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A control method for an attitude control thruster

An attitude control and control method technology, applied in the field of satellite guidance, navigation and control, can solve the problems of poor attitude control accuracy, weaken attitude control ability and timeliness, affect the efficiency and accuracy of orbit control, and improve the anti-interference ability. Effect

Active Publication Date: 2019-08-30
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This scheme will weaken the control ability and timeliness of the attitude. When the satellite receives a small disturbance torque, this scheme is completely feasible; The use of satellites will cause severe flexural jitter and poor attitude control accuracy, which will affect the efficiency and accuracy of orbit control

Method used

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  • A control method for an attitude control thruster
  • A control method for an attitude control thruster
  • A control method for an attitude control thruster

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Embodiment Construction

[0028] The steps of the method of the present invention will be further described below in conjunction with the drawings and embodiments.

[0029] Such as figure 1 Shown is a schematic layout diagram of the thrusters ZK1-ZK6. Such as figure 2 As shown, the control method of attitude control thruster of the present invention comprises the following steps:

[0030] Step 1. The on-board control software calculates the pulse width in three directions according to the attitude control algorithm;

[0031] Step 2. The on-board control software calculates the pulse width and performs limit processing for the two axes that need to reuse the thruster;

[0032] Step 3: The on-board control software superimposes the limited pulse width and sends it to the multiplexed thruster.

[0033] 1) Calculate the pulse width in three directions according to the attitude control algorithm

[0034] The pulse width in three directions is: T oni_mid

[0035] Among them, i=x, y, z, corresponding ...

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Abstract

The present invention provides a control method for an attitude control thruster, comprising the following steps: step 1, the on-board control software calculates the pulse widths in three directions according to the attitude control algorithm; The two axes, calculate the pulse width and perform limiting processing; step 3, the on-board control software superimposes the limited pulse width and sends it to the multiplexed thruster. The present invention realizes simultaneous two-axis control and improves the anti-interference ability of the attitude control by performing equal-proportional superposition on the pulse width of the thrusters multiplexed by the two-axis control.

Description

technical field [0001] The invention relates to satellite guidance, navigation and control technology, in particular to a control method for an attitude control thruster. Background technique [0002] As satellites carry more and more functions, their structure is also more and more loaded. Therefore, due to the limitation of the thruster layout, the attitude control thrusters in the three axes of the satellite cannot be completely independent. The phenomenon of thruster multiplexing often occurs, that is, a certain thruster is required for both direction controls. Usually, the current solution is to adopt a certain strategy for time-division multiplexing, that is, only one-way control is performed at the same time. This scheme will weaken the control ability and timeliness of the attitude. When the satellite receives a small disturbance torque, this scheme is completely feasible; The use of satellites will cause severe flexural jitter and poor attitude control accuracy, ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/245
Inventor 张艳召陈为伟石晓涵张云霞张增安
Owner SHANGHAI AEROSPACE CONTROL TECH INST