The propulsion system mode transition phase of a turbine-based combined cycle (TBCC) powered hypersonic vehicle is studied to determine the impact of mode transition on flight vehicle stability and performance. A non-linear, physics-based model of the longitudinal dynamics of a hypersonic vehicle has been augmented with both a non-linear turbine engine model and a ramjet propulsion model. A mode transition control approach is proposed and a linear quadratic regulator tracking control for the hypersonic vehicle is designed and implemented at a prospective mode transition operating point Example propulsion mode transition sequences are tested on the full non-linear model and the effect on overall vehicle flight performance is investigated. The models developed provide an investigative tool for identifying, implementing, and evaluating candidate mode transition control approaches.
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