View
45A
´ 19.39 deg. Up
´ 12.04 deg. Down
Roskam, Part III, Pg 16
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Landing Gear Michael LaBarbera
46A
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Landing Gear Layout
47A
´ Fixed Tricycle Gear
´ Spring Main Gear
´ Drum Brakes on Main Gear
´ Front Oleo Shock-Strut
Raymer pg. 239
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Main Landing Gear Design
48A
´ 7075-T6 Aluminum
´ 15.5 in. Axle to Water Line
´ Track Width 67.25 in.
´ Weight 18.1 lbs.
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Nose Landing Gear Design
49A
´ Internal Oleo Strut
´ Steerable with Direct
Linkages
´ Travel 6 in.
´ Strut Diameter 1 in.
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Landing Gear Static Load
50A
´ Front Gear Load 257 lbs
´ Main Gear Load 643 lbs
´ 321.5 lbs/wheel
´ Tire Size 12 in x 5 in
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Longitudinal Tip-Over
51A Roskam, Part II, P219
´ Most Aft CG
´ 19.82 deg.
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Longitudinal Ground Clearance
52A
Roskam, Part II, P221
´ Wheel Base 45.6 in.
´ 52.07 in. Ground to
Tail
´ Prop Ground
Clearance 9.6 in.
´ 16 deg.
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Lateral Ground Clearance
53A
´ Track 67.25 in.
´ Wing Tip from Wheel 147 in.
´ Bottom of Wing to Ground
62.5 in.
´ Φ = 23 deg.
Roskam, Part II, P221
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Weight and Balance Analysis Cassidy Luedtke
54A
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Center of Gravity Locations
55A
1
Z
X
7 6
3
5
2
4 8
9
10
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Excursion Diagram
56A
0
100
200
300
400
500
600
700
800
900
1000
59 60 61 62 63 64 65 66 67 68
Weight(lbs)
C.G.LocaRon(in)
Weight-C.G.ExcursionDiagram
13
45
2
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Stability and Control Analysis Cassidy Luedtke
57A
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Longitudinal Stability
58A
´ Static Margin Greater than 0 Considered Stable
´ Static margin greater than 10% considered
moderate to high stability
´ Volume Sizing Gives Horizontal Tail Area of 22.5 ft^2
´ Returns static margin of 12.1%
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Directional Stability
59A
´ Cnβ Greater than 0 Considered Stable
´ Roskam Suggests Approximate Cnβ = 0.001
´ Returns vertical tail area of approximately 1.1 ft^2
´ Volume Sizing Gives Vertical Tail Area of 13.4 ft^2
´ Returns Cnβ = 0.0743
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Market Analysis Cassidy Luedtke
60A
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Market Research & Analysis
´ 8,000 LSA Accounting for 5% of Single Engine
Aircraft in USA
´ Experimental LSA Dominated by Vans RV-12
´ 74 Units/Year at $80,000
´ Special LSA Dominated by CubCrafters
CarbonCubSS
´ 53 Units/Year at $185,000 61A
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Labor Analysis Cassidy Luedtke
62A
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Labor Hours
63A
Breakdown of Hours per Category
Management
Engineering
Technical
Administration
Breakdown of Cost per Category
Management
Engineering
Technical
Administration
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Phase III Gantt Chart
64A
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Conclusion and Recommendations Cassidy Luedtke
65A
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Conclusions
1. Small Field of View in Downward Direction
2. Very High Value of Cnβ
3. Similar Size as Similar Aircraft but Much Lighter
66A
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References
´ Raymer, D. (1989). Aircraft design: A conceptual approach. Washington, D.C.: American Institute of Aeronautics and Astronautics.
´ Roskam, J. (1985). Airplane design. Ottawa, Kan.: Roskam Aviation and Engineering.
´ Harloff, G. (2013). Light Sport and General Aviation Airplane Comparison and Harloff Performance Factor. Westlake, Oh.:Harloff Incorporated.
67A
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Q & A
68A