Space sailboard bending and turning mode vibration simulation active control device and method

Abstract

The invention discloses an active control device of vibration simulation for bending and torsional modes of space sailboards and a method. The device symmetrically sticks multi-chip bending mode piezoelectric actuators on front and rear faces of a flexible plate, a bending mode sensor is arranged at the position horizontally closing to a fixed end by 320-25mm of the flexible plate and on the longitudinal center line of the flexible plate, torsional mode actuators composed of a plurality of piezoelectric ceramic chips are antisymmetrically stuck on both faces of the flexible plate, and torsional mode sensors composed of a plurality of the piezoelectric ceramic chips are stuck on both faces of the flexible plate. The method operates an active vibration control strategy according to information of the bending mode and trosional mode sensed by a piezoelectric sensor, and then drives a voltage amplifier through piezo-electricity to respectively drive the piezoelectric actuators for controlling multimode vibrations of bending and torsion, thereby realizing the purpose of actively inhibiting the vibrations. The invention employs the optimum distribution of piezoelectric sensor chips and driving chips, and realizes decoupling of bending modes and torsional modes of flexible cantilever plates in inspection and drive control.

Description

Technical field [0001] The invention relates to vibration control of a large flexible structure, in particular to a device and method for multi-modal active control of bending and torsional vibration of a flexible space sailboard structure, and specifically provides a cantilever deflection for simulating flexible space sailboard The flexible plate structure uses a multi-modal vibration active control device and method based on the optimized configuration of piezoelectric sensors and drivers to realize the decoupling of multi-bending and multi-torsion modes in detection and control. Background technique [0002] With the rapid development of space technology, new requirements are put forward for the performance of space structure systems. Large-scale, low-rigidity and flexibility are an important development trend of spacecraft structures. Large-scale structures can increase the functions of space structures. On the one hand, the use of large-scale flexible accessories increases t...

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Problems solved by technology

The purpose of global control (high-power control) is to suppress the vibration response at a specific point of the structure. This control is usually a control form of non-co-located (external) configuration of sensors and drivers, which requires an accurate input-output system model. The main problems are How to Guarantee the Global Stability and Improve the Robustness of the System

[0006] (1) The geometric size of the selected board is small, and the modal frequency is relatively high, generally above tens of hertz, which is much higher than the modal frequency of the space solar panel, so it cannot be used to simulate the control research of the solar panel. Also, the rapid vibration control of large flexible sailboard structures is not well resolved;

[0007] (2) The space sailboard is basically a cantilever outrigger structure, and the vibration excited by the disturbance includes the vibration of bending and torsional modes. The existing technology is mainly aimed at the vibration control of bending mode, but it is realized based on the optimal configuration of piezoelectric sensors and drivers. The problem of decoupling in the detection and control of bending and torsional modes is not well resolved, which is likely to cause the problem of "overflow" in observation and control; in order to overcome the "overflow" problem, it is necessary to base To design an analog or digital bandpass filter, and achieve decoupling of bending and torsional vibrations by filtering modal methods, which will cause problems such as phase lag in applications and increase the complexity of the system;

[0008] (3) In the actual system, there are number and position optimization problems at the same time when using piezoelectric ceramic chips to achieve vibration control

The problem of optimal configuration of sensors and actuators for this type of structure: that is, the optimal number selection, optimal size and location of sensors and actuators are not well resolved.

The problem with the co-location of the sensor and the driver is that it is easy to cause false suppression phenomenon, that is, the output of the sensor is suppressed but the vibration is not suppressed, which is due to the local control problem of local stiffening caused by the stress concentration of the co-located configuration

Due to factors such as different phase differences of different modes, the ectopic configuration will cause the stability of the system control;

[0009] (4) Considering the limitation of the weight, cost and volume of the spacecraft, the piezoelectric ceramic power supply is required to be miniaturized, and the technical realization of the miniaturized piezoelectric ceramic power supply has not been well solved

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