| 运载火箭推力故障不确定性下轨迹可达包络分析 |
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| 引用本文： | 李超兵,包为民,李忠奎,程晓明,魏才盛.运载火箭推力故障不确定性下轨迹可达包络分析[J].宇航学报,2023,44(1):25-33. |
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| 作者姓名： | 李超兵 包为民 李忠奎 程晓明 魏才盛 |
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| 作者单位： | 1. 北京大学工学院， 北京 100871；
2. 中国航天科技集团有限公司， 北京 100048；
3. 北京航天自动控制研究所， 北京 100854；
4. 中南大学自动化学院， 长沙 410083 |
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| 基金项目： | 国家重点研发计划(2021YFA0717100)；国家自然科学基金(62003371)；湖南省自然科学基金(2022JJ20081) |
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| 摘 要： | 针对运载火箭突发推力故障且故障存在不确定性的轨迹设计问题，提出了一种基于状态转移张量法(STT)的故障火箭轨迹可达包络分析方法。首先，建立了推力故障火箭的运动模型，通过构建故障火箭轨迹重规划问题，基于序列二次规划法获得了不考虑故障不确定性的重规划轨迹; 其次，基于线性协方差对非线性系统的不确定性传播进行建模，并对模型进行线性化，在此基础上提出了基于SST的运载火箭轨迹可达包络分析方法; 最后，通过与多次蒙特卡洛仿真对比验证所提方法在运载火箭轨迹可达包络定量分析中的有效性。
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| 关 键 词： | 运载火箭 推力故障 不确定性 状态转移张量 轨迹可达包络 |
| 收稿时间： | 2022-08-19 |
Trajectory Reachable Envelope Analysis of Launch Vehicle under Thrust Failure and Uncertainties |
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| LI Chaobing,BAO Weimin,LI Zhongkui,CHENG Xiaoming,WEI Caisheng.Trajectory Reachable Envelope Analysis of Launch Vehicle under Thrust Failure and Uncertainties[J].Journal of Astronautics,2023,44(1):25-33. |
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| Authors: | LI Chaobing BAO Weimin LI Zhongkui CHENG Xiaoming WEI Caisheng |
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| Affiliation: | 1. College of Engineering, Peking University, Beijing 100871, China;
2. China Aerospace Science and Technology Corporation, Beijing 100048, China;
3. Beijing Aerospace Automatic Control Institute, Beijing 100854, China;
4. School of Automation, Central South University, Changsha 410083, China |
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| Abstract: | A state transition tensor (STT)based trajectory reachable envelope analysis method is proposed in this paper for the launch vehicle under uncertain thrust failures. First, the motion model of launch vehicle under thrust drop failure is introduced. Then, by constructing the trajectory replanning problem, the sequential quadratic programming method is employed to obtain the replanned trajectory without considering the uncertainties of thrust failures. Furthermore, the uncertainty propagation model is constructed by linear covariance, and the model is linearized. The trajectory reachable envelope analysis method of launch vehicle is then proposed based on STT method. Finally, numerical examples are organized to show that the trajectory reachable envelope can be analyzed and obtained quantitatively by the proposed method compared with the monte carlo simuclations. |
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| Keywords: | Launch vehicles Thrust drop failure Uncertainty State transition tensor Trajectory reachable envelope |
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