Method for determining the control parameters of spacecraft autonomous cooperative coarse-fine layering master-layer integration three-superior

Abstract

A method for determining the control parameters of spacecraft autonomous and cooperative coarse-fine layering, master-substrate, and three-super-control, which is suitable for fields such as astronomical observation and high-resolution earth observation that require ultra-high-precision determination of payloads. A control parameter design method is provided for spacecraft three-superior control with ultra-high precision, ultra-high stability, and ultra-agile control. Based on the index decomposition method, each controller parameter of the spacecraft three-superior control system is designed, which improves the design efficiency and control performance. The main design ideas are as follows: 1) First, according to the three-level control system architecture, establish the control model of the three-level control of the star, the load, and the fast mirror; ; 3) According to the noise characteristics of the selected sensors and actuators, the parameters of the controllers at all levels are designed through the method of frequency domain analysis, so that the power spectral densities of the control loops at all levels meet the design indicators, and the three-superior control performance of the spacecraft is realized. .

Description

technical field [0001] The invention relates to a star-load-fast mirror three-stage attitude control system and a parameter design method for realizing a spacecraft, belonging to the field of spacecraft attitude control. 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 composite control system came into being according to the demand for high-precision attitude control of such optical loads. The spacecraft multi-level composite control system refers to the sp...

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

In the satellite control system model including the active pointing ultra-static platform and the fast mirror, it is necessary to design a multi-level composite pointing control scheme for the spacecraft. At the same time, in order to solve the problems of many multi-level composite control design components and complex transmission relationships of each channel, the given An index decomposition and parameter design method based on frequency domain analysis, which realizes the rapid and optimal design of multi-level compound control and realizes the three-superior control performance of spacecraft

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