Real-time planning method of moving coordinate system maneuvering target by spacecraft

Abstract

A real-time planning method of a moving coordinate system maneuvering target by a spacecraft comprises the steps of: performing conventional attitude maneuvering planning initialization calculation, and obtaining an initial quaternion and a maneuvering planning parameter of a target moving coordinate system relative to a satellite orbit system; performing real-time planning pre-calculation of theconventional attitude maneuvering planning according to the maneuvering planning parameter information in each control cycle, and obtaining a pre-calculation result; and finally, calculating an attitude quaternion of real-time planning relative to an inertial system and an angular speed of real-time planning relative to the inertial system according to a real-time direction cosine matrix of the target moving coordinate system relative to an orbit system and the angular speed of the target moving coordinate system relative to the inertial system in each control cycle in the maneuvering process,and completing the moving coordinate system maneuvering target real-time planning by the spacecraft.

Description

technical field [0001] The invention relates to the field of attitude determination and control of spacecraft, in particular to a real-time planning method for a maneuvering target of a spacecraft in a moving coordinate system. Background technique [0002] Satellite attitude maneuver planning methods currently include BangBang trajectory planning, sinusoidal trajectory planning, etc., which are widely used in satellite imaging maneuvers and other tasks. However, these methods are all aimed at the situation that there is no relative movement of the coordinate system before and after the maneuver. For example, when the satellite is swinging sideways, the attitude body coordinate system before the maneuver and the target attitude body coordinate system after the maneuver are both stationary relative to the orbit coordinate system, while for The situation where the maneuvering target frame is constantly moving relative to the orbital frame is not handled well. For example, whe...

AI Technical Summary

Problems solved by technology

The dynamic adjustment caused by the deviation of attitude and attitude angular velocity affects the stability of satellite operation and the realization of maneuvering indicators

However, if the extrapolation of the sun orientation coordinate system for a certain period of time is used as the target attitude for planning, due to the uncertainty of the relative positions of the ground coordinate system before the maneuver and the sun orientation coordinate system after the maneuver, a definite extrapolation cannot be given duration to eliminate the aforementioned maneuver bias

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