Satellite attitude maneuver method for performing routing planning relative to moving coordinate system

Abstract

The invention provides a satellite attitude maneuver method for performing routing planning relative to a moving coordinate system, and aims to realize maneuver of any attitude angles and to track target attitude after maneuvering. With the method, a moving target attitude system is taken as a reference coordinate system to plan angular speed routes and attitude quaternion routes which are relative to the reference coordinate system. The routes are taken as instructions to drive the satellite maneuver, so that switch of maneuvering capture and tracking modes can be omitted, large instruction moment hopping during the whole moving target attitude tracking is eliminated, and adjusting process and stablizing time are reduced. The planned routes are simple and easy to realize.

Description

technical field [0001] The invention relates to a satellite attitude control technology, in particular to a satellite attitude maneuver method for path planning relative to a moving coordinate system, which can be used for any satellite that needs to perform attitude maneuvers. Background technique [0002] With the development of aerospace technology, the agility requirements of current satellites are getting higher and higher, which requires the satellite attitude to achieve rapid maneuvering and enter into a stable state to provide a stable satellite working platform. The existing attitude maneuvering algorithms mainly include: [0003] ①The control methods used include adaptive control, fuzzy control, genetic algorithm, etc. and a combination of related methods. The disadvantage is that the implementation of the method is generally complicated, and the actual constraints of the on-board computer in the project are not considered; [0004] ② Although some literatures hav...

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Problems solved by technology

[0003] ①The control methods used include adaptive control, fuzzy control, genetic algorithm, etc. and a combination of related methods. The disadvantage is that the implementation of the method is generally complicated, and the actual constraints of the on-board computer in the project are not considered;

[0004] ② Although some literatures have properly considered the engineering constraints, the shortcoming is that the output torque of the actuator is not taken as a constraint condition, which is far from the actual engineering;

[0005] ③Many design methods do not use the maximum output torque of the actuator during the maneuvering process. The disadvantage is that they are lacking in time optimization. When the time index requirements for attitude maneuvering are very strict, the system performance will be affected;

[0006] ④ Part of the method uses the maximum output torque of the actuator, but the method involves iterative solution calculations. The disadvantage is that the calculation amount is large and the method is complicated;

[0007] ⑤Some of the domestically launched satellites have attitude maneuvering capabilities, but their shortcoming is that the rapidity of large-angle maneuvering still lags behind the demand;

[0008] ⑥Most of the maneuvering methods give step commands without planning the maneuvering path;

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