1. Ikelos Virginia Tech and Loughborough University present: 2001/2002 Interdisciplinary/International Aircraft Design Project

2. Key Requirements: Aircraft fits on trailer Lightweight and Simple STOL or VTOL Land in 46m (150ft) over 5m obstacle Cruise > 90 kts Range > 150nm 1 Seat Aircraft Original Specification

3. Each group produced 3 concepts: Counter-rotating Helicopter 2 Gyroplanes VTOL tilt duct Vectored jet Pusherprop Selected VTOL Tilt duct: Most adaptable Most Original Initial Design Ideas

4. VTOL Tilt Duct Pusher Prop Initial Concepts

5. Reviewed advantages and disadvantages of: STOL VTOL Vectored Thrust Modified Design to: STOL as standard aircraft Vectored thrust option Design Development

6. 46m (150ft) ground roll Meet SSTOL requirement 150m (500ft) over 15m (50ft) obstacle Cruise speed to be competitive with GA aircraft: 110kts – 150kts Range - 500nm at cruise speed 2 Seat Aircraft Revised Specification

7. Configuration

8. Configuration

9. Fuselage Structure Layout

10. Wing Structure Layout

11. Trailer criteria of 2.2m max. width Front Wing: I – section spars overlap in fuselage, bolted together in hollow box structure Rear Wing: Connected to top of tail using two “3-way” brackets Vertical Spars: Bolted to outer ribs using hollow tube connections Wing Detachment

12. Glass epoxy skin on wings and fuselage Skin is honeycomb sandwich Kevlar reinforcement on fuselage bottom and lower wing skins Structure framework of carbon fiber with metal reinforcements in critical areas Aluminum firewalls and steel undercarriage Materials

13. V-n Diagram

14. Manufacturing Planes assembled in individual bays Composites used where possible Composites used where possible Internal skeleton Internal skeleton Assembly team at each bay Assembly team at each bay Team unity and pride in work Team unity and pride in work Important due to the complexity of wiring, controls, and electronics Important due to the complexity of wiring, controls, and electronics

15. Non-planar vortex lattice method Incorporates various wing features Tornado VLM

16. Box-wing design Front wing twisted Unswept inboard TE flap Wing Layout

17. Based on forward wing area C LMAX = 4.19 Leading edge devices Front wing flapped Fowler te flaps, fixed vane Lift Characteristics

18. Induced drag reduction C D0 =.045 in cruise UNDERCARRIAGE 24% FUSELAGE 17% DUCTS 5% WINGS 35% INLETS AND OUTLETS 12% VERTICAL TAIL 4% OTHER 12% SIDE PLATES 3% Drag Characteristics

19. Static Stability Design Criteria: Acceptable static margin in all configuration, FAR 23 compliance Final Configuration balanced (positve Cm 0L ) with positive pitch stiffness (negative Cm  ) Lateral-Directional stability satisfied but nearly neutral to retain maneuverability Dynamic Stability Design Criteria: MIL-F-8785C specifications with Level 1 flight qualities Stability and Control

20. Aircraft equipped with standard elevators, ailerons, and rudder Control Surfaces

21. Trim Diagram

22. Used Roskam methods to determine control forces Analysis shows that FAR 23 stick force limits are satisfied Control Forces

23. CG Excursion Graph

24. Conclusion: Stable Aircraft CG Travel in MTOM Flight

25. The Rand Cam Engine Innovative diesel rotary engine Innovative diesel rotary engine Inherently simple, no pistons, timing values, Inherently simple, no pistons, timing values, spark plugs spark plugs Uses a system of axial vanes that rotate in a Uses a system of axial vanes that rotate in a cam shaped housing cam shaped housing

26. Light weight – High power to weight ratioLight weight – High power to weight ratio Fuel efficientFuel efficient Costs similar to that of an equivalent automotive engineCosts similar to that of an equivalent automotive engine Low noiseLow noise Very little vibrationVery little vibration Low maintenanceLow maintenance The Rand Cam Engine

27. Oil Pump Oil Tank Intake Cooling Air Intake Cooling Air Exhaust Fuel Tank Engine Alternator Starter Cooling Fan Oil Cooler Intake Plenum Exhaust Pipes Engine Layout

28. Higher thrust per horsepower for a given diameter than a propellerHigher thrust per horsepower for a given diameter than a propeller Better performance at low speeds than propellers – no recirculation at the tipsBetter performance at low speeds than propellers – no recirculation at the tips Quieter than propellers – noise damping material used in ductsQuieter than propellers – noise damping material used in ducts Duct provides an additional safety feature.Duct provides an additional safety feature. Duct diameter 0.92 m (3 ft)Duct diameter 0.92 m (3 ft) Fan consists of 5 rotor blades and 12 stator bladesFan consists of 5 rotor blades and 12 stator blades Fans attached to engine via a 1:2 helical spiral bevel gearFans attached to engine via a 1:2 helical spiral bevel gear Low noise 60dBs. Tip speed 113 m/s (370 ft/s)Low noise 60dBs. Tip speed 113 m/s (370 ft/s) Ducted Fans

