1. G.O.D.I.S Complex: “Gaurdian of Defense, Intelligence & Surveillance” Project Advisor: Dr. James Lang Team Leader: Dan Dalton Chief Engineer: Eugene Mahmoud Propulsion Specialist: Caitlin Smythe

2. Motivation: Northrop Grumman-Bird of Prey U.S. Patent: 5984231 June 19th, 1998 Image from: www.area51zone.com

3. Outline of Presentation Mission Profiles & Prioritization Preliminary Vehicle Configurations Downselect Criteria GODIS Configuration GODIS Performance Aerodynamics, Stability & Control Engine Integration Weights & Sub-systems Cost and Supportability Conclusion

4. Mission #1 Mission #2 Mission Profiles

5. Mission #5 Mission #4 Mission #3

6. Mission Priorities Mission #1 Mission #2 Mission #4 With Fallouts: Mission #3 Mission #5

7. Vehicle Configurations Configuration #1 Endurance/Performance Configuration #3 High-Speed Fighter Configuration #2 High-Altitude Bomber Configuration #4 Dolphin Configuration #5 Low-Altitude Bomber Configuration #6 Crowd Control

8. JLFANG Concepts: Endurance/Performance (Config. #1) High-Speed Fighter (Config. #2) High-Altitude Bomber (Config #3) Preliminary Research on Supersonic Performance and High-Technology Mission 5: De-prioritized Comparative Study Conducted to Determine Missions Prioritization and Optimal Compatibility Mission Priorities: Counter Air & High-Altitude Interdiction G.O.D.I.S COMPLEX “Gaurdian of Defense, Intelligence, and Surveillance” Subsonic UAV Concepts: Dolphin (Config. #4), Low Alt. Bomber (Config #5), Crowd Control (Config #6) Significant Factors in Design

9. GODIS configuration

10. Maneuver Weight Performance (G.O.D.I.S. Complex alpha @ 0.9 Mach, 15000 feet) Max. Mach Number @ Military Thrust = 1.61M Specific Excess Thrust: 1-g Max. Thrust = 903 feet/sec 5-g Max. Thrust = 674 feet/sec Maximum Sustained Turn = 15.73 deg/sec Maximum Sustained Loading = 9.0+ Max. Instantaneous Turn Rate = 20.64 deg/sec

11. 1-g Specific Excess Power (G.O.D.I.S Complex alpha at Maneuver Weight)

12. Aerodynamics Area = 760 ft 2 Aspect Ratio = 5.45 Sweep angle (L.E.) = -28° (extended), 50° (swept) Taper Ratio = 0.14 (extended), 0.05 (swept) t/c = 0.14 (extended), 0.04 (swept) Wing Root : NACA 64210.68 Wing Tip : NACA 64209.80 L/D max subsonic = 15 C L,max subsonic = 1.43 C Do subsonic= 0.016 M crit = 0.88

13. Aerodynamics (continued) Canard (control) –NACA 65A009 airfoil –50 degree sweep –taper ratio = 0.4 –aspect ratio = 4 Control Surfaces –subsonic: 2 flaperons per wing: First: (near tip) chord = 5.0 ft; span = 19.3 ft Second: (closer to root) chord = 5.7 ft; span = 16.1 ft –supersonic: 2 flaperons on rear: chord = 4.8 ft span = 6 ft

14. Stability & Control Due to variable forward swept wings, Switchblade requires an active flight control system (AFCS) –Switchblade will have “relaxed static stability” (i.e. - a negative static margin) The AFCS will maintain center of gravity (c.g.) positioning as well as canard, flaperon, and thrust vectoring interaction to achieve unparalleled performance regardless of mission type

15. Engine Integration Two engines per module Missions 1, 2 & 4 –Afterburning turbofan –T max (s.l.) = 45886 lb * –D max = 3.63 ft * Missions 3 & 5 –High-Bypass Turbofan –T max (s.l.) = 17030 lb * –D max = 2.37 ft * External compression 2-D ramp with 3-shock inlet –Diffuser Length = 19 ft * –External Length = 2.1 ft * 3-D Thrust Vectoring Nozzle –Exit Area = 4.35 ft * * per engine, nozzle, or inlet

16. Weight Estimates & Center of Gravity Travel C. G. Travel Counter Air Missions/High-Altitude Interdiction: Complex alpha Propulsion: Afterburning Low Bypass Turbofan Engine Empty Weight = 37,675 lbs Internal Payload = 4,000 lbs Internal Fuel = 26,730 lbs Maximum Mach number = 1.6 Maximum Thrust = 91,663 lbs Engine Weight = 9,959 lbs (2) Maritime Strike/ISR-Attack: Complex beta Propulsion: High Bypass Turbofan Engine Empty Weight = 32,410.5 lbs Internal Payload = 4,000 lbs Internal Fuel = 25,830 lbs Maximum Mach number = 1.1 Maximum Thrust = 34,061 lbs Engine Weight = 3,918 lbs (2)

17. Cost and Supportability Flyaway + RDT&E planes produced FA+RDT&E (per airplane) 50 $190 million 100 $120 million 500 $51 million Lifecycle Costs planes produced Total LCC 50 $17 billion 500 $33 billion Supportability modular engines variable sweep engine height thrust vectoring system Cost

18. Conclusion: Future Work Needed Aerodynamics Center of Gravity Travel Stability and Controls Inlet Configuration & Propulsion System Subsystem Weights and Cost Sustained Loading

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