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Model prediction control method of spacecraft attitude avoidance by taking consideration of flywheel dynamic characteristics

A dynamic characteristic, spacecraft technology, applied in attitude control, aircraft, adaptive control and other directions, can solve the problems of small reaction torque, affecting spacecraft attitude control, easy to reach saturation, etc.

Active Publication Date: 2018-09-14
BEIHANG UNIV
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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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  • Model prediction control method of spacecraft attitude avoidance by taking consideration of flywheel dynamic characteristics
  • Model prediction control method of spacecraft attitude avoidance by taking consideration of flywheel dynamic characteristics
  • Model prediction control method of spacecraft attitude avoidance by taking consideration of flywheel dynamic characteristics

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[0084] The following is a detailed description of the specific implementation of the present invention. It is necessary to point out that the following implementation is only used for further description of the present invention and cannot be understood as a limitation of the protection scope of the present invention. Some non-essential improvements and adjustments made still belong to the protection scope of the present invention.

[0085] The invention provides a model predictive control method for spacecraft attitude avoidance considering the dynamic characteristics of the flywheel, such as figure 1 As shown, the specific steps are as follows: firstly, according to the attitude kinematics and dynamics characteristics of the spacecraft and the rotational dynamic characteristics of the flywheel, establish the attitude model of the spacecraft including the actuator as the prediction model of the MPC; secondly, according to the sight angle of the instrument on the spacecraft And t...

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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 relates to the technical field of spacecraft control, and is mainly applied to the avoidance control of spacecraft attitude maneuver using reaction flywheel control, and specifically relates to a model predictive control method for spacecraft attitude avoidance considering the dynamic characteristics of the flywheel. Background technique [0002] In recent years, space technology has developed rapidly, and the mission requirements of orbiting spacecraft have become more and more. Therefore, spacecraft are equipped with various optical instruments, such as CCD cameras and infrared interferometers. During the operation of these instruments It is necessary to keep the line of sight from directly facing the strong light to protect the components in the instrument that are sensitive to light and temperature. Therefore, it is required that the spacecraft should be directed to avoid the direction of strong light during the attitude maneuvering proces...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04G05D1/08
CPCB64G1/244G05B13/042
Inventor 胡庆雷杨昊旸郭雷王陈亮
Owner BEIHANG UNIV
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