Abstract
A fault-tolerant control for launch vehicle actuator with actuator faults is proposed assuming the fault has been diagnosed in this paper. Firstly, the model for the launch vehicle with actuator failures is established considering faults. The tracking differentiator is used to process the angle signal of the program for the subsequent controller design. Using the attitude angle and angular velocity information measured by the control components, a basic controller is designed by LQR method to make the launch vehicle stable, thus a reference model with good stability is obtained. Moreover, the adaptive control law is designed in the form of integral by means of model reference adaptive control (MRAC) method to ensure attitude stability in flight. Finally, the validity of the algorithm was verified by simulation.
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Niu, Q., Li, Q., Liu, Y., Han, L., Ren, Z. (2022). Fault-Tolerant Control for Launch Vehicle Actuator Based on Adaptive Control. In: Yan, L., Duan, H., Yu, X. (eds) Advances in Guidance, Navigation and Control . Lecture Notes in Electrical Engineering, vol 644. Springer, Singapore. https://doi.org/10.1007/978-981-15-8155-7_382
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DOI: https://doi.org/10.1007/978-981-15-8155-7_382
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