Satellite attitude control method based on variable control periods

Abstract

The invention discloses a satellite attitude control method based on variable control periods. The satellite attitude control method includes the steps of S1, selecting corresponding control periods and controller parameters according task requirements; S2, using original data collected by a gyro to calculate inertial angular speed according to the control periods; S3, using attitude information output by an attitude sensor to calculate a satellite attitude determined angle; S4, using the inertia angular speed obtained in S2 and the attitude determined angle obtained in S3 to calculate controlmoment; S5, using the control moment to transmit control pulse width to an actuator; S6, returning to S1 to repeat a new round of satellite attitude control to achieve variable-period satellite attitude control. The satellite attitude control method has the advantages that different control periods and controller parameters are selected according to different task requirements, restriction of thecalculation quantity of attitude control tasks and computer hardware conditions is broken through, and high-precision transfer orbital control and high-precision, long-term and reliable earth observation tasks are completed.

Description

technical field [0001] The invention relates to the technical field of satellite attitude control, in particular to a satellite attitude control method based on a variable control period. Background technique [0002] Satellite attitude control adopts a discrete digital control method, and its control period is restricted by the following two aspects: 1. The selection of the control period is restricted by the control bandwidth of the system and the characteristics of the control object; 2. The control period is also affected by the calculation amount and Computer hardware constraints. If the control cycle is selected too long, it will bring a large delay to the system, thus affecting the stability of the attitude control system, especially for satellite orbit change control and fixed-point capture tasks, because the system responds quickly, in order to ensure system stability It is required that the control of the system has a high sampling frequency for sampling and contr...

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Problems solved by technology

If the control cycle is selected too long, it will bring a large delay to the system, thus affecting the stability of the attitude control system, especially for satellite orbit change control and fixed-point capture tasks, because the system responds quickly, in order to ensure system stability It is required that the control of the system has a high sampling frequency for sampling and control (the control cycle is generally selected to be no more than 100ms). According to the requirements of earth observation tasks, the number of attitude sensors that are turned on is the largest, and high-precision attitude determination technology and attitude control technology are used. The system has a large amount of calculation, and the data collection of the sensors is completed with the existing space-borne CPU computing power. It takes at least 200ms for the calculation and sending of control commands and processing, trajectory recursion and attitude determination

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