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Robust Controller Design of Non-minimum Phase Hypersonic Aircrafts Model based on Quantitative Feedback Theory

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Abstract

Hypersonic aircrafts are introduced as a platform for cost-efficient access to space. However, challenging problems of control hypersonic aircrafts exist due to aerodynamic parametric uncertainties, external disturbances and unstable internal dynamics. This paper explores how to design and tune a controller with quantitative feedback theory (QFT). Furthermore, robust controllers based on QFT for longitudinal model are designed to solve the non-minimum phase problem and the large aerodynamic parameters uncertainty problem due to complex flight environment. According to the summary of the plant dynamics and control method, different performance specifications are presented and transformed into a set of design criteria in transfer function form as constrains for the controller design. Simulation results obtained with the designed controller and prefilter demonstrate that the designed robust controller can guarantee the stability of hypersonic aircraft model and satisfy the given performance specifications. Simulation comparisons to LQR control approach are performed to demonstrate the advantages of the proposed QFT robust controller.

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Acknowledgements

This work was supported by the National Natural Science Foundation of China under Grants 61873012 and 61503012.

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  1. School of Astronautics, Beihang University, Beijing, 100191, People’s Republic of China

    Zhaoying Li, Wenjie Zhou & Hao Liu

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  1. Zhaoying Li
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  2. Wenjie Zhou
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  3. Hao Liu
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Correspondence to Hao Liu.

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Li, Z., Zhou, W. & Liu, H. Robust Controller Design of Non-minimum Phase Hypersonic Aircrafts Model based on Quantitative Feedback Theory. J Astronaut Sci 67, 137–163 (2020). https://doi.org/10.1007/s40295-019-00187-y

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