This thesis examines themodeling, analysis, and control system design issues for scramjet powered hypersonic vehicles. A nonlinear three degrees of freedom longitudinal model which includes aero-propulsion-elasticity effects was used for all analyses. This model is based upon classical compressible flow and Euler-Bernouli structural concepts. Higher fidelity computational fluid dynamics and finite element methods are needed for more precise intermediate and final evaluations. The methods presented within this thesis were shown to be useful for guiding initial control relevant design.
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- Electrical Engineering
- Aerospace Engineering
- Mechanical Engineering
- Control design
- Hypersonic Vehicle
- Hypersonic planes--Mathematical models.
- Hypersonic planes
- Airbreathing launch vehicles--Mathematical models.
- Airbreathing launch vehicles
- Flight control--Mathematical models.
- Flight control
- Partial requirement for: M.S., Arizona State University, 2011Note typethesis
- Includes bibliographical references (p. 207-220)Note typebibliography
- Field of study: Electrical engineering