Double-vector included angle limiting range determining method and system based on constraint analysis

Abstract

The invention provides a double-vector included angle limiting range determining method and a double-vector included angle limiting range determining system based on constraint analysis. The double-vector included angle limiting range determining method comprises analysis of attitude singular constraints, analysis of attitude benchmark determination error constraints, analysis of attitude maneuverability constraints and setting of a dual-vector included angle limiting range, and comprises the steps of: judging whether an attitude singularity phenomenon of attitude overturn occurs or not according to a three-axis attitude change rule determined by double vectors; according to the triaxial attitude determined by the double vectors, determining an error by analyzing an attitude reference, andjudging whether load pointing errors of an antenna, a camera and the like meet on-orbit requirements or not; judging whether angular momentum and moment meet the requirements or not by analyzing theattitude maneuver capability according to the triaxial attitude determined by the double vectors; and setting a double-vector included angle limiting range by integrating the attitude singularity constraint determined by the double vectors, the attitude reference determination error constraint and the attitude maneuver capability constraint. The double-vector included angle limiting range determining method solves the problem of determining the double-vector included angle limiting range based on constraint analysis, and is simple and easy to implement in engineering.

Description

technical field [0001] The present invention relates to the field of spacecraft attitude control, in particular to a method and system for determining the limited range of the included angle between two vectors based on constraint analysis. Background technique [0002] There are many ways to control the attitude of the spacecraft, the most commonly used is the three-axis stable attitude control method. The method is to limit the orientation of the two axes, use the right-hand rule to determine the three-axis attitude of the spacecraft, and ensure the stability of the three-axis attitude of the spacecraft. [0003] Any two-vector in space can be used as a reference to determine the three-axis attitude of the spacecraft, but affected by factors such as energy, measurement and control, the earth-centered vector, the sun vector, and the negative normal vector of the orbital plane are one of the commonly used two-vectors. If the geocentric vector and the negative normal vector ...

AI Technical Summary

Problems solved by technology

[0007] Invention patent "Large Ellipse Orbit Attitude Reference Determination Method" (public number: CN106767811A) proposes to use the earth center vector and the sun vector as the two vectors, but does not involve the angle range of the two vectors based on constraint analysis

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