Abstract
With the advantages in direct measurement and control of the flight overload and its change rate, feedback of angular acceleration has become perspective for the flight control system of high maneuvering aircrafts. In this contribution, an enhanced acceleration autopilot with the angular acceleration feedback is designed for the pitch channel of tail-controlled missiles. The linear quadratic approach is implemented to determine the feedback gain of two-loop autopilots. To investigate the superiority of the angular acceleration feedback over the traditional angular rate feedback, a criterion named degree of output controllability (DOC) has been modified for evaluating the output controllability of the system with different feedback constructures. Stability and controllability analysis is carried out through numerical simulations for both kinds of autopilots with different static stability properties. The results show that the static instability and the feedback of angular acceleration is able to enhance the controllability of the two-loop autopilot.
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This research is supported by National Natural Science Foundation (NNSF) of China under Grant 61906016.
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Hu, Y., Shen, K., Neusypin, K.A., Shi, J., Zheng, J. (2023). Controllability Analysis of the Autopilot with Angular-Acceleration Feedback. In: Yan, L., Duan, H., Deng, Y. (eds) Advances in Guidance, Navigation and Control. ICGNC 2022. Lecture Notes in Electrical Engineering, vol 845. Springer, Singapore. https://doi.org/10.1007/978-981-19-6613-2_86
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DOI: https://doi.org/10.1007/978-981-19-6613-2_86
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