Rotation control method and device of coarse pointing device for space optical communication

Abstract

The invention discloses a rotation control method and device of a coarse pointing device for space optical communication. The method comprises the following steps: S1, acquiring a path curve of the coarse pointing device rotating from a current position angle to a target position angle; S2, discretizing the path curve by taking the control period as a sampling period, and decomposing the data to obtain a target angle corresponding to each control period; and S3, controlling the coarse pointing device to rotate towards the target position angle until the actual position angle of the coarse pointing device is equal to the target position angle, and controlling the coarse pointing device to rotate to the target angle corresponding to the control period in each control period in the rotating process. According to the invention, the coarse pointing device stably rotates to the target position angle along with the planned path curve, the angular velocity and the angular acceleration are restrained, shaking and power fluctuation generated when the laser communication coarse pointing device works can be greatly reduced, the control stability of the whole satellite is guaranteed, the impacton a power source is reduced, and the power consumption of the satellite is reduced.

Description

technical field [0001] The invention relates to the field of space laser communication, in particular to a method and device for controlling rotation of a coarse pointing device for space light communication. Background technique [0002] The key to the successful establishment and maintenance of space optical communication optical links lies in the stability and accuracy of the coarse pointing device. At the beginning of the establishment of the optical link, the main control unit needs to control the device to point to the target according to the space position of the target satellite. The helical scan is performed in the uncertainty field through the coarse pointing device to quickly capture the target satellite. [0003] At present, the control of the coarse pointing device uses three closed-loop control of the motor, including the current loop, the speed loop, and the position loop. In the process of pre-pointing and helical scanning, if the target pointing or the targ...

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Problems solved by technology

[0003] At present, the control of the coarse pointing device uses three closed-loop control of the motor, including the current loop, the speed loop, and the position loop. In the process of pre-pointing and helical scanning, if the target pointing or the target node angle of the helical scanning is directly used for calculation and control command, the controller will quickly respond to the target position, but the response path curve is out of control. If the gap between the target pointing angle and the current angle of the actuator is too large, the angle will change sharply in a short period of time, resulting in acceleration peaks, Unstable factors such as current peak

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