Saturated sliding mode variable structure control method for rapidly maneuvering attitudes of satellites

Abstract

The invention discloses a saturated sliding mode variable structure control method for rapidly maneuvering attitudes of satellites. The saturated sliding mode variable structure control method includes steps of 1, acquiring current attitudes of the satellites and acquiring attitude errors of the current attitudes of the satellites relative to target attitudes; 2, determining bandwidths, damping coefficients, the maximum torque of actuating mechanisms, torque regulation coefficients and fundamental frequencies of flexible accessories, and computing control parameters for rapidly maneuvering the attitudes of the satellites; 3, computing saturated sliding mode surfaces of the satellites in rolling directions and computing linear sliding mode surfaces of the satellites in pitching and yawing directions; 4, acquiring control torque by means of computation; 5, acquiring corresponding control instructions for the actuating mechanisms by the aid of the control torque acquired in the step 4, transmitting the instructions to the corresponding actuating mechanisms and controlling the actuating mechanisms to rapidly maneuver the attitudes of the satellites. The saturated sliding mode variable structure control method has the advantages that the method is simple and reliable and is low in computational complexity, the satellites can be rapidly maneuvered and stabilized by the aid of the saturated sliding mode variable structure control method, accordingly, the attitude maneuvering time can be shortened, and the saturated sliding mode variable structure control method is obviously superior to other methods.

Description

technical field [0001] The invention relates to a satellite attitude control method, in particular to a saturated sliding mode variable structure control method for satellite rapid attitude maneuvering. Background technique [0002] With the improvement of satellite user requirements, many satellites require the attitude control system to not only achieve high-precision and high-stability control, but also have the ability to quickly maneuver in order to shorten the revisit cycle. In the process of satellite attitude maneuvering, the acceleration, constant speed, and deceleration stages of the satellite basically depend on the ability of the actuator, and have little to do with the algorithm; but in the rapid stabilization stage, the rapidity of convergence and stability depends entirely on the algorithm. In the prior art , the algorithm is not reliable, and the amount of calculation is too large, which leads to the slow speed and low reliability of the attitude maneuver of ...

AI Technical Summary

Problems solved by technology

In the process of satellite attitude maneuvering, the acceleration, constant speed, and deceleration stages of the satellite basically depend on the ability of the actuator, and have little to do with the algorithm; but in the rapid stabilization stage, the rapidity of convergence and stability depends entirely on the algorithm. In the prior art , the algorithm is not reliable, and the amount of calculation is too large, which leads to the slow speed and low reliability of the attitude maneuver of the satellite

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