Issue |
JNWPU
Volume 41, Number 5, Octobre 2023
|
|
---|---|---|
Page(s) | 878 - 886 | |
DOI | https://doi.org/10.1051/jnwpu/20234150878 | |
Published online | 11 December 2023 |
Research on integrated aircraft-engine control method of hypersonic vehicle based on dynamic inversion control
基于动态逆控制的高超声速飞行器飞/发一体化控制方法研究
1
School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
2
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
3
Hypersonic Technology Laboratory, National University of Defense Technology, Changsha 410073, China
4
Unmanned System Research Institute, Northwestern Polytechnical University, Xi'an 710072, China
Received:
17
November
2022
In order to reduce the influence of the coupling characteristics between the aircraft and engine of hypersonic vehicle, an integrated aircraft-engine control method of hypersonic vehicle is studied in this paper. Firstly, the control-oriented aircraft-engine integrated mathematical model of the hypersonic vehicle is established. Then, by using the nonlinear dynamic inversion (NDI) and the incremental nonlinear dynamic inversion (INDI), the outer loop control algorithm with slow attitude change and the inner loop control algorithm with fast angular rate change are respectively designed. Moreover, based on the online ontology model including aircraft-engine coupling characteristics of the hypersonic vehicle, the coupling control scheme of flight posture and engine of the hypersonic vehicle is designed in the form of control linkage. Finally, the reference model, error control, online estimation and other modules are introduced into the NDI controller to ensure the flight quality and robustness requirements of the hypersonic vehicle. The simulation results show that the aircraft-engine coupling control scheme based on the NDI achieves the expected control performance.
摘要
为了减小高超声速飞行器飞/发耦合效应对自身的影响, 开展了高超声速飞行器飞/发一体化控制研究。建立面向控制的高超声速飞行器飞/发一体化数学模型。分别采用非线性动态逆控制与增量非线性动态逆控制方法, 设计了姿态慢变外回路、角速率快变内回路控制算法。基于包含高超声速飞行器飞/发耦合特性的在线本体模型, 以操纵交联的形式设计了高超声速飞行器姿态与发动机的耦合控制方案。在非线性动态逆控制器中引入参考模型、误差控制、在线估计等模块, 保证了高超声速飞行器的飞行品质和鲁棒性要求。仿真实验结果表明, 采用了非线性动态逆控制设计的飞/发耦合控制方案达到了预期的控制性能。
Key words: hypersonic vehicle / aircraft/engine integration / nonlinear dynamic inversion / incremental nonlinear dynamic inversion
关键字 : 高超声速飞行器 / 飞/发一体化 / 非线性动态逆 / 增量非线性动态逆
© 2023 Journal of Northwestern Polytechnical University. All rights reserved.
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