Flexible agile satellite attitude maneuver rolling optimization control method

A satellite attitude and roll optimization technology, applied in the field of satellite attitude control, can solve the problems of easy vibration of flexible accessories, strong nonlinearity, and difficulty in meeting control requirements

Active Publication Date: 2014-10-08
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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Problems solved by technology

[0005] The present invention provides a flexible and agile satellite in order to solve the existing problems of strong nonlinearity, various constraints, and easy vibration of flexible accessories when the attitude of the flexible satellite is quickly maneuvered, which makes it difficult to meet the control requirements. Attitude Maneuvering Roll Optimization Control Method

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  • Flexible agile satellite attitude maneuver rolling optimization control method
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  • Flexible agile satellite attitude maneuver rolling optimization control method

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specific Embodiment approach 1

[0021] Specific implementation mode 1. Combination Figure 1 to Figure 4 Describe this embodiment, a flexible and agile satellite attitude maneuver rolling optimization control method, the method is implemented by the following steps:

[0022] Step A: Select the reference coordinate system, establish the attitude dynamics and kinematics equations of the satellite with flexible attachments using the pyramid configuration CMG group as the actuator, and establish the dynamic equations of the vibration of the flexible attachments in the modal coordinate system ; By defining a new state variable, establish a nonlinear state space equation for predicting the future information of satellite attitude;

[0023] Step B: According to the satellite attitude information measured at the current moment, the satellite attitude information in the predicted time domain is predicted through the discretized nonlinear state space equation, and the satellite attitude prediction output equation is e...

specific Embodiment approach 2

[0028] Specific embodiment two, combine Figure 1 to Figure 4 Describe this implementation mode, this implementation mode is an embodiment of a flexible and agile satellite attitude maneuver rolling optimization control method described in the first specific implementation mode, and its specific process is:

[0029] 1. Taking the inertial coordinate system as the reference coordinate system, the attitude dynamics of the satellite with flexible appendages with the pyramid configuration CMG group established as the actuator is:

[0030] J w · + δ T η · · + [ w × ] Jw + [ w × ] δ T η · = - H · ...

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Abstract

The invention relates to a satellite attitude maneuver control method, in particular to a flexible agile satellite attitude maneuver rolling optimization control method. The flexible agile satellite attitude maneuver rolling optimization control method resolves the problems that when rapid maneuver of an existing flexible satellite attitude is carried out, nonlinearity is strong, various constraints are provided, and a flexible accessory vibrates easily, and then the control requirement can not be met easily. A nonlinearity state space equation comprising satellite attitude dynamics, kinematics and vibration of the flexible accessory is built and used for carrying out accurate prediction of future information of the satellite attitude. A weighing optimization index for achieving rapid maneuver of the satellite attitude and restraining vibration of the flexible accessory is built, design of an expectation control law is carried out through a nonlinearity model prediction control method, the planned expectation moment is shaped based on the input shaping technology, the manipulation law of a CMG group is designed through a robust pseudo-inverse method, the expectation control moment obtained after input shaping serves as input, a frame angular speed of each CMG is planned, and large-angle rapid maneuver control over the satellite attitude restraining vibration of the flexible accessory is achieved.

Description

technical field [0001] The invention relates to the technical field of satellite attitude control, in particular to a satellite attitude maneuver control method, which is especially suitable for a large-angle rapid maneuver control process of a satellite attitude with a flexible attachment. Background technique [0002] With the rapid development of space mission planning, there is an increasing demand for the ability of the satellite attitude to perform large-angle rapid maneuvers in a short period of time, that is, the satellite needs to have the agility of the attitude. Compared with traditional satellites, this kind of satellite with fast maneuverability can greatly increase the range of earth observation, increase the communication time with ground stations, and provide guarantee for a variety of space smart imaging modes. [0003] In order to realize the rapid maneuvering of satellite attitude, on the one hand, a new type of high-moment satellite attitude actuator is a...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
Inventor 金光范国伟戴路徐开杨秀彬常琳
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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