Initial attitude capture control method and system of spacecraft

Abstract

The invention provides an initial attitude capture control method and system of a spacecraft. The initial attitude capture control method of the spacecraft includes the steps that a three-shaft magnetmoment device is used for applying a control magnetic moment to the spacecraft according to the change rate of terrestrial magnetism on a satellite, and a speed damping stage is controlled; and a counteractive wheel set is used for spinning, three-shaft wheel control is applied to the spacecraft according to attitude information of the spacecraft, meanwhile, the control magnetic moment applied bythe three-shaft magnet moment device to the spacecraft is removed, and a sun capture stage is controlled. Only counteractive wheels and the magnet moment device are adopted as attitude control components, measures for dealing with the too large satellite and rocket separation deviation are considered, speed damping is applied firstly, the condition that the counteractive wheels are not saturatedserves as a precondition, meanwhile, in the sun capture stage, three-shaft wheel control is applied only depending on magnetometer information and sun sensor information, and initial capture control can be finished.

Description

technical field [0001] The invention relates to the technical field of satellite control, in particular to an initial attitude capture control method and system of a spacecraft. Background technique [0002] Due to the particularity of satellites, once a fault occurs during in-orbit flight, it is often difficult to make up for it through maintenance like other ground products. Therefore, in the development of satellites, how to ensure that satellites can safely and reliably complete their tasks in orbit has become their primary task. The safety of the satellite in orbit is divided into two stages: the first stage is the initial normal safety capture of the orbit; the second stage is the completion of the normal safety guarantee task. The initial normal and safe capture of the first stage of orbiting, that is, how to eliminate the attitude deviation caused by the separation of the satellite and the rocket at the initial stage of satellite orbiting, and achieve the initial cap...

AI Technical Summary

Problems solved by technology

[0005] In view of the shortcomings of the prior art described above, the purpose of the present invention is to provide a method and system for controlling the initial attitude capture of a spacecraft, which is used to solve the problem of complex installation structures caused by the need for a propulsion system when the initial capture of a spacecraft enters orbit in the prior art. , the problem of low security

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