Test device for measuring thrust of shock tunnel

A test device, shock wave wind tunnel technology, applied in the direction of measuring device, aerodynamic test, machine/structural component test, etc., can solve the problem of high strength requirements of the test section, achieve saving production costs, improve adaptability, and overall Simple and reasonable structure

Active Publication Date: 2021-06-25
中国空气动力研究与发展中心超高速空气动力研究所 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In view of the existing engine thrust measurement technology, the suspension installation method has high requirements on the strength of the test section and the high temperature of the combustion chamber affects the measurement accuracy of the balance. The purpose of the present invention is to provide a shock tunnel thrust measurement test dev

Method used

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  • Test device for measuring thrust of shock tunnel
  • Test device for measuring thrust of shock tunnel
  • Test device for measuring thrust of shock tunnel

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0035] In this embodiment, a shock tunnel thrust measurement test device such as Figure 1-2 As shown, it includes a support base 1 , a balance 2 , a model balance adapter 3 , a fairing 4 and an accelerometer 5 .

[0036] Such as Figure 7 As shown, the support base 1 includes a base plate 17 and two balance mounting bases 16 fixedly mounted on the base plate 17, and a set of balances 2 is mounted on each balance mounting base 16. The bottom plate 17 is an integral rectangular structure. The two balance mounts 16 are arranged in parallel along the length direction of the bottom plate 17 (that is, the length direction of the model). The balance mounting base 16 is composed of two main bodies and a mounting panel in a rectangular parallelepiped structure. The bottom plate 17 is fixedly connected with the angle-of-attack mechanism of the wind tunnel by means of screw connection.

[0037] Such as Figure 4-5As shown, the balance 2 includes an upper connection plate 7 , a lowe...

Embodiment 2

[0043] In this embodiment, a shock tunnel thrust measurement test device such as image 3 As shown, it includes a support base 1 , a balance 2 , a model balance adapter 3 , a fairing 4 , an accelerometer 5 and an angle wedge 15 .

[0044] Such as Figure 7 As shown, the support base 1 includes a base plate 17 and two balance mounting bases 16 fixedly mounted on the base plate 17, and a set of balances 2 is mounted on each balance mounting base 16. The bottom plate 17 is an integral rectangular structure. The two balance mounts 16 are arranged in parallel along the length direction of the bottom plate 17 (that is, the length direction of the model). The balance mounting base 16 is composed of two main bodies and a mounting panel in a rectangular parallelepiped structure. The bottom plate 17 is fixedly connected with the angle-of-attack mechanism of the wind tunnel by means of screw connection.

[0045] Such as Figure 4-5 As shown, the balance 2 includes an upper connectio...

Embodiment 3

[0051] In this embodiment, a shock tunnel thrust measurement test device such as Figure 1-2 As shown, it includes a support base 1 , a balance 2 , a model balance adapter 3 , a fairing 4 and an accelerometer 5 .

[0052] Such as Figure 10 As shown, the support base 1 includes a base plate 17 and two balance mounting bases 16 fixedly mounted on the base plate 17, and a set of balances 2 is mounted on each balance mounting base 16. The bottom plate 17 is a split structure composed of the bottom plate I and the bottom plate II, and the two balance mounting seats 16 are installed on the bottom plate I and the bottom plate II respectively. The two balance mounts 16 are arranged in parallel along the length direction of the bottom plate 17 . The balance mounting base 16 is composed of two main bodies and a mounting panel in a rectangular parallelepiped structure. The bottom plate I and the bottom plate II are fixedly connected with the angle of attack mechanism of the wind tunn...

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Abstract

The invention discloses a test device for measuring thrust of a shock tunnel. The test device comprises a supporting seat, a balance, a model balance adapter, a fairing and an accelerometer. The supporting seat, the balance and the model balance adapter are sequentially arranged from bottom to top, the fairing is fixedly mounted on the supporting seat and surrounds the outer sides of the balance and the model balance adapter, and the inner wall of the fairing is not in contact with the balance and the model balance adapter. The accelerometer is installed on the balance. According to the test device provided by the invention, the two balances are combined to measure the thrust acting on the model, the thrust measuring requirements of models with different lengths can be met by adjusting the distance between the two balances, the adaptability of the balances is good, the manufacturing cost of the balances is saved, the measurement signal is compensated through the accelerometer, and the measurement requirement of the shock tunnel in extremely short effective test time is met.

Description

technical field [0001] The invention belongs to the technical field of aerodynamic testing, and relates to a shock tunnel thrust measurement testing device. Background technique [0002] In the development of combustion ramjet, the optimization of engine thrust is the focus of researchers. Therefore, the measurement of engine thrust in ground test equipment is an important direction in scramjet research. Carrying out scramjet thrust measurement test in pulsed shock tunnel is an important means to obtain high Mach number scramjet thrust. Stress wave balance scramjet thrust measurement tests have been carried out in the T4 shock wave wind tunnel of the University of Queensland in Australia, and the scramjet thrust measurement test has been carried out in Japan's HIEST free piston shock wave wind tunnel using accelerometer free flight force measurement technology . [0003] However, both stress wave balance and accelerometer free-flight measurement tests require the model to...

Claims

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Application Information

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IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 赵荣娟刘施然吴里银吕治国周正吕明磊孔小平
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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