A control method for spacecraft attitude maneuver and a convergence time estimation method thereof

CN116909302BActive Publication Date: 2026-08-28CHANGZHOU INST OF TECH
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Patent Information

Application Number
CN202310858149.2
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2023-07-13
Publication Date
2026-08-28
Estimated Expiration
2043-07-13

AI Technical Summary

Technical Problem

[0004]以上已公开的专利都是基于终端滑模提出了航天器有限时间姿态控制方法，这些方法都能实现航天器姿态机动的高精度、更快速、刚扰动能力强等要求，然而利用终端滑模设计有限时间控制器的方法存在“控制奇异与收敛时间矛盾性”的问题，即要么控制器无奇异但没法给出估算收敛时间的完整上界，要么可以估算收敛时间完整上界但控制存在奇异现象

Benefits of technology

[0029]相比于现有技术，本发明的优点在于：1、本发明针对航天器姿态机动控制问题，提出一种基于终端滑模的有限时间姿态控制方法，相比传统线性控制(如PID控制)，本发明提出的方法具有收敛快、精度高、抗扰动能力强等优点，能满足日益复杂航天任务对姿态机动和姿态稳定的高要求。

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Abstract

The application discloses a kind of spacecraft attitude maneuver control method and its convergence time estimation method, comprising the following operating steps: S1: establishing spacecraft attitude kinematics and dynamics model, design a kind of nonsingular terminal sliding mode variable and a kind of attitude controller;S2: propose a kind of S1 in nonsingular terminal sliding mode variable sliding phase convergence time estimation method;S3: propose a kind of S1 in nonsingular terminal sliding mode variable to reach phase convergence time estimation method.Summing up, the application is aimed at spacecraft attitude maneuver control problem, designs a kind of nonsmooth attitude control method based on terminal sliding mode, the complete convergence time upper bound expression of terminal sliding mode variable reach phase and sliding phase in attitude maneuver process can be given in this method, and attitude closed loop system is finite time stable, thus has high precision and fast maneuvering stable characteristics.
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Citation Information

Patent Citations

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