| Summary: | This paper investigates the fault tolerance control of hypersonic aircrafts with <inline-formula><math display="inline"><semantics><msub><mi mathvariant="script">L</mi><mn>1</mn></msub></semantics></math></inline-formula> adaptive control method in the presence of loss of actuator effectiveness fault. The hypersonic model considers the uncertainties caused by the features of nonlinearities and couplings. Elasticity is taken into account in hypersonic vehicle modeling which makes the model more accurate. A velocity <inline-formula><math display="inline"><semantics><msub><mi mathvariant="script">L</mi><mn>1</mn></msub></semantics></math></inline-formula> adaptive controller and an altitude <inline-formula><math display="inline"><semantics><msub><mi mathvariant="script">L</mi><mn>1</mn></msub></semantics></math></inline-formula> adaptive controller are designed to control flexible hypersonic vehicle model with actuator loss fault. A PID controller is designed as well for comparison. Finally, the simulation results are used to analyze the effectiveness of the controller. Compared to the results of PID controller, <inline-formula><math display="inline"><semantics><msub><mi mathvariant="script">L</mi><mn>1</mn></msub></semantics></math></inline-formula> controllers have better performance.
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