Control method of satellite actuating mechanism configuration

A technology of an actuator and a control method, applied in the aerospace field, can solve the problems of short lifetime of the whole satellite, poor stability of satellite attitude control, low control accuracy, etc., and achieve the effect of improving the service life and reducing the utilization rate of the flywheel.

Pending Publication Date: 2022-07-15
CHANGGUANG SATELLITE TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defects of low control precision of the actuator in the prior art, poor control stability of the satellite attitude, and short lifetime of the entire satellite, thereby providing a control method for the configuration of the satellite actuator

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  • Control method of satellite actuating mechanism configuration
  • Control method of satellite actuating mechanism configuration
  • Control method of satellite actuating mechanism configuration

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Effect test

Embodiment 1

[0050] Embodiment 1: Choose to use the main flywheel for independent maneuvering and attitude stabilization, and the satellite realizes the maneuver from the sun-oriented three-axis stable attitude to the ground-oriented three-axis stable attitude and achieves attitude stability for imaging tasks, such as Figure 4 The shown satellite completes attitude stabilization after 300 s when the current attitude and the desired attitude have a large deviation, Figure 5 In the variation curve of the satellite maneuvering angular velocity of this embodiment, the maximum maneuvering angular velocity of the star is 0.46° / s, Image 6 The speed curves of the three main reaction flywheels and the two heterogeneous high-torque flywheels show that the entire process uses the main flywheel completely and the heterogeneous flywheel is in a state of 0 revolutions per minute (rpm).

Embodiment 2

[0051] Example 2: Carry out a combination of two tasks. First, the first task uses the main flywheel and the XY-axis heterogeneous flywheel to alternately merge and use to realize the satellite from the sun-oriented three-axis stable attitude to the ground-oriented three-axis stable attitude. For the attitude stabilization imaging task, after the second task of 500s starts, the main flywheel and the XY-axis heterogeneous flywheel are used at the same time for fast maneuvering. Figure 7 is the control deviation curve of the two tasks before and after, Figure 8 It is the attitude maneuvering angular velocity curve of the two tasks before and after. It can be seen from the figure that the maximum attitude angular velocity of the satellite is 0.46° / s when the flywheel and the flywheel are used alternately, and the maximum attitude angular velocity of the satellite is 0.80° / s when the flywheel is used at the same time. Figure 9 It is the speed curve of the main flywheel and the ...

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Abstract

The invention relates to the technical field of aerospace, in particular to a control method of a satellite execution mechanism configuration. Comprising the following steps of 1, performing flywheel heterogeneous configuration on a satellite body; step 2, calculating control moments under different use modes; 3, performing instruction distribution on the calculated control torque according to different flywheel use modes; according to the satellite execution mechanism configuration and the use strategy considering maneuvering rapidness and long service life of the satellite, the main flywheel can be used for realizing conventional attitude maneuvering and stability, and on one hand, rapid maneuvering of the satellite can be realized when the main flywheel and heterogeneous high torque are used together; on the other hand, acceleration and deceleration of the main flywheel can be avoided when the main flywheel and the heterogeneous flywheel are alternately fused for use, the utilization rate of the flywheel is reduced, and therefore the service life of a satellite is prolonged.

Description

technical field [0001] The invention relates to the technical field of aerospace, in particular to a method for controlling the configuration of a satellite actuator. Background technique [0002] With the development of aerospace technology and the increasingly fierce competition in the commercial aerospace market, the industry has higher and higher requirements for imaging efficiency and high stability brought about by the high agility of satellites. At the same time, satellites are required to have high reliability in orbit. and long life to maximize benefits. [0003] The conventional control strategy of using the reaction flywheel for attitude maneuvering and stabilization can achieve high stability of the satellite, but it is difficult to achieve high agility maneuvering of the satellite. Although the control scheme can take into account the maneuverability of the satellite and the high stability of the attitude, the algorithm is complex, the operation of the actuator...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/28
CPCB64G1/283
Inventor 陈志刚牟洪元姜曜范林东戴璐张雷
Owner CHANGGUANG SATELLITE TECH CO LTD
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