A Model Predictive Control Method for Spacecraft Attitude Avoidance Considering Flywheel Dynamic Characteristics

Abstract

A model prediction control method of spacecraft attitude avoidance by taking the consideration of flywheel dynamic characteristics comprises the following steps of: establishing a prediction model based on attitude dynamics of the spacecraft and dynamics of flywheels; establishing a constraint mathematic model according to the dynamic characteristics of the flywheels and an instrument angle of sight; designing a performance index function facing different task demands, and converting a control problem to a problem of solving an extreme value of a target function in equality and inequality constraint conditions; and finally, rapidly solving the problem based on the optimization method of real-time iteration. The method can process the attribute avoidance problem of the spacecraft in the execution mechanism constraint condition, can reach the comprehensive optimization of energy and time of the design of the target function, can perform processing through real-time iteration and hot start methods and can reduce the computing amount of solving the optimization problem.

Description

technical field [0001] The invention belongs to the technical field of spacecraft control, and is mainly applied to the avoidance control of spacecraft attitude maneuvers controlled by reaction flywheels, in particular to a model predictive control method for spacecraft attitude avoidance considering the dynamic characteristics of flywheels. Background technique [0002] In recent years, with the rapid development of space technology, more and more mission requirements are required for on-orbit spacecraft. Therefore, various optical instruments, such as CCD cameras and infrared interferometers, are mounted on spacecraft. During the work of these instruments, It is necessary to keep the line of sight away from directly facing the strong light, so as to protect the components in the instrument that are sensitive to light and temperature. Therefore, this requires the spacecraft to make the direction of these instruments avoid the direction of strong light during the attitude ma...

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Problems solved by technology

However, during the use of the reaction flywheel, there are also problems such as relatively small reaction torque and easy saturation, which affects the attitude control of the spacecraft.

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