Attitude control flywheel rotating speed self-balancing control method
A technology of balance control and self-balancing, which is applied to aircrafts, astronauts, and guidance devices for astronauts. It can solve problems such as satellite attitude jitter, reduce disturbance, reduce flywheel speed zero-crossing events, and increase hardware costs. Effect
Active Publication Date: 2021-06-04
航天科工空间工程发展有限公司
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Problems solved by technology
[0004] The purpose of the present invention is to provide a self-balancing control method for attitude control flywheel speed, which can solve the problem that the flywheel speed crosses zero during the attitude control process and may cause satellite attitude shake
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[0062] In order to make the technical solution of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. The present invention is described in detail through specific examples below, but these do not constitute a limitation to the present invention. Without departing from the principles of the present invention, those skilled in the art may make changes and improvements, which should also be considered as the protection scope of the present invention.
[0063] This embodiment provides an attitude control flywheel rotational speed self-balancing control method, and the method is applied to all flywheel control systems with four oblique configurations. The flowchart of the method is as figure 1 As shown, the method includes:
[0064] S101: Carry out singular value decomposition calculation according to the installation matrix of the flywheel control system in the flywheel con...
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The embodiment of the invention discloses an attitude control flywheel rotating speed self-balancing control method. The method comprises the following steps: S101, performing singular value decomposition calculation according to an installation matrix of a flywheel control system in a flywheel configuration; S102, forming a singular matrix according to singular vectors corresponding to zero singular values in the singular values; S103, according to the flywheel rotating speed deviation and the singular matrix, performing real-time calculation in a flywheel rotating speed self-balancing algorithm module of the satellite to obtain flywheel rotating speed balance control torque of each flywheel; S104, obtaining a first control torque of each flywheel through torque distribution in a flywheel torque distribution module of the satellite according to a three-axis control torque calculated by a satellite attitude control system; S105, superposing the first control moment and the flywheel rotating speed balance control moment to obtain a second control moment of each flywheel; S106, outputting the second control torque of each flywheel to each flywheel.
Description
technical field [0001] The invention relates to the technical field of satellite attitude control, in particular to an attitude control flywheel speed self-balancing control method. Background technique [0002] The main equipment for satellite attitude control includes attitude control thrusters, moment gyroscopes, and flywheels. Attitude control thrusters and moment gyroscopes are suitable for large satellites with fast maneuvering requirements. As a small attitude control component, flywheels have small angular momentum and output The characteristic of small torque is suitable for attitude control of small satellites, and can realize high-precision attitude control of small satellites. In recent years, it has become a preferred attitude control component for small satellites represented by Internet satellites. [0003] Satellite attitude control using a flywheel is based on the principle of conservation of angular momentum. The attitude maneuver of the satellite is realiz...
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Login to View More IPC IPC(8): B64G1/24B64G1/28B64G1/10G06F17/16
CPCB64G1/244B64G1/285B64G1/10G06F17/16
Inventor 王鹏飞辛星黄丽雅金震程春晓翟峻仪
Owner 航天科工空间工程发展有限公司