# Air-Breathing Hypersonic Flight Vehicle Faculty Advisors Dr Chivey Wu Team Members Danny Covarrubias Alfie Gil Antonio Martinez 11/05/2009NASA Grant URC.

## Presentation on theme: "Air-Breathing Hypersonic Flight Vehicle Faculty Advisors Dr Chivey Wu Team Members Danny Covarrubias Alfie Gil Antonio Martinez 11/05/2009NASA Grant URC."— Presentation transcript:

Air-Breathing Hypersonic Flight Vehicle Faculty Advisors Dr Chivey Wu Team Members Danny Covarrubias Alfie Gil Antonio Martinez 11/05/2009NASA Grant URC NCC NNX08BA44A Presented by: Alfie Gil Antonio Martinez

Objective To understand the system model behavior before applying the control algorithm To apply an adaptive control to the current model 11/05/2009NASA Grant URC NCC NNX08BA44A

Overview Hypersonic Model Simulink Future Goals 11/05/2009NASA Grant URC NCC NNX08BA44A

Hypersonic Model 11/05/2009NASA Grant URC NCC NNX08BA44A Conditions:Trim State: M = 10 (Mach Number) Altitude = 98,425 feet Image from Semi-Final Report p62

InputOutput Nominal Ridge Body Equation Ridge Body Equations 11/05/2009NASA Grant URC NCC NNX08BA44A 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)

(conti) Equations 11/05/2009NASA Grant URC NCC NNX08BA44A

Disturbance 11/05/2009NASA Grant URC NCC NNX08BA44A Disturbance due to the longitudinal and vertical wind gusts dx and dz. where V 0 is the velocity of Mach 10 in terms of ft/s

Simulink Model 11/05/2009NASA Grant URC NCC NNX08BA44A Some fun facts: –1 mach = 761.2 mph (Speed of Sound) FA-18 Hornet Breaking the sound barrier, Photo Custody of the Navy

Simulink Model 11/05/2009NASA Grant URC NCC NNX08BA44A Some fun facts: –1 mach = 761.2 mph (Speed of Sound) Hyper-X at mach 7, Photo Custody of the Nasa –10 mach = 7,612 mph ~ 2 miles/sec –AHFV would fly from CSULA to Santa Monica (~20 miles) in 10 seconds!

Simulink Model 11/05/2009NASA Grant URC NCC NNX08BA44A

Simulink Model 11/05/2009NASA Grant URC NCC NNX08BA44A Preliminary Tests: Varying Fuel Ratio INPUT: FuelRatio 5 Defl. Angle - 25 deg INPUT: FuelRatio 2 Defl. Angle - 25 deg

Simulink Model 11/05/2009NASA Grant URC NCC NNX08BA44A Preliminary Tests: Varying Deflect. Angle INPUT: FuelRatio 2 Defl. Angle +5 deg INPUT: FuelRatio 2 Defl. Angle - 25 deg

Future Goals Addition to Simulink Model 11/05/2009NASA Grant URC NCC NNX08BA44A 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)

(continued) Future Goals Once the modeling of the Hypersonic Vehicle is done, we would test the control algorithm –Mix μ Compensator –Robust Adaptive Supervisor 11/05/2009NASA Grant URC NCC NNX08BA44A

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. 5 th printing.1997. Wu, Chivey. Mechanical Engineering Professor. California State University, Los Angeles. 11/05/2009NASA Grant URC NCC NNX08BA44A

Questions? 11/05/2009NASA Grant URC NCC NNX08BA44A

Extra Slide 1 11/05/2009NASA Grant URC NCC NNX08BA44A

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