29. Static thrust calculated using disc actuator theoryStatic thrust calculated using disc actuator theory Dynamic thrust found using general thrust equationDynamic thrust found using general thrust equation Efficiency found by reading from chart of empirical data chartsEfficiency found by reading from chart of empirical data charts Thrust Calculations

30. Thrust Curve

31. Cockpit Layout

32. Cockpit Designed for 95th percentile male (tallest male) and adjustable to 5th percentile female (shortest female) Designed for 95th percentile male (tallest male) and adjustable to 5th percentile female (shortest female) Adjustable seats and rudders Adjustable seats and rudders Center stick Center stick Energy absorbing Confor™ foam seats for high impact landing Energy absorbing Confor™ foam seats for high impact landing Canopy door allows ease of entrance Canopy door allows ease of entrance Harness seatbelts for pilot and passenger safety Harness seatbelts for pilot and passenger safety

33. Base Cockpit Instrumentation: EFIS: Display EFIS Computer AHRS Computer PFD & Engine instrumentation Transmission & Reception devices: NAV/COMM Radio Mode A/C Transponder Avionics

34. TRANSMISSION & RECEPTION EQUIPMENT PRIMARY FLIGHT DISPLAYS AND ENGINE INSTRUMENTS EFIS DISPLAY Avionics

35. Safety Anti-lock brakes Ballistic parachute 5 Point seat belt Control surface actuation Mechanical Canopy Single piece with gas struts Systems

36. Cabin Conditioning Warm air taken from oil cooler Mixed with external air Provides de-misting (de-frosting) Electrical Standard 28V system 120 Ampere alternator Systems

37. Original Specification – 46m (150ft) landing distance over 5m obstacle 46m 150ft 5m 7o7o 14m 46ft 5m 9o9o If stall speed = 25kts and free roll = 1 second free Roll = 15m Landing Issues

38. Target ground roll – 46m (150ft) Total landing and take off – NASA SSTOL 9 o Glideslope used in NASA analysis DEFINITION LANDING DISTANCE OVER 50ft OBSTACLE CTOL2000ft STOL1000ft SSTOL500ft VTOL 100 ft Revised Specifications

39. Target met at all take-off weights Landing Target met with 1 pilot and full fuel Target Landing Take-off Landing and Take-off

40. Certification over 50ft (15m) obstacle SSTOL requirement met at all conditions Target Landing Take-off Landing and Take-off

41. Cruise Performance Max Range Full Payload 650nm @ 80 knots 500 nm @ 124 knots 500 nm @ 124 knots Max Endurance over 8 hours @ 64 Knots Max Endurance over 8 hours @ 64 Knots

42. Climb Performance 10,000 ft in under 10min @ 85 % and 90 Knots 10,000 ft in under 10min @ 85 % and 90 Knots Max Climb 1364 ft/min @ 90 Knots Max Climb 1364 ft/min @ 90 Knots

43. Turn Rates Max Turn Rate 70 Deg/sec @ 57 knots Max Turn Rate 70 Deg/sec @ 57 knots

44. kg lb % kg lb % Structure 235 486 37 Structure 235 486 37 Propulsion 112 246 18 Propulsion 112 246 18 Equipment 28 62 4 Equipment 28 62 4 OEM 375 794 59 OEM 375 794 59 Payload 182 400 29 Payload 182 400 29 Fuel 78 172 12 Fuel 78 172 12 MTOM 635 1366 100 MTOM 635 1366 100 Mass Breakdown

45. Target price – luxury sports carTarget price – luxury sports car US $200,000 price ceilingUS $200,000 price ceiling Costing analysis is conducted using RoskamCosting analysis is conducted using Roskam methods methods Anticipated cost reductions from avionics development are not yet consideredAnticipated cost reductions from avionics development are not yet considered Aircraft Cost Analysis

46. Certify under Joint Airworthiness Requirements Very Light Aircraft Category Federal Airworthiness Requirements Sport aviation category: Revise requirements Certification Philosophy

47. Strengths

48. Strengths

49. Risk – Unproven propulsion system Control authority in landing – more analysis required Specialized product for SSTOL market. Weaknesses and Threats

50. Range of aircraft – basic to high performance High performance options: More advanced avionics Thrust vectoring Circulation control Higher end of Market Military or law enforcement possibilities Opportunities

51. Innovative modern technology employed. Large scope for adaptability Configuration set – but still opportunity for adjustments Project still in progress Conclusions