air-breathing hypersonic flight vehicle faculty advisors dr chivey wu team members danny covarrubias...
TRANSCRIPT
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
11/05/2009 NASA Grant URC NCC NNX08BA44A
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
11/05/2009 NASA Grant URC NCC NNX08BA44A
Disturbance
11/05/2009 NASA Grant URC NCC NNX08BA44A
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
11/05/2009 NASA Grant URC NCC NNX08BA44A
Simulink Model
11/05/2009 NASA Grant URC NCC NNX08BA44A
Equations in Simulink
Simulink Model
11/05/2009 NASA Grant URC NCC NNX08BA44A
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