Attitude stabilization for flexible spacecraft with inertia uncertainty by a sliding mode control law

被引：0
|
作者：
Wu, Ai-Guo [1 ]
Dong, Rui-Qi [1 ]
Zhang, Ying [1 ]
He, Liang [2 ]
机构：
[1] Harbin Inst Technol Shenzhen, Shenzhen 518055, Peoples R China
[2] Shanghai Aerosp Control Technol Inst, Shanghai 221116, Peoples R China
来源：
2019 12TH ASIAN CONTROL CONFERENCE (ASCC) | 2019年
基金：
中国国家自然科学基金;
关键词：
adaptive law; attitude stabilization; flexible spacecraft; inertia uncertainty; sliding mode control; ADAPTATION LAWS; UPPER-BOUNDS; TRACKING; NORM;
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
In this paper, attitude control for a flexible spacecraft with inertia uncertainty is considered. First, an adaptive law is constructed to estimate the upper bound of a certain function of the inertia uncertainty. Then, based on the proposed adaptive law, an adaptive sliding mode control law based on state feedback is established for the case while the flexible modal variables are measurable for the flexible spacecraft with inertia uncertainty. To verify the effectiveness of the presented control laws, simulations are performed in the presence of inertia uncertainty. Simulation results show that the proposed control laws attenuate the effect of inertia uncertainty successfully and the attitude states can be stabilized by the proposed sliding mode control laws.
引用
收藏
页码：1472 / 1477
页数：6
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