1. 1 Conceptual Design Review 4/17/07 Team 1 John Horst John Horst Jared Odle Jared Odle Keith Fay Keith Fay Boyce Dauby Boyce Dauby Andrew Kovach Andrew Kovach Akshay Raje Akshay Raje Manish Handa Manish Handa Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

2. AAE 451 - Team 1 - 4/17/072 Mission Statement: Mission Statement: The objective is to provide a fixed-wing, semi- autonomous, long-endurance, continuous-area coverage unmanned aerial vehicle to relay communication of tactical importance for an extended period of time. The objective is to provide a fixed-wing, semi- autonomous, long-endurance, continuous-area coverage unmanned aerial vehicle to relay communication of tactical importance for an extended period of time. Department of Defense Department of Defense Front-line tactical communication relay to/from warfighter Front-line tactical communication relay to/from warfighter Relief Agencies/FEMA Relief Agencies/FEMA Front-line tactical communication relay to/from ground first responders Front-line tactical communication relay to/from ground first responders Commercial Customers Commercial Customers Damaged service locations, scouting of new telecommunication markets, and remote locations Damaged service locations, scouting of new telecommunication markets, and remote locations Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

3. AAE 451 - Team 1 - 4/17/073 CONOPS Takeoff Takeoff Conventional runway takeoff (Autonomous or Remote Operation) Conventional runway takeoff (Autonomous or Remote Operation) Distance from Takeoff to Coverage Area Distance from Takeoff to Coverage Area Transmitting/Receiving Transmitting/Receiving Ground Forces  UAV  Command Station or other Ground Forces Ground Forces  UAV  Command Station or other Ground Forces Control Control Autonomous with manual backup/mission override Autonomous with manual backup/mission override Remote Operators Remote Operators Trained military UAV pilots controlling from Mission Command Center Trained military UAV pilots controlling from Mission Command Center Level of Threat Level of Threat Design for high threat environment Design for high threat environment Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

4. AAE 451 - Team 1 - 4/17/074CONOPS http://www.afcea.org/signal/articles/templates/SIGNAL_Article_Template.asp?articleid=507&zoneid=4 Provide continuous area coverage for and extended time period Provide continuous area coverage for and extended time period Multiple UAVs in system Multiple UAVs in system Redundancy by overlapping coverage Redundancy by overlapping coverage Survivability via electronic countermeasures Survivability via electronic countermeasures Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

5. AAE 451 - Team 1 - 4/17/075 Design Requirements TargetThreshold Endurance 24 hr 14 hr Range 200 nm 50 nm Ceiling 30,000 ft MSL 15,000 ft MSL Takeoff 500 ft 1,000 ft Landing 500 ft 1,000 ft Transportation Volume Fit inside C-130 55’x10’x9’ Fit inside C-5 143’x19’x13.5’ Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

6. AAE 451 - Team 1 - 4/17/076 Communications Payload AJCN - Adaptive Joint C4ISR Node AJCN - Adaptive Joint C4ISR Node by BAE Systems by BAE Systems Weight 200 – 270 lbs Power 2 hp Volume * 6 – 9 ft 3 Range (Air-to-Ground)** 55 – 100 nm @ 15,000 ft Range (Air-to-Air)** 60 nm @ 15,000 ft *Volume approximated by avionic density: 0.02 – 0.03 ft 3 /lb **According to available data Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

7. AAE 451 - Team 1 - 4/17/077 Additional Payload Missile Warning/Countermeasures - BAE Systems Missile Warning/Countermeasures - BAE Systems AN/ALQ-156(V) Warning System AN/ALQ-156(V) Warning System 425 Watts of Power 425 Watts of Power 50 pounds 50 pounds 20.4 × 10.2 × 7.6 in 20.4 × 10.2 × 7.6 in AN/ALE-47 Dispensing System AN/ALE-47 Dispensing System Automatic Response Automatic Response Protects Against: Protects Against: Air Interceptor (AI), Anti-Aircraft Artillery (AAA), and Surface-to-Air Missiles (SAMs) 20 pounds 20 pounds Fielded on 1,307 Aircraft Fielded on 1,307 Aircraft 43.7 x 39.5 x 26.8 in 43.7 x 39.5 x 26.8 in Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

8. AAE 451 - Team 1 - 4/17/078 Payload Summary Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work MicroPilot - Dayview/Nightview

9. AAE 451 - Team 1 - 4/17/079 Sizing Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Custom written sizing code. Attempts are being made with FLOPs and ACS—results may be available in the report. Using General Aviation component weight predictions from Raymer.

