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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
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

objective
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

overview
Overview
  • Hypersonic Model
  • Simulink
  • Future Goals

NASA Grant URC NCC NNX08BA44A

hypersonic model
Hypersonic Model

Conditions: Trim State:

M = 10 (Mach Number)

Altitude = 98,425 feet

Image from Semi-Final Report p62

NASA Grant URC NCC NNX08BA44A

ridge body equations
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

conti equations
(conti) Equations

NASA Grant URC NCC NNX08BA44A

disturbance
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

simulink model
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

simulink model1
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

simulink model2
Simulink Model

NASA Grant URC NCC NNX08BA44A

simulink model3
Simulink Model

Equations in Simulink

NASA Grant URC NCC NNX08BA44A

simulink model4
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

simulink model5
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

future goals addition to simulink model
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

continued future goals
(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

references
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

questions
Questions?

NASA Grant URC NCC NNX08BA44A

extra slide 1
Extra Slide 1

NASA Grant URC NCC NNX08BA44A

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