| 引用本文: | 窦立谦,李逸群,张秀云,李智禹,宗群.面向机动的临近空间飞行器自适应协调控制[J].哈尔滨工业大学学报,2023,55(7):141.DOI:10.11918/202111007 |
| DOU Liqian,LI Yiqun,ZHANG Xiuyun,LI Zhiyu,ZONG Qun.Maneuver-oriented adaptive coordination controlofnear space vehicle[J].Journal of Harbin Institute of Technology,2023,55(7):141.DOI:10.11918/202111007 |
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| 摘要: |
| 为提高临近空间飞行器的机动性能,提出一种结合推力矢量的新型自适应滑模控制方法,并搭建闭环最优控制分配系统,实现气动舵面与矢量喷管最优分配,保证飞行器稳定机动飞行。首先为应对机动飞行环境中复杂不确定,设计新型自适应滑模控制器,放宽了现有自适应滑模控制不确定有界性限制,获得确保姿态角稳定跟踪的期望控制力矩。引入推力矢量技术的临近空间飞行器存在多种控制输入,控制分配是机动飞行控制的关键。其次为确保机动飞行稳定安全,从稳定性角度提升分配性能,设计闭环最优控制分配策略,将期望控制力矩精确稳定地分配到执行器,完成气动舵面和矢量喷管协调控制,实现机动飞行中姿态角对参考指令的稳定跟踪。仿真结果表明:推力矢量技术对于扩大临近空间飞行器横纵方向姿态角变化范围具有有效性,同时验证了所设计控制策略能够在复杂不确定影响下保证飞行姿态稳定。 |
| 关键词: 临近空间飞行器 机动性 推力矢量 自适应滑模控制 闭环控制分配 |
| DOI：10.11918/202111007 |
| 分类号:TP273 |
| 文献标识码:A |
| 基金项目:国家自然科学基金(0,9,4,6,62022060) |
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| Maneuver-oriented adaptive coordination controlofnear space vehicle |
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DOU Liqian,LI Yiqun,ZHANG Xiuyun,LI Zhiyu,ZONG Qun
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(School of Electrical Automation and Information Engineering, Tianjin University, Tianjin 300072, China)
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| Abstract: |
| To solve the maneuvering control problem, a new adaptive sliding mode control combined with thrust vector is proposed, and a closed-loop optimal control allocation system is built to realize the optimal allocation of aerodynamic rudder and vector nozzle ensuring stable maneuvering flight of the near space vehicle. To cope with the complex uncertainty in the maneuvering flight environment, a new adaptive sliding mode controller is designed to relax the limit of uncertainty boundedness assumption of the typical adaptive sliding mode control, and obtain the expected control torque to ensure the stable tracking of attitude angle. Control allocation is the key to maneuver flight control because there are many control inputs for the near-space vehicle with thrust vector technology. To ensure the stability and safety of maneuvering flight, an optimal closed-loop optimal control distribution system was designed to improve the distribution performance from the perspective of stability. The expected control torque is accurately and stably distributed to actuators, completing the coordinated control of the aerodynamic rudders and the vector nozzles, and achieving the stable tracking of the reference command by the attitude angle during the maneuvering flight. The simulation results verify the effectiveness of thrust vector technology for expanding the range of attitude angles in the horizontal and vertical directions of near space vehicles, and prove that the designed controller can ensure flight attitude stability under the influence of complex uncertainties. |
| Key words: near space vehicle maneuverability thrust vector adaptive sliding mode control closed-loop optimal control allocation |
