八推力器结构航天器的控制分配方法

By adopting an eight-thrust structure layout and control allocation method, the problems of large number of thrusters and complex calculations for microsatellites are solved, achieving low-cost and highly robust control force/torque allocation, which is suitable for attitude-orbit coupling control and general orbit control of microsatellites.

CN121376220BActive Publication Date: 2026-07-17HARBIN INST OF TECH
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
HARBIN INST OF TECH
Filing Date
2025-12-10
Publication Date
2026-07-17

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Abstract

一种八推力器结构航天器的控制分配方法，属于航天器控制技术领域。本发明针对现有航天器的推力器数量降低后不能满足各方向力 / 力矩的解耦控制需求的问题。包括在航天器上布局八个推力器，使八个推力器在结构安装坐标系中满足轴对称分布，且喷口朝向规避限制区域以及喷口轴线规避整星结构中心区域的质心偏移范围；对于期望单轴力与期望三轴力矩的组合控制，以四个推力器的点火总时长最长为目标建立关系式，计算每个推力器的点火时长；对于期望三轴力与期望三轴力矩的组合控制：在八个推力器中选择六个推力器建立点火时长与期望三轴力及期望三轴力矩的关系式，计算六个推力器的点火时长。本发明用于航天器的点火控制。
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