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High-precision ultralow frequency six-dimensional force micro-vibration measuring system

A measurement system and micro-vibration technology, applied to measurement devices, ultrasonic/sonic/infrasonic waves, instruments, etc., can solve the problems of inflexible installation interface, low measurement accuracy of micro-vibration measurement system, etc., to improve anti-interference ability and test Accuracy, real-time measurement accuracy improvement, good signal-to-noise ratio effect

Inactive Publication Date: 2016-05-25
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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Problems solved by technology

[0004] The purpose of the present invention is to solve the technical problems of low measurement accuracy and inflexible installation interface of the micro-vibration measurement system in the prior art, and provide a high-precision ultra-low frequency six-dimensional force micro-vibration measurement system

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  • High-precision ultralow frequency six-dimensional force micro-vibration measuring system

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Embodiment Construction

[0035] Further illustrate the present invention below in conjunction with accompanying drawing.

[0036] Such as Figure 1-5 As shown, the high-precision ultra-low frequency six-dimensional force micro-vibration measurement system of the present invention includes a box body 1, a load plate 2, four vertical piezoelectric sensors 3, six horizontal piezoelectric sensors 4, and six lateral positioning plates 5. Signal adjustment device 9 and data acquisition and processing system 10 .

[0037] Wherein, box body 1 is made up of casing 11 and base 12, and casing 11 is the hollow structure of bottom end opening, and the top surface of casing 11 is provided with first central through hole 111, and side is provided with window 112, facilitates casing 1 The internal piezoelectric sensor is routed and when the disturbance source is arranged inside the box body 1, it is convenient to operate the disturbance source; the base 12 is fixed on the bottom opening of the housing 11, and forms ...

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Abstract

The invention relates to a high-precision ultralow frequency six-dimensional force micro-vibration measuring system, and the system belongs to a field of high-precision measuring system technology. The problem that the measuring system in prior art has low measuring precision and inflexible installation interface is solved. The measuring system comprises a box body, a load disc, four vertical piezoelectric sensors, six horizontal piezoelectric sensors, six lateral positioning plates, a signal adjustment device and a data acquisition and processing system; wherein the box body is formed by a shell body and a base, the load disc is formed by a bottom disc and a mounting column, the vertical piezoelectric sensors are impacted by a top surface in the shell body and a top surface of the bottom disc, the horizontal piezoelectric sensors are respectively impacted by the side surfaces of the bottom disc and the side surfaces of the lateral positioning plates, charge signals measured by ten piezoelectric sensors are converted into voltage signals through the signal adjustment device, the voltage signals are analyzed and calculated by the data acquisition and processing system, so that three dynamic forces and three dynamic bending moments of a disturbance source are obtained. The measuring system can precisely measure the disturbance force of the disturbance source, the installation interface is flexible and easy to operate, and the system has high measurement reliability.

Description

technical field [0001] The invention belongs to the technical field of high-precision measurement systems, and in particular relates to a high-precision ultra-low frequency six-dimensional force micro-vibration measurement system. Background technique [0002] In the spacecraft attitude control system, there are important components such as reaction wheels, single-frame moment gyroscopes, and solar wing drive mechanisms. Due to the existence of flywheel unbalance, bearing disturbance, motor disturbance, and motor drive errors in these components, these components cannot provide necessary At the same time of the control power, it will also cause some harmful vibrations (for simplicity, these components are collectively referred to as disturbance sources below). There are a large number of optical components in the spacecraft, which put forward high requirements for pointing accuracy and stability. The disturbance force and disturbance moment of these disturbance sources will...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01H11/08
CPCG01H11/08
Inventor 夏明一徐振邦李昂霍琦吴清文
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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