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Distributed spacecraft solar panel vibration control method considering adjacent control force

A solar panel and control force technology, which is applied in the field of aerospace control systems, can solve the problems that a single controller cannot meet the control requirements, the vibration suppression time is long, and the influence of the output force coupling of adjacent control nodes on the control effect is not considered. Achieve good stable control effect, short stable convergence time, and improve the effect of anti-disturbance ability

Pending Publication Date: 2022-04-12
JILIN UNIV
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Problems solved by technology

[0004] The present invention solves the problem that when the centralized control system suppresses the vibration of a large flexible component, the vibration suppression time is long because a single controller cannot meet the control requirements; and the current distributed control method does not consider the coupling of the output force of adjacent control nodes The problem of influence and effect of actuator position on control effectiveness

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  • Distributed spacecraft solar panel vibration control method considering adjacent control force
  • Distributed spacecraft solar panel vibration control method considering adjacent control force
  • Distributed spacecraft solar panel vibration control method considering adjacent control force

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specific Embodiment approach 2

[0054] Specific embodiment two, combine Figure 1 to Figure 6 This embodiment is described. This embodiment is an embodiment of the vibration control method for distributed spacecraft solar panels considering the adjacent control force described in the first embodiment:

[0055] Apply the vibration control method of the distributed spacecraft solar panel considering the adjacent control force designed in this embodiment to the vibration suppression control of a large flexible solar panel, ignoring the torsion of the panel on the x oy plane, and only considering the panel Vibration in the z-axis direction. The actuator is installed on the sailboard, and outputs a control force to act on the sailboard according to the control requirements, so that the sailboard realizes active vibration suppression. The actuators are arranged in two columns along the x-axis of the sailboard coordinate system, such as figure 1 shown. The solar panel is 10m long, 3m wide, 0.05m thick, elastic m...

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Abstract

The invention discloses a distributed spacecraft solar panel vibration control method considering adjacent control force, relates to the field of aerospace control systems, and solves the problems that when an existing centralized control system carries out vibration suppression on a large flexible component, the vibration suppression time is long due to the fact that a single controller cannot meet the control requirement. According to the method, the solar panel is divided into sub-modules according to the mounting positions of the actuator sensors on the solar panel, the actuator sensor of each sub-module and a control circuit of the actuator sensor form a control node, a vibration equation of the sub-module is established, and according to the vibration equation, the vibration of the sub-module is calculated. The influence of the installation positions of actuators and sensors on the control effect is considered, the coupling relation between the sub-modules is analyzed, the coupling influence of output force of adjacent control nodes is considered, and a distributed self-adaptive controller is provided. According to the invention, the vibration suppression time is shorter, and the anti-interference capability is effectively improved.

Description

technical field [0001] The invention relates to the field of aerospace control systems, in particular to a method for controlling the vibration of solar panels of distributed spacecraft considering adjacent control forces. Background technique [0002] In order to ensure the stability of the spacecraft’s in-orbit operating environment and effectively suppress the vibration of the large flexible parts of the spacecraft caused by the external environment and its own attitude adjustment, the designed control systems are divided into two categories, one is the traditional centralized control system, and the other is a distributed control system. In the traditional centralized control system, when performing vibration suppression control, all the vibration information of the sailboard is collected by the sensor as the input of the system, calculated by the on-board computer, and output the control rate. This centralized control system has a certain control effect, but because th...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/02
Inventor 张刘曾庆铭赵寰宇范国伟
Owner JILIN UNIV
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