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Control method for united actuating mechanism of flexible agile satellite

A joint execution and control method technology, applied in the field of satellite attitude control, can solve problems such as strong nonlinearity, difficulty in meeting control requirements, and easy vibration, and achieve the effect of attitude control

Active Publication Date: 2016-12-14
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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Problems solved by technology

[0005] In order to solve the existing problems of fast maneuvering or high-precision tracking control for flexible satellite attitudes, the present invention has the characteristics of strong nonlinearity, various constraints, and easy vibration of flexible accessories, which makes it difficult to meet the control requirements. A joint actuator control method for a flexible and agile satellite

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  • Control method for united actuating mechanism of flexible agile satellite
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  • Control method for united actuating mechanism of flexible agile satellite

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specific Embodiment approach 1

[0023] Specific implementation mode 1. Combination Figure 1 to Figure 4 Describe this embodiment, the joint actuator control method of the flexible agile satellite, the method is realized by the following steps:

[0024] Step A: select the inertial coordinate system as the reference coordinate system, set up the flexible satellite attitude dynamics and kinematics equations with the pyramid configuration CMG group and the reaction flywheel as the actuator; take the modal coordinate system of the flexible attachment as the benchmark, establish Dynamic equations for the vibration of the flexible attachment;

[0025] Step B: define a new state variable, obtain the nonlinear continuous state space equation for the optimal trajectory planning of the frame angular velocity of the CMG group and predict the future information of the satellite attitude based on the three equations established, and obtain the discreteness of the equation through the discretization method into the form;...

specific Embodiment approach 2

[0032] Specific embodiment two, combine Figure 1 to Figure 6 This implementation mode is described. This implementation mode is an embodiment of the joint actuator control method of the flexible agile satellite described in the first specific implementation mode. The specific process is as follows:

[0033] 1. Taking the inertial coordinate system as the reference coordinate system, the attitude dynamics of the established flexible satellite with joint actuators is:

[0034] I w · + σ T η ·· + [ w × ] I w + [ w × ] σ T η · = - H · C M G ...

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Abstract

The invention relates to a control method for a united actuating mechanism of a flexible agile satellite, relates to the technical field of satellite attitude control, and solves the problems that when rapid maneuver tracking control or high-precision tracking control is performed on the attitude of a conventional flexible satellite, the conventional flexible satellite has the characteristics that the conventional flexible satellite is high in nonlinearity and under multiple limits, and flexible accessories are easy to vibrate, so that control demands are difficult to meet. In accordance with the flexible agile satellite which is used for uniting two actuating mechanisms, and through the combination of the flexible satellite attitude dynamics, the kinematics and vibration equations of the flexible accessories, a nonlinear state-space equation which faces an optimum track programming of the attitude of the satellite and forecasts future attitude information is established; based on that composite indicators including attitude maneuver rapidity, flexible accessory vibration suppression, CMG group singularity and the like are established, and based on a pseudospectral method, the discretization of original continuous optimization problem is realized, and the optimum track of the maneuvering of the satellite attitude and the optimum track of the angular speed of a CMG group framework are calculated; and based on a nonlinear model predictive control technology, the control of a reaction flywheel is designed.

Description

technical field [0001] The invention relates to the technical field of satellite attitude control, in particular to a joint actuator control method of a flexible agile satellite, which is especially suitable for large-angle rapid maneuvering and high-precision tracking control process of satellite attitude with flexible accessories. Background technique [0002] At present, my country's remote sensing optical satellites usually adopt the push-broom imaging mode of sub-satellite point and side swing, which requires the satellite attitude control system to have certain attitude maneuverability and high attitude stability after maneuvering. In order to solve this problem, the existing technology mainly reserves a long enough maneuvering and stabilization time to overcome the attitude fluctuation caused by flexible attachments or disturbing moments. But this greatly limits the application efficiency of remote sensing satellites. In order to shorten the gap with the technical le...

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/242B64G1/247
Inventor 范国伟常琳杨秀彬王旻徐伟王绍举金光
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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