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Test setup for multi-jet side jets

An experimental device and multi-nozzle technology, applied in the field of experimental devices, can solve the problems of not effectively reducing the impact of jet flow, not considering shock absorption and anti-shock structure, not considering the effect of pipeline rigidity, etc., to avoid uneven jet flow, Avoid the effect of limited total jet pressure and error avoidance

Active Publication Date: 2019-01-18
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In the past, the multi-nozzle lateral jet flow test device either did not consider the shock-absorbing and anti-shock structure or could not effectively reduce the impact of the jet flow impact, or did not include a rectifying and stabilizing structure, or did not add sensor measurement and detection devices, or did not consider The rigidity of the pipeline and the shock-absorbing structure limit the total pressure of the spray flow to be low, etc.

Method used

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  • Test setup for multi-jet side jets
  • Test setup for multi-jet side jets
  • Test setup for multi-jet side jets

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Embodiment Construction

[0035] The present invention will be further described in detail below in conjunction with the accompanying drawings, so that those skilled in the art can implement it with reference to the description.

[0036] It should be understood that terms such as "having", "comprising" and "including" as used herein do not entail the presence or addition of one or more other elements or combinations thereof.

[0037] Based on the requirements of the jet flow test, the present invention specially designs and manufactures a multi-nozzle lateral jet flow test device suitable for sub / span / super / hypersonic wind tunnels. Such as figure 1 ~Shown in 3, the present invention provides a kind of test device for multi-jet side jet flow, comprising:

[0038] chamber 1, which has a closed chamber 1 cavity; and

[0039] Gas rectifying device 3, which is arranged in the chamber 1 cavity of said chamber 1, and a plurality of ventilation holes are provided on the side wall to communicate with the cavi...

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Abstract

The invention discloses a test device for lateral jet flows of multiple nozzles. The test device comprises a plenum chamber and an air rectification device, wherein the plenum chamber has a closed plenum chamber cavity, the air rectification device is arranged in the plenum chamber cavity of the plenum chamber, a side wall of the air rectification device is provided with a plurality of air vent holes communicated with the plenum chamber cavity, and one end of the air rectification device extends beyond the plenum chamber cavity and is communicated with an air source. The device disclosed in the invention can provide multiple stable and accurate jet flows, effects exerted by jet flow impact and pipeline rigidity can be eliminated, total pressure of the jet flows can be provided, and the total pressure of the jet flows in the plenum chamber of a jet pipe can be accurately measured in tests when a test system is installed.

Description

technical field [0001] The invention belongs to the technical field of experimental devices, and relates to a test device for providing accurate and stable multi-nozzle lateral jet flow in a sub / span / super / hypersonic wind tunnel, in particular to a multi-nozzle lateral jet flow test device. flow testing device. Background technique [0002] The reaction force (RCS) generated by the lateral jet can change the attitude or trajectory of the aircraft. Its function is to supplement the inefficiency of the aerodynamic rudder surface and quickly change the flight state. It has been applied to a variety of aircraft at home and abroad: such as PAC-3 , THAAD, Aster, returner and many new types of high-mobility aircraft in my country, RCS control technology has become an essential key technology for the above-mentioned aircraft. However, the interference of multiple jets and outflows will cause significant changes in the surface and space flow of the aircraft, resulting in additional a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/06
CPCG01M9/06G01M9/065
Inventor 倪招勇李素循罗世杰
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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