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Long-Endurance UAV for Tactical Communication Relay

This conceptual design review presents a fixed-wing, semi-autonomous long-endurance unmanned aerial vehicle (UAV) for tactical communication relay in high-threat environments. The review includes mission analysis, payload sizing, aircraft description, aerodynamics, performance, propulsion, structure, weights, stability and control, cost, and future work.

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Long-Endurance UAV for Tactical Communication Relay

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  1. Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Conceptual Design Review4/17/07Team 1 • John Horst • Jared Odle • Keith Fay • Boyce Dauby • Andrew Kovach • Akshay Raje • Manish Handa

  2. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work • 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. • Department of Defense • Front-line tactical communication relay to/from warfighter • Relief Agencies/FEMA • Front-line tactical communication relay to/from ground first responders • Commercial Customers • Damaged service locations, scouting of new telecommunication markets, and remote locations

  3. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work • Takeoff • Conventional runway takeoff (Autonomous or Remote Operation) • Distance from Takeoff to Coverage Area • Transmitting/Receiving • Ground Forces  UAV  Command Station or other Ground Forces • Control • Autonomous with manual backup/mission override • Remote Operators • Trained military UAV pilots controlling from Mission Command Center • Level of Threat • Design for high threat environment CONOPS

  4. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work CONOPS http://www.afcea.org/signal/articles/templates/SIGNAL_Article_Template.asp?articleid=507&zoneid=4 • Provide continuous area coverage for and extended time period • Multiple UAVs in system • Redundancy by overlapping coverage • Survivability via electronic countermeasures

  5. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Design Requirements

  6. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Communications Payload • AJCN - Adaptive Joint C4ISR Node by BAE Systems *Volume approximated by avionic density: 0.02 – 0.03 ft3/lb **According to available data

  7. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Additional Payload • Missile Warning/Countermeasures - BAE Systems • AN/ALQ-156(V) Warning System • 425 Watts of Power • 50 pounds • 20.4 × 10.2 × 7.6 in • AN/ALE-47 Dispensing System • Automatic Response • Protects Against: Air Interceptor (AI), Anti-Aircraft Artillery (AAA), and Surface-to-Air Missiles (SAMs) • 20 pounds • Fielded on 1,307 Aircraft • 43.7 x 39.5 x 26.8 in

  8. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Payload Summary MicroPilot - Dayview/Nightview

  9. Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Sizing • 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. AAE 451 - Team 1 - 4/17/07

  10. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Sizing • Various parameters were held constant during trade studies and carpet plot generation

  11. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work 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. • Decreasing endurance from 24 hours to 20 hours saved 500 lbs.

  12. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Carpet Plot

  13. Aircraft Description *All dimensions in feet AAE 451 - Team 1 - 4/17/07

  14. AAE 451 - Team 1 - 4/17/07 Aircraft Description Missile Defense System Avionics Rear Landing Gear Camera Fuel Tanks Main Landing Gear Rotax 914 AJCN

  15. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work 1. Camera 2. AJCN 3. Engine Nacelles 4. Missile Defense 5. Fuel Tanks 6. Avionics 1 2 4 6 3 5 *All dimensions in feet

  16. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Aerodynamics • NACA 652-415 • Thick profile allows easier structural layout • Wide drag bucket @ high lift coefficients • Center at 0.4 • Extends to 0.9 • Aircraft travels entire range as fuel is burned and aircraft lightens

  17. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Aerodynamics • Trailing edge flaps on main wings. • Fowler Flaps • 33% chord ratio • 50% of wing area is covered • Basic drag component buildup using techniques described in Raymer

  18. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Aerodynamics

  19. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Performance

  20. Compliance Matrix AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work

  21. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Propulsion System • Variable pitch propeller • In-flight adjustable • Diameter : 7 ft • Number of blades : 3 • Advance ratio (J) : 0.482 • Activity Factor (AF) : 100 • Integrated design lift coefficient (Cli) : 0.3 • Maximum working RPM : 2400

  22. Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Propulsion System *Cruise velocity: 80 knots *Propeller Efficiency: 0.81 AAE 451 - Team 1 - 4/17/07

  23. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Engine Description • Rotax 914 UL Aircraft Engine • 100 HP, with maximum 115 HP for 5 minutes • 4-stroke, 4-cylinder , with turbo charger • Max RPM 5800 • Integrated reduction gear i = 2.4 • Shaft RPM 2400 • Electric starter • Electric dual ignition system

  24. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Material Comparison

  25. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Selected Materials • Internal Structure (wing/tail/body) • Aluminum 2024-T3 • Landing Gear • Aluminum 7075-T6 • Aircraft Skin • Aluminum 7075-T6

  26. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Internal Structure

  27. Weight Breakdown AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work • 1. WCamera • 2. WAJCN • 3. WEngine • 4. WMissile Defense • 5. WMainGear • 6. WWing • 7. WFuselage • 8. WFuel • 9. WAvionics • 10. WVertTail • 11. WHorizTail • 12. WRearGear

  28. AAE 451 - Team 1 - 4/17/07 Weight Breakdown *Moment and location measured from tip of the nose

  29. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Stability & Control

  30. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Stability & Control

  31. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Stability & Control

  32. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Control Surface Sizing • Tail Volume Coefficient Method • Vertical tail – 60 ft2 • Horizontal tail – 68 ft2 • Statistical Approximation • Elevator – 22 ft2 • Rudder – 25 ft2 • Aileron – 31 ft2

  33. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Cost • Very hard to estimate per aircraft • DoD Endurance-Payload model  $1.8 million • DoD $1500 / lb empty weight  $3.2 million • DoD $8000 / lb payload  $2.2 million • DAPCA IV model,  $2.7 million (50 aircraft produced) • Average is $2.5 million

  34. AAE 451 - Team 1 - 4/17/07 Introduction Mission Analysis Payload Sizing Aircraft Description Aerodynamics Performance Propulsion Structure Weights Stability & Control Cost Future Work Future Work • Sizing • Update Carpet Plots • More Accurate Results from ACS and FLOPS • Structures • More detailed layout and analysis • Better cost estimate • Stability and Control • Lateral Stability • Control surface sizing • Dynamics • Flight control computer definition • More detailed Aerodynamic work • Potential flow analysis • CFD analysis

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