10. AAE 451 - Team 1 - 4/17/0710 Sizing Various parameters were held constant during trade studies and carpet plot generation Various parameters were held constant during trade studies and carpet plot generation L/D12 Propeller Efficiency 0.8 Specific Fuel Consumption (c bhp ) 0.4 lb/hp-hr (cruise) 0.5 lb/hp-hr (loiter) Loiter Velocity 80 kts w e /w 0 (from UAV database) Aspect Ratio 10 Λ0 C Lmax 1.8 (Takeoff) 1.6 (Landing) Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

11. AAE 451 - Team 1 - 4/17/0711 Trade-offs Using sizing code, it was determined that increasing the design combat range from 100 to 200 nm resulted in an increase in gross weight of 100 lbs. Using sizing code, it was determined that increasing the design combat range from 100 to 200 nm resulted in an increase in gross weight of 100 lbs. Decreasing endurance from 24 hours to 20 hours saved 500 lbs. Decreasing endurance from 24 hours to 20 hours saved 500 lbs. Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

12. AAE 451 - Team 1 - 4/17/0712 Carpet Plot Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

13. AAE 451 - Team 1 - 4/17/0713 Aircraft Description *All dimensions in feet

14. AAE 451 - Team 1 - 4/17/0714 Aircraft Description Camera Rotax 914 AJCN Fuel Tanks Rear Landing Gear Main Landing Gear Missile Defense System Avionics

15. AAE 451 - Team 1 - 4/17/0715 1. Camera 2. AJCN 3. Engine Nacelles 4. Missile Defense 5. Fuel Tanks 6. Avionics *All dimensions in feet 12 3 4 5 6 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

16. AAE 451 - Team 1 - 4/17/0716 Aerodynamics NACA 65 2 -415 NACA 65 2 -415 Thick profile allows easier structural layout Thick profile allows easier structural layout Wide drag bucket @ high lift coefficients Wide drag bucket @ high lift coefficients Center at 0.4 Center at 0.4 Extends to 0.9 Extends to 0.9 Aircraft travels entire range as fuel is burned and aircraft lightens Aircraft travels entire range as fuel is burned and aircraft lightens Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

17. AAE 451 - Team 1 - 4/17/0717 Aerodynamics Trailing edge flaps on main wings. Trailing edge flaps on main wings. Fowler Flaps Fowler Flaps 33% chord ratio 33% chord ratio 50% of wing area is covered 50% of wing area is covered Basic drag component buildup using techniques described in Raymer Basic drag component buildup using techniques described in Raymer Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

18. AAE 451 - Team 1 - 4/17/0718 Aerodynamics Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

19. AAE 451 - Team 1 - 4/17/0719 Performance Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

20. AAE 451 - Team 1 - 4/17/0720 TargetThresholdCurrent Endurance 24 hr 14 hr 20 hr Combat Radius 200 nm 50 nm 200 nm Ceiling 30,000 ft MSL 15,000 ft MSL 41,000 ft MSL Takeoff Ground Roll 500 ft 1,000 ft 750 ft Landing Ground Roll 500 ft 1,000 ft 490 ft Loiter Altitude 15,000 ft AGL Current Gross Weight 3,450 lbs Stall Speed 49 kts Maximum Speed 150 kts Compliance Matrix Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

21. AAE 451 - Team 1 - 4/17/0721 Propulsion System Variable pitch propeller Variable pitch propeller In-flight adjustable In-flight adjustable Diameter : 7 ft Diameter : 7 ft Number of blades : 3 Number of blades : 3 Advance ratio (J) : 0.482 Advance ratio (J) : 0.482 Activity Factor (AF) : 100 Activity Factor (AF) : 100 Integrated design lift coefficient (Cl i ) : 0.3 Integrated design lift coefficient (Cl i ) : 0.3 Maximum working RPM : 2400 Maximum working RPM : 2400 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

