火星稀薄大气进入过程伞舱组合体振荡阻尼方法研究  

Oscillation damping method for parachute and aeroshell system for Mars entry process

作　　者：韩宏伟 乔栋 崔祜涛[4] 黄翔宇[5] 滕锐[6] HAN HongWei;QIAO Dong;CUI HuTao;HUANG XiangYu;TENG Rui(School of Automation,Beijing Institute of Technology,Beijing 100081,China;Key Laboratory of Autonomous Navigation and Control for Deep Space Exploration,Ministry of Industry and Information Technology,Beijing 100081,China;School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;School of Astronautics,Harbin Institute of Technology,Harbin 150001,China;Beijing Institute of Control Engineering,Beijing 100094,China;Science and Technology on Space Physics Laboratory,China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]北京理工大学自动化学院,北京100081 [2]深空探测自主导航与控制工信部重点实验室,北京100081 [3]北京理工大学宇航学院,北京100081 [4]哈尔滨工业大学航天学院,哈尔滨150001 [5]北京控制工程研究所,北京100094 [6]中国运载火箭技术研究院空间物理重点实验室,北京100076

出　　处：《中国科学：技术科学》2020年第9期1140-1149,共10页Scientia Sinica(Technologica)

摘　　要：火星着陆探测任务中,伞舱组合体的稳定是保证EDL过程安全性以及设备工作可靠性的前提,而姿态大幅振荡是目前造成着陆舱下降过程存在安全隐患的主要原因.本文针对伞舱系统在不同阶段发生高动态耦合力冲击作用下姿态振荡问题,提出了一种基于比例反馈的主动阻尼控制方法,该方法通过将姿态角偏差指数稳定作为控制律设计的目标,推导了在着陆舱有限控制能力下的姿态振荡抑制方法,并通过李雅普诺夫稳定性分析方法,严格证明了本文所提方法的一致收敛性.最后,本文分别针对减速伞展开后和防热大底分离后的姿态振荡问题,同时进行了有、无主动阻尼下的仿真分析,结果表明,无阻尼控制的着陆舱姿态振荡难以自然衰减,而施加主动阻尼后,伞舱系统可以在短时间实现稳定,从而验证了本文所提方法在姿态稳定中的有效性和多阶段任务中的适用性.In a Mars landing exploration mission,the stability of the parachute system is a prerequisite for ensuring the safety of the entry,descent,and landing process and the reliability of the equipment operation.The large oscillation of the attitude is currently the main threat to the safety of the descent and landing process.This paper proposes an active damping control method that is based on proportional feedback for the attitude oscillation problem of the parachute system with high dynamic coupling force shock.This method performs elimination of the attitude angle deviation as the goal of the control law design.The attitude oscillation suppression method under the limited control capability of the aeroshell is introduced,and the Lyapunov stability analysis method is used to strictly prove the uniform convergence of the proposed method.Finally,this paper separately addresses the problems of attitude oscillation after parachute deployment and after heat shield separation via numerical simulation analysis with and without active damping.The results demonstrate that the parachute system can be stabilized in a short time and verify the effectiveness of the proposed method in attitude stabilization.

关 键 词：伞舱组合体 姿态振荡 主动阻尼控制 减速伞展开 防热大底分离 

分 类 号：V476.4[航空宇航科学与技术—飞行器设计]