[1]张 勃,蔡远利. 月面定点软着陆次优制导控制一体化设计[J].控制与信息技术(原大功率变流技术),2019,(04):1.[doi:10.13889/j.issn.2096-5427.2019.04.100]
　ZHANG Bo,CAI Yuanli. Integrated Suboptimal Guidance and Control for Lunar Pinpoint Soft Landing[J].High Power Converter Technology,2019,(04):1.[doi:10.13889/j.issn.2096-5427.2019.04.100]
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 月面定点软着陆次优制导控制一体化设计()
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《控制与信息技术》（原《大功率变流技术》）[ISSN:2095-3631/CN:43-1486/U]

卷:
期数:
2019年04期
页码:
1
栏目:
出版日期:
2019-08-05

文章信息/Info

Title:
 Integrated Suboptimal Guidance and Control for Lunar Pinpoint Soft Landing
作者:
 张 勃; 蔡远利
 （西安交通大学 电子与信息工程学院，陕西 西安 710049）
Author(s):
 ZHANG Bo;  CAI Yuanli
 ( School of Electronic and Information Engineering, Xi’an Jiaotong University, Xi’an, Shaanxi 710049, China )
关键词:
 ; 月面定点软着陆; ZEM/ZEV; 反步法; 制导控制一体化; 姿态控制; 轨迹跟踪
Keywords:
 ; Luner pinpoint soft landing;  ZEM/ZEV;  backstepping control;  integrated guidance and control;  attitude control;  trajectory tracking
分类号:
V4
DOI:
10.13889/j.issn.2096-5427.2019.04.100
文献标志码:
A
摘要:
 针对月面定点软着陆制导系统和控制系统分开设计带来的精度欠佳问题，提出了一种基于改进的ZEM/ZEV（zero-effort-miss/zero-effort-velocity）方法与反步控制方法的次优制导控制一体化设计方法。首先，对传统的ZEM/ZEV方法进行必要的改进，使其能够满足飞行安全的需要和飞行末端对于加速度的约束；其次，将反步法与改进后的ZEM/ZEV方法相结合，设计定点软着陆制导控制一体化系统； 最后，对整个系统的稳定性进行了分析。标称仿真及蒙特卡洛分析结果表明，本文所提出的方法具有更好的鲁棒性、更高的制导控制精度。
Abstract:
 An integrated guidance and control method is proposed in this paper for lunar pinpoint soft landing to deal with the mismatch between the guidance system and control system in conventional separating design philosophy. The method is based on an improved ZEM/ZEV (zero-effort-miss/zero-effort-velocity) method and the back-stepping control technique. Firstly, the ZEM/ZEV algorithm is improved and extended to satisfy the flight safety and terminal accelerate constraint. Secondly, combining the improved ZEM/ ZEV method with the back-stepping technique, we design an integrated guidance and control scheme for the lunar pinpoint soft landing. Finally, the stability of the whole system is analyzed and extensive simulations are conducted. The testing results of nominal simulation and Monte Carlo analysis show that the proposed method is more accurate and more robust than the conventional separating designed one.

参考文献/References:

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[8] ZHANG F, DUAN G. Integrated translational and rota-tional control for the terminal landing phase of a lunar module[J]. Aerospace Science and Technology, 2013, 27(1): 112-126.
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备注/Memo

备注/Memo:
 收稿日期：2019-05-15
作者简介：张勃（1988—），男，博士，助理研究员，从事飞行器制导与控制研究工作。
更新日期/Last Update: 2019-08-02