首页|基于漏斗策略的航天器高精度姿态控制器设计

基于漏斗策略的航天器高精度姿态控制器设计

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针对一类具有外部扰动的航天器控制系统，提出一种基于漏斗策略的高精度姿态控制方法，从而对整个跟踪控制轨迹进行规划，保证控制误差时刻满足设计需求，有效提升控制系统动态性能与品质。首先，对所提出姿态控制策略的跟踪性能进行理论分析，结果表明如果姿态控制误差初值位于根据性能需求设计的漏斗区域内，则在后续任意时刻跟踪误差将始终位于该动态性能漏斗中。在此基础上，考虑到实际工程应用中航天器系统控制信号的有界性需求，给出性能漏斗的优化设计方法，从而保证在输入幅值约束下控制系统的动态性能。最后通过数值仿真验证了所提出航天器姿态漏斗控制策略设计方法及理论分析结果的正确性和有效性。
Toward funnel strategy based high-precision attitude controller design for spacecraft
In this work,we propose one type of high-precision funnel control strategy to achieve attitude control for spacecraft control systems with external disturbances,based on which we program the whole control process such that the control error satisfies the design requirements.Firstly,we investigate the proposed funnel control strategy's transient performance.It is shown that if the initial value of the attitude tracking error is located in the funnel,which is designed based on the requirements of control precision,the tracking error can be guaranteed in this funnel at any time.Furthermore,considering the criteria for control value,we revise the design for the funnel function,ensuring the transient performance of the attitude control system.Finally,the proposed funnel control strategy and theoretic analysis are verified by numerical simulation,which shows the correctness and effectiveness.

attitude tracking control for spacecraftfunnel control strategyprescribe error performanceinput constraintextended state observerdisturbance rejection

黄元、魏春岭、严晗、郝仁剑

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北京控制工程研究所空间智能控制技术国家重点实验室,北京 100190

航天器姿态跟踪控制 漏斗控制策略 预设误差性能 输入幅值约束 扩张状态观测器 扰动抑制

国家自然科学基金国家自然科学基金北京市科技新星计划

U21B600161873029Z201100006820102

2024

10.13195/j.kzyjc.2022.1642

控制与决策
东北大学

控制与决策

CSTPCD北大核心
影响因子：1.227
ISSN：1001-0920
年,卷(期)：2024.39(5)
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