Flexible link and actuating unit integrated stress balancing method for driving-driven integrated flexible actuator based on three-super control

Abstract

The invention discloses a flexible link and actuating unit integrated stress balancing method for a driving-driven integrated flexible actuator based on three-super control, and the method is suitablefor the fields of astronomical observation, high-resolution earth observation and the like with ultrahigh load precision, ultrahigh stability and super-agility control requirements. Aiming at a spacecraft with multi-stage cooperative control, the invention provides a design method of a membrane spring, flexible hinge and actuation unit parallel integrated control structure, which has the functions of vibration isolation, disturbance suppression and accurate pointing adjustment, and realizes analysis and stress optimization design of an anti-mechanical environment of an over-launch active section of the driving-driven integrated flexible actuator, the reliability of the emission active section of the actuator is improved. The method can be applied to the design of an active pointing ultra-static platform, and is used for realizing the ultra-high precision, ultra-high stability and ultra-sensitive 'three-super' control performance of the load.

Description

technical field [0001] The invention relates to an integrated stress balance method of a flexible link and an actuating unit of an integrated flexible actuator based on three super-controls, and belongs to the field of spacecraft vibration isolation mechanism design. Background technique [0002] In the future, high-performance spacecraft will require three-super (ultra-high precision, ultra-high stability, and ultra-agility) control. However, there are reaction flywheels, solar panel drive mechanisms, antenna servo drives, and Stirling refrigerators on satellites. These on-board disturbance sources will generate random vibration and harmonic vibration, which will stimulate a large acceleration and destroy the high-static environment of the satellite, thereby affecting the attitude control accuracy and stability of the spacecraft. [0003] Limited by the measurement accuracy and measurement bandwidth limitations of traditional attitude sensors (star sensors, gyroscopes), the...

AI Technical Summary

Problems solved by technology

At the same time, considering the existence of flexible structures such as membrane springs and flexible hinges in the flexible actuator integrated with the active part, the flexible structure will withstand the harsh mechanical environment when the active section is launched, and it is necessary to analyze and optimize the mechanical environment of the actuator. , In the prior art, the flexible link and the actuating unit have not been integrated in the design and analysis, which may lead to stress concentration in the flexible link, and there are problems with the reliability of the active section of the launch, which cannot meet the requirements of engineering applications

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