Air-Breathing Hypersonic Flight Vehicle

Faculty Advisors

Dr Chivey Wu

Team Members

Danny CovarrubiasAlfie GilAntonio Martinez

11/05/2009 NASA Grant URC NCC NNX08BA44A

Presented by:

Alfie GilAntonio Martinez

Objective

• To understand the system model behavior before applying the control algorithm

• To apply an adaptive control to the current model

11/05/2009 NASA Grant URC NCC NNX08BA44A

Overview

• Hypersonic Model

• Simulink

• Future Goals

11/05/2009 NASA Grant URC NCC NNX08BA44A

Hypersonic Model

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Conditions: Trim State:M = 10 (Mach Number)Altitude = 98,425 feet

Image from Semi-Final Report p62

Ridge Body Equations

11/05/2009 NASA Grant URC NCC NNX08BA44A

where T = Fuel Ratioe = 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

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Disturbance

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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

Simulink Model

11/05/2009 NASA 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

11/05/2009 NASA 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

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Simulink Model

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Equations in Simulink

Simulink Model

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Preliminary Tests: Varying Fuel Ratio

INPUT:

FuelRatio5

Defl. Angle- 25 deg

INPUT:

FuelRatio2

Defl. Angle- 25 deg

Simulink Model

11/05/2009 NASA Grant URC NCC NNX08BA44A

Preliminary Tests: Varying Deflect. Angle

INPUT:

FuelRatio2

Defl. Angle+5 deg

INPUT:

FuelRatio2

Defl. Angle- 25 deg

Future GoalsAddition to Simulink Model

11/05/2009 NASA 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

11/05/2009 NASA 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. 5th printing.1997.

• Wu, Chivey. Mechanical Engineering Professor. California State University, Los Angeles.

11/05/2009 NASA Grant URC NCC NNX08BA44A

Questions?

11/05/2009 NASA Grant URC NCC NNX08BA44A

Extra Slide 1

11/05/2009 NASA Grant URC NCC NNX08BA44A