22. AAE 451 - Team 1 - 4/17/0722 Propulsion System Propulsion System *Cruise velocity: 80 knots *Cruise velocity: 80 knots *Propeller Efficiency: 0.81 *Propeller Efficiency: 0.81 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

23. AAE 451 - Team 1 - 4/17/0723 Engine Description Engine Description Rotax 914 UL Aircraft Engine Rotax 914 UL Aircraft Engine 100 HP, with maximum 115 HP for 5 minutes 100 HP, with maximum 115 HP for 5 minutes 4-stroke, 4-cylinder, with turbo charger 4-stroke, 4-cylinder, with turbo charger Max RPM 5800 Max RPM 5800 Integrated reduction gear i = 2.4 Integrated reduction gear i = 2.4 Shaft RPM 2400 Shaft RPM 2400 Electric starter Electric starter Electric dual ignition system Electric dual ignition system Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

24. AAE 451 - Team 1 - 4/17/0724 Material Comparison Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

25. AAE 451 - Team 1 - 4/17/0725 Selected Materials Internal Structure (wing/tail/body) Internal Structure (wing/tail/body) Aluminum 2024-T3 Aluminum 2024-T3 Landing Gear Landing Gear Aluminum 7075-T6 Aluminum 7075-T6 Aircraft Skin Aircraft Skin Aluminum 7075-T6 Aluminum 7075-T6 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

26. AAE 451 - Team 1 - 4/17/0726 Internal Structure Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

27. AAE 451 - Team 1 - 4/17/0727 Weight Breakdown 1. W Camera 1. W Camera 2. W AJCN 2. W AJCN 3. W Engine 3. W Engine 4. W Missile Defense 4. W Missile Defense 5. W MainGear 5. W MainGear 6. W Wing 6. W Wing 7. W Fuselage 7. W Fuselage 8. W Fuel 8. W Fuel 9. W Avionics 9. W Avionics 10. W VertTail 10. W VertTail 11. W HorizTail 11. W HorizTail 12. W RearGear 12. W RearGear Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

28. AAE 451 - Team 1 - 4/17/0728 Weight Breakdown *Moment and location measured from tip of the nose

29. AAE 451 - Team 1 - 4/17/0729 Stability & Control Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

30. AAE 451 - Team 1 - 4/17/0730 Stability & Control Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

31. AAE 451 - Team 1 - 4/17/0731 Stability & Control Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

32. AAE 451 - Team 1 - 4/17/0732 Control Surface Sizing Tail Volume Coefficient Method Tail Volume Coefficient Method Vertical tail – 60 ft 2 Vertical tail – 60 ft 2 Horizontal tail – 68 ft 2 Horizontal tail – 68 ft 2 Statistical Approximation Statistical Approximation Elevator – 22 ft 2 Elevator – 22 ft 2 Rudder – 25 ft 2 Rudder – 25 ft 2 Aileron – 31 ft 2 Aileron – 31 ft 2 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

33. AAE 451 - Team 1 - 4/17/0733 Cost Very hard to estimate per aircraft Very hard to estimate per aircraft DoD Endurance-Payload model DoD Endurance-Payload model  $1.8 million DoD $1500 / lb empty weight DoD $1500 / lb empty weight  $3.2 million DoD $8000 / lb payload DoD $8000 / lb payload  $2.2 million DAPCA IV model, DAPCA IV model,  $2.7 million (50 aircraft produced) Average is $2.5 million Average is $2.5 million Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

34. AAE 451 - Team 1 - 4/17/0734 Future Work Sizing Sizing Update Carpet Plots Update Carpet Plots More Accurate Results from ACS and FLOPS More Accurate Results from ACS and FLOPS Structures Structures More detailed layout and analysis More detailed layout and analysis Better cost estimate Better cost estimate Stability and Control Stability and Control Lateral Stability Lateral Stability Control surface sizing Control surface sizing Dynamics Dynamics Flight control computer definition Flight control computer definition More detailed Aerodynamic work More detailed Aerodynamic work Potential flow analysis Potential flow analysis CFD analysis CFD analysis Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work