This thesis examines the modeling, 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 analysis. This model is based upon classical compressible flow and Euler-Bernouli structural concepts. Higher fidelity computational fluid dynamics and finite elementmethods are needed formore 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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- Engineering, Electronics and Electrical
- Hypersonic planes--Design and construction--Mathematical models.
- Hypersonic planes
- Flight control--Mathematical models.
- Flight control
- Plumes (Fluid dynamics)--Mathematical models.
- Plumes (Fluid dynamics)
- Propulsion systems--Mathematical models.
- Propulsion systems
- Partial requirement for: M.S., Arizona State University, 2010Note typethesis
- Includes bibliographical references (p. 152-
- Field of study: Electrical engineering