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Explicit Parameterized Energy Management for Scramjet Transition

This paper presents a guidance law for a booster to meet the requirements of scramjet transition. The straightforward open-loop and closed-loop guidance laws are combined together through a smooth switch. In the closed-loop guidance law, the worst case with a minimal lift-drag ratio is selected to obtain a nominal elevation angle. The excessive energy due to various uncertainties could be dissipated around this nominal trajectory adaptively. Numerical simulations are conducted to validate the effectiveness and robustness of the proposed method.