Spacecraft autonomous coordination coarse-fine layering active-passive integrated three-ultra control parameter determination method

Abstract

The invention relates to a spacecraft autonomous coordination coarse-fine layering active-passive integrated three-ultra control parameter determination method, which is suitable for the fields of astronomical observation, high-resolution earth observation and the like with load ultra-high precision determination requirements. A control parameter design method is provided for spacecraft three-ultra control with ultrahigh precision, ultrahigh stability and ultra-agility control, parameters of all controllers of a spacecraft three-ultra control system are designed based on an index decompositionmethod, and design efficiency and control performance are improved. The main design thought is as follows: 1) firstly, according to a three-ultra control system architecture, a control model for three-level control of a star body, a load and a fast reflector is established; 2) transfer functions of all levels of three-level control loops are deduced according to the three-ultra control system model; and 3) parameters of all levels of controllers are designed through a frequency domain analysis method according to noise characteristics of a selected sensor and an executing mechanism, so that the power spectral density of all levels of control loops meets design indexes, and the three-ultra control performance of a spacecraft is achieved.

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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