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A Vibration Isolation Method for a Model Mechanism in a Hypersonic Wind Tunnel Test Section

A hypersonic and wind tunnel test technology, applied in aerodynamic tests, machine/structural component testing, instruments, etc., can solve problems that affect the accuracy of aircraft aerodynamic measurement, and achieve simple structure, simple construction, and vibration isolation effects Good results

Active Publication Date: 2022-04-12
中国空气动力研究与发展中心超高速空气动力研究所
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to eliminate the vibration generated during the operation of the wind tunnel from being transmitted to the model mechanism and thus affect the accuracy of aircraft aerodynamic measurement, it is urgent to develop a vibration isolation method for the model mechanism in the hypersonic wind tunnel test section.

Method used

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  • A Vibration Isolation Method for a Model Mechanism in a Hypersonic Wind Tunnel Test Section
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  • A Vibration Isolation Method for a Model Mechanism in a Hypersonic Wind Tunnel Test Section

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Embodiment 1

[0048] According to an embodiment of the present invention,

[0049] see Figure 1-10 , a vibration isolation method for a model mechanism in a hypersonic wind tunnel test section, including the following four steps:

[0050] a. Set the supporting foundation for installing the model mechanism system as an independent foundation platform 1, and set a vibration isolation gap 3 between the independent foundation platform 1 and the foundation 2 of the test section, and fill the interior of the vibration isolation gap 3 with fine sand, vibration isolation cotton or Foam board, the independent foundation platform 1 adopts multiple pile foundations to support on the underground rock layer;

[0051] b. Install the lower chamber 5 of the test section of the lower mechanism 4 in the model mechanism system on the independent foundation platform 1 of the model mechanism, and fix it through the pre-embedded anchor bolts. The anchor bolts are connected to the lower chamber 5 of the test se...

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Abstract

The invention discloses a vibration isolation method for a model mechanism in a hypersonic wind tunnel test section, which comprises the following four steps: a. The supporting foundation of the model mechanism is set as an independent foundation platform, and the independent foundation platform and the foundation of the test section Set vibration isolation gaps between them; b. Install the lower chamber of the test section of the lower mechanism on an independent foundation platform, and use rectangular bellows to eliminate the vibration generated by the diffuser equipment connected to the main chamber of the test section; c. Nozzle The connection between the test section and the test section is inflated and sealed to prevent vibration from being transmitted to the model mechanism through the test section; d. Chamber vibration isolation. The invention adopts the support of an independent foundation platform to prevent ground vibration from being transmitted to the model mechanism; and adopts an air-filled sealing structure to prevent the vibration of main equipment such as nozzles from being transmitted to the model mechanism, and has good vibration isolation effect.

Description

technical field [0001] The invention relates to the field of hypersonic wind tunnel equipment, in particular to a vibration isolation method for a model mechanism in a hypersonic wind tunnel test section. Background technique [0002] The hypersonic wind tunnel is an important ground test equipment for the design and performance evaluation of hypersonic vehicles. The test section is the place where the hypersonic wind tunnel conducts model tests, and it is also the place where the test personnel have more contact with the wind tunnel. It is mainly used to install the model mechanism for adjusting the attitude of the aircraft test model, the measuring balance and measuring sensors, and the observation of the wind tunnel flow field, etc. . The hypersonic wind tunnel model mechanism system generally includes an upper mechanism and a lower mechanism with multiple degrees of freedom. The aircraft test model and measuring balance are installed on the upper mechanism and the lower...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/04
CPCG01M9/04
Inventor 孙启志张德炜许晓斌凌岗
Owner 中国空气动力研究与发展中心超高速空气动力研究所
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