A method for real-time planning of maneuvering targets in a moving coordinate system by a spacecraft

Abstract

A method for real-time planning of a maneuvering target of a spacecraft in a moving coordinate system. First, the initial calculation of conventional attitude maneuvering planning is performed to obtain the initial quaternion and maneuvering planning parameters of the target moving coordinate system relative to the satellite orbit system, and then in each control cycle according to Maneuver planning parameter information, carry out real-time planning pre-calculation of conventional attitude maneuver planning, and obtain pre-calculation results. Finally, in each control cycle during the maneuver process, according to the real-time direction cosine matrix of the target moving coordinate system relative to the orbit system, the target moving coordinate Calculate the angular velocity of the real-time planning relative to the inertial system attitude quaternion and the real-time planning relative to the angular velocity of the inertial system, and complete the real-time planning of the spacecraft for the maneuvering target of the moving coordinate system.

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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