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.
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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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