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Air-Breathing Hypersonic Flight Vehicle

S P A C E Structures, Propulsion, And Control Engineering C e n t e r. Air-Breathing Hypersonic Flight Vehicle. Presented by: Alfie Gil Antonio Martinez. Team Members Danny Covarrubias Alfie Gil Antonio Martinez. Faculty Advisors Dr Chivey Wu. Objective.

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Air-Breathing Hypersonic Flight Vehicle

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  1. S P A C E Structures, Propulsion, And Control Engineering C e n t e r Air-Breathing Hypersonic Flight Vehicle Presented by: Alfie Gil Antonio Martinez Team Members Danny Covarrubias Alfie Gil Antonio Martinez Faculty Advisors Dr Chivey Wu NASA Grant URC NCC NNX08BA44A

  2. Objective • To understand the system model behavior before applying the control algorithm • To apply an adaptive control to the current model NASA Grant URC NCC NNX08BA44A

  3. Overview • Hypersonic Model • Simulink • Future Goals NASA Grant URC NCC NNX08BA44A

  4. Hypersonic Model Conditions: Trim State: M = 10 (Mach Number) Altitude = 98,425 feet Image from Semi-Final Report p62 NASA Grant URC NCC NNX08BA44A

  5. Ridge Body Equations where T = Fuel Ratio e = Elevon Deflection Angle (rad) V = Velocity (ft/s)  = Flight Path Angle (rad) h = Altitude (ft)  = Angle of Attack (rad) q = Pitch Rate (rad/s) NASA Grant URC NCC NNX08BA44A

  6. (conti) Equations NASA Grant URC NCC NNX08BA44A

  7. Disturbance Disturbance due to the longitudinal and vertical wind gusts dx and dz. where V0 is the velocity of Mach 10 in terms of ft/s NASA Grant URC NCC NNX08BA44A

  8. Simulink Model • Some fun facts: • 1 mach = 761.2 mph (Speed of Sound) FA-18 Hornet Breaking the sound barrier, Photo Custody of the Navy NASA Grant URC NCC NNX08BA44A

  9. Simulink Model • Some fun facts: • 1 mach = 761.2 mph (Speed of Sound) • 10 mach = 7,612 mph ~ 2 miles/sec • AHFV would fly from CSULA to Santa Monica (~20 miles) in 10 seconds! Hyper-X at mach 7, Photo Custody of the Nasa NASA Grant URC NCC NNX08BA44A

  10. Simulink Model NASA Grant URC NCC NNX08BA44A

  11. Simulink Model Equations in Simulink NASA Grant URC NCC NNX08BA44A

  12. Simulink Model Preliminary Tests: Varying Fuel Ratio INPUT: FuelRatio 2 Defl. Angle - 25 deg INPUT: FuelRatio 5 Defl. Angle - 25 deg NASA Grant URC NCC NNX08BA44A

  13. Simulink Model Preliminary Tests: Varying Deflect. Angle INPUT: FuelRatio 2 Defl. Angle - 25 deg INPUT: FuelRatio 2 Defl. Angle +5 deg NASA Grant URC NCC NNX08BA44A

  14. Future GoalsAddition to Simulink Model Additional uncertainty due to structural deformation. Elastic Deflection: n = 2.5751 x 10-8 (rad, local change in angle of attack) t = 3.0666 x 10-8 (rad, elevon deflection) NASA Grant URC NCC NNX08BA44A

  15. (continued)Future Goals • Once the modeling of the Hypersonic Vehicle is done, we would test the control algorithm • Mix μ Compensator • Robust Adaptive Supervisor NASA Grant URC NCC NNX08BA44A

  16. References • Anderson, John D. Fundamentals of Aerodynamics. McGraw-Hill. 1984. • Intelligent Flight Control. Semi-Final Report. Prepared by USC students. • Brandt, Steven et al. Introduction to Aeronautics: A Design Perspective. AIAA. 5th printing.1997. • Wu, Chivey. Mechanical Engineering Professor. California State University, Los Angeles. NASA Grant URC NCC NNX08BA44A

  17. Questions? NASA Grant URC NCC NNX08BA44A

  18. Extra Slide 1 NASA Grant URC NCC NNX08BA44A

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