A multi-level compound control method for spacecraft coarse and fine layering speed combined with main and quilt

Abstract

The present invention relates to a multi-stage composite control method for the combination of coarse and fine layering speed of a spacecraft, and the master and quilt are integrated. The idea of ​​layered control in the star-load-fast mirror three-stage system is as follows: 1) The three-stage control of the fast mirror adopts a guide star The sensor is the measuring element, the fast mirror actuator is used as the actuator, and the PID controller is used to realize the ultra-high-precision pointing control of the roll-pitch axis of the fast mirror. 2) Secondary control of the load: the load star sensor, the micrometer gyroscope and the FSM eddy current are used as the measuring elements, the active pointing ultra-static platform (VIPPS) actuator is used as the actuator, and the PID controller is used to realize the high-precision pointing control of the load; 3) First-level control of the star: gyroscope, load star sensor and VIPPS eddy current are used as the measuring elements, the momentum wheel is used as the actuator, and the PID controller is used to realize the coarse pointing control of the star.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and relates to a three-stage attitude control system and a control method for realizing a star body-load-fast mirror of a spacecraft. Background technique [0002] At present, spacecraft generally use components containing high-speed rotors such as flywheels and control moment gyroscopes as actuators for attitude control systems. These high-speed rotating parts will inevitably produce high-frequency jitter and micro-vibration, which directly affect the working performance of the load. This cannot meet the requirements of space missions such as astronomical observations and extremely high-resolution earth observations that require high-performance control of optical loads. The spacecraft multi-level compound control system was born to meet the demand for high-precision attitude control of this type of optical load. The spacecraft multi-level composite control system refers to the space...

AI Technical Summary

Problems solved by technology

The flexible vibration and high-frequency micro-vibration existing in the spacecraft star are directly transmitted to the payload, so that the optical payload cannot further improve the imaging quality

However, the traditional spacecraft attitude system is limited by the bandwidth of the controller and the accuracy of the actuator, so it cannot realize the active control of the flexible vibration and high-frequency micro-vibration, and the further improvement of the control accuracy and stability of the star is limited.

[0006] 2. It is difficult to achieve ultra-high precision pointing and ultra-high stability control of the load optical axis

Limited by factors such as the measurement bandwidth of the sensor and the response bandwidth of the actuator, the pointing accuracy and stability of the load cannot be further improved

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