DS-900 Series Lightflyer

1A

Overview

´ Team Members

´ Motivation

´ Mission Specifications

´ Mission Profile

´ Similar Aircraft

2A

Overview

3A

´ Weight and Balance Analysis

´ Stability and Control Analysis

´ Three View Drawing

´ Market Analysis

´ Conclusions and Recommendations

´ Questions

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

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

Mission Cassidy Luedtke

6A

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

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

Mission Weight Analysis Cassidy Luedtke

9A

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

Take-off Weight Sensitivities Cassidy Luedtke

11A

Weight Sensitivity Summary

Empty Weight Sensitivity: 𝜕𝑊↓𝑇𝑂 /𝜕𝑊↓𝐸   1.545

L/D Sensitivity: 𝜕𝑊↓𝑇𝑂 /𝜕𝐿/𝐷  -98.60 lbs.

12A

Performance Constraint Analysis Cassidy Luedtke

13A

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

Aircraft Configuration Cassidy Luedtke

15A

Aircraft Configuration

16A

´ Tricycle Landing Gear

´ High Wing

´ 3 Blade Propeller

´ Tractor Engine Layout

´ Enclosed Cockpit with Side by Side Seats

Similar Aircraft Kevin Garcia

17A

Coyote II

18A

Pros:

Foldable Wings

Cost

Cons:

Range

Weight

Pros:

Foldable Wings

Range

Cruise Speed

Cons:

Range

Cost

Weight

Denney Kitfox

19A

Pros:

Low Weight

High Power

Tricycle Gear

Cons:

Non-Folding Wings

Range

Cost

Aerosport C42 Ikarus

20A

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

Propulsion Layout and Design Kevin Garcia

22A

Propulsion Layout

´  Internal Combustion

´ 4-Stroke

´ Firewall Mounted

´ Tractor Configuration

23A

Aero Swiss Engines 750 Turbo-Charged

24A

´ 4-Stroke

´ 2-Cylinder

´ 750cc Displacement

´ Turbo Charged

Aero Swiss Engines 750 Turbo-Charged

25A

´ High Power to Weight Ratio

´ TBO 2000 hrs

´ Low Cost

´ Performance Compensation at Higher Altitudes

´ Compact Design

ASE 750 TC Performance Analysis

26A

´ 138 SHP @ 7500 rpm

´ Peak Horsepower for 5 Minutes

´ Cruise 65 SHP @ 4750 rpm

´ 3.5 GPH @ Cruise

Propeller Selection and Sizing

27A

´ 3 – Bladed

´ Composite

´ Gear Reduction

´ Ground Adjustable Pitch

´ Standard Spinner

´ Conservative Ground Clearance

Wing Layout and Design Mac McCaleb

28A

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

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

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

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

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

Empennage Layout and Design Mac McCaleb

34A

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

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

´  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

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

Aircraft Performance Mac McCaleb

39A

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

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

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.

Cockpit Layout and Design Michael LaBarbera

43A

Cockpit Layout

44A

´ Side-by-Side Seating

´ 42 in Cockpit Width

´ Bucket Seats

´ Joystick Flight Controls

Field of View

45A

´ 19.39 deg. Up

´ 12.04 deg. Down

Roskam, Part III, Pg 16

Landing Gear Michael LaBarbera

46A

Landing Gear Layout

47A

´ Fixed Tricycle Gear

´ Spring Main Gear

´ Drum Brakes on Main Gear

´ Front Oleo Shock-Strut

Raymer pg. 239

Main Landing Gear Design

48A

´ 7075-T6 Aluminum

´ 15.5 in. Axle to Water Line

´ Track Width 67.25 in.

´ Weight 18.1 lbs.

Nose Landing Gear Design

49A

´  Internal Oleo Strut

´ Steerable with Direct

Linkages

´ Travel 6 in.

´ Strut Diameter 1 in.

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

Longitudinal Tip-Over

51A Roskam, Part II, P219

´ Most Aft CG

´ 19.82 deg.

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.

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

Weight and Balance Analysis Cassidy Luedtke

54A

Center of Gravity Locations

55A

1

Z

X

7 6

3

5

2

4 8

9

10

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

Stability and Control Analysis Cassidy Luedtke

57A

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%

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

Market Analysis Cassidy Luedtke

60A

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

Labor Analysis Cassidy Luedtke

62A

Labor Hours

63A

Breakdown of Hours per Category

Management

Engineering

Technical

Administration

Breakdown of Cost per Category

Management

Engineering

Technical

Administration

Phase III Gantt Chart

64A

Conclusion and Recommendations Cassidy Luedtke

65A

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

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

Q & A

68A