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浙江大学学报(工学版)
浙江大学学报(工学版)
计算机技术、控制技术     
基于稳定性判据的高超声速复合控制方法
杨春宁, 方家为, 李春, 葛晖
1.浙江大学 航空航天学院,浙江 杭州 310027
2.上海航天控制技术研究所,上海 201109
Hypersonic vehicle blended control methodology based on stability criterion
YANG Chun ning, FANG Jia wei, LI Chun, GE Hui
1.School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China;
2. Shanghai Institute of Spaceflight Control Technology, Shanghai 201109, China
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摘要：

针对传统直气复合控制系统侧喷发动机开启策略对先验数据的依赖性较强,导致鲁棒性较差的问题,提出基于稳定性判据的直气复合控制方法.根据高超声速飞行器模型推导稳定性判据,按照该判据预测飞行器的稳定状态,当飞行器即将失稳时开启侧喷发动机,及时增加直接力矩,控制飞行器稳定.该方法不依赖先验数据,可满足飞行器高马赫数下的稳定飞行和高机动性要求.通过建立全状态六自由度高超声速模型进行仿真研究,结果表明所提出的控制器具有较好的抗干扰能力,比传统控制策略鲁棒性更强.
Abstract:
The traditional strategy to open the side jet in blended control system was strongly dependent on priori data, which led to poor robustness, therefore, a blended control methodology based on stability criterion was proposed. According to hypersonic vehicle model, the stability criterion was deduced to predict the vehicle stability. When the vehicle was nearly unstable, side force moment was added by opening the side jet engines to control the vehicle. This method does not rely on priori data, and it can ensure the steady flight and high maneuverability in high Mach flight. The full state six-degrees of freedom hypersonic vehicle model was established to finish the simulation, results indicate that the proposed method has better performance on disturbance rejection, and is more robust than traditional control strategy.
出版日期: 2017-03-06
CLC:  V 249.122  
基金资助:

上海航天科技创新基金资助项目(SAST2015085)
作者简介: 杨春宁(1970—),男,副研究员,从事飞行器建模与控制等研究. ORCID: 0000-0001-7225-4286. E-mail: chnyang@zju.edu.cn
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杨春宁, 方家为, 李春, 葛晖. 基于稳定性判据的高超声速复合控制方法[J]. 浙江大学学报(工学版), 10.3785/j.issn.1008-973X.2017.02.027.

YANG Chun ning, FANG Jia wei, LI Chun, GE Hui. Hypersonic vehicle blended control methodology based on stability criterion. JOURNAL OF ZHEJIANG UNIVERSITY (ENGINEERING SCIENCE), 10.3785/j.issn.1008-973X.2017.02.027.

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