Flutter/vibration control device and method for simulating space vehicle panel structure

A technology for simulating space and aircraft, which is applied in the field of active vibration control devices for simulating the structure of space vehicles, and can solve problems such as the selection of the optimal number of sensors and drives, the optimal size and optimal configuration of the position, etc.

Inactive Publication Date: 2015-10-28
SOUTH CHINA UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

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.

Method used

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  • Flutter/vibration control device and method for simulating space vehicle panel structure
  • Flutter/vibration control device and method for simulating space vehicle panel structure
  • Flutter/vibration control device and method for simulating space vehicle panel structure

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Embodiment Construction

[0027] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments, but the implementation of the present invention is not limited thereto.

[0028] Such as Figure 1 to Figure 3As shown, a flutter / vibration control device for simulating a space vehicle panel structure, the two opposite sides of the flexible board 3 in the width direction of the control device are fixed by a mechanical clamping device 7, and the piezoelectric ceramic sheet reference signal sensor 2 and the piezoelectric ceramic sheet The ceramic chip control sensor 6 is respectively pasted on the horizontal position of the flexible board 3 close to the two fixed ends 50mm, and the longitudinal midline position; an acceleration sensor 4 is installed at the geometric center of the flexible board as a control sensor; At 25mm from the fixed end, 8 pieces of piezoelectric ceramic sheets are pasted symmetrically on both sides, four pieces on each side...

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Abstract

The invention discloses a simulated spacecraft wallboard structure fluttering / vibrating control device and method. The device comprises a flexible board body, a mechanical clamping device, a signal generator, a computer, an A / D (analog / digital) conversion data collecting card, a D / A conversion card, a piezoelectric ceramic drive power source, an acceleration sensor, piezoelectric ceramic piece sensors and piezoelectric ceramic piece drive devices. The flexible board is fixed through two ends of the mechanical clamping device, a plurality of piezoelectric ceramic piece sensors and piezoelectric ceramic piece drive devices are adhered on the flexible board structure and provided with the acceleration sensor. The signal generator stimulates a natural mode of the flexible board through a piezoelectric ceramic piece stimulation drive device and the piezoelectric ceramic drive power source, when the sensors detect a vibrating signal of the flexible board, an active control algorithm is operated, the controlled quantity is applied onto the piezoelectric ceramic piece control drive device through the piezoelectric ceramic drive power source, so that the vibration of the flexible two-end fixed supporting plate can be actively controlled.

Description

technical field [0001] The invention relates to the vibration control of a large flexible two-end fixed-support plate structure, in particular to an active vibration control device and method for simulating a space vehicle structure. Specifically, it provides a device and method for simulating the wall structure of a space vehicle and adopting the optimal configuration of sensors / drivers to realize active vibration control. Background technique [0002] The flutter and vibration active control technology of panel structures has always been an important issue in the aviation field. In order to reduce the structural weight, more thin-walled structures are used in the structural design of the new generation of aerospace vehicles. It is particularly important to conduct aeroelastic analysis of this type of aircraft structure under supersonic or hypersonic flight. Siding flutter is one of the important research topics. The so-called panel flutter refers to a self-excited vibrat...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B23/02G01M7/02
Inventor 邱志成马彪
Owner SOUTH CHINA UNIV OF TECH
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