An acceleration feedback vibration control method for spacecraft flexible structures

Abstract

The invention discloses an acceleration feedback vibration control method for a flexible structure of a spacecraft. First, the dynamic equation and transfer function of the structure are obtained according to simulation modeling analysis or structural test testing; then a controller based on acceleration feedback is designed to introduce A second-order system compensator and a first-order system compensator, and configure the compensator damping parameter ζ f and the frequency parameter ω f ; Finally, configure the feedback gains α and β of the controller, and the control output is the addition of the variables of the two compensators and negative feedback. The invention uses the acceleration as the feedback physical quantity to avoid the accumulation of errors; introduces a second-order system compensator, directly uses the compensator variable as negative feedback, and overcomes the high-frequency control overflow problem through its low-pass filtering characteristics; adds a first-order system compensator , By configuring two compensator gain parameters, it solves the problem that the control effect of the closed-loop control system decreases due to the existence of time delay, and improves the vibration control ability of the system.

Description

technical field

[0001] The invention relates to the technical field of vibration control, and specifically designs an acceleration feedback vibration control method suitable for a flexible structure of a spacecraft. Background technique

[0002] With the continuous development of aerospace technology, ultra-large-scale and multi-functional spacecraft is an important direction for the development of spacecraft structure technology in the future. As the size gradually increases, the structure of the spacecraft exhibits the characteristics of large flexibility, low frequency and small damping. It is easily affected by the space environment and is prone to low-frequency vibration. Once it occurs, the attenuation will be slow, affecting the high-precision and high-stability performance of the spacecraft, and may even be possible. It will endanger the normal operation of the spacecraft, so the vibration control of the flexible structure of the spacecraft is of great significance. ...

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