A roll optimization control method for flexible and agile satellite attitude maneuver

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

Active Publication Date: 2016-12-07
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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  • A roll optimization control method for flexible and agile satellite attitude maneuver
  • A roll optimization control method for flexible and agile satellite attitude maneuver
  • A roll optimization control method for flexible and agile satellite attitude maneuver

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

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Abstract

A flexible and agile satellite attitude maneuver rolling optimization control method, which relates to a satellite attitude maneuver control method, solves the existing characteristics of strong nonlinearity, various constraints, and easy vibration of flexible accessories when performing rapid maneuvers for flexible satellite attitudes , which leads to problems such as difficulty in meeting the control requirements. A nonlinear state-space equation including satellite attitude dynamics, kinematics and vibration of flexible attachments is established to accurately predict the future information of satellite attitude. The weighted optimization index for rapid maneuvering of satellite attitude and vibration suppression of flexible attachments is established, and the expected control law is designed by using the nonlinear model predictive control method. Based on the input shaping technology, the planned expected moment is shaped, and the robust pseudo-inverse method is used The control law of the CMG group is designed, and the frame angular velocity of each CMG is planned by taking the expected control torque after shaping as the input, so as to realize the large-angle rapid maneuvering control of the satellite attitude that suppresses the vibration of the flexible attachment.

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 Patents(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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