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Ejector module used for intake-exhaust simulation experiment of low-speed wind tunnel aircraft

A simulation test and aircraft technology, applied in the field of wind tunnel test, can solve problems such as difficult, difficult to ensure non-contact between EPES and model, difficult to obtain, etc., and achieve the effect of compact structure

Active Publication Date: 2019-11-05
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantages are: it is difficult to ensure complete non-contact between the EPES and the model during the test, and there is a requirement for good sealing and no external force to be introduced; for a flat aircraft model equipped with multiple embedded engines, it is limited by the model space and power plant layout. Due to the limitation of the method, it is extremely difficult to meet the above requirements, and it is not easy to obtain clean data on the influence of the intake and exhaust effects on the aerodynamic force of the aircraft in the test.

Method used

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  • Ejector module used for intake-exhaust simulation experiment of low-speed wind tunnel aircraft
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  • Ejector module used for intake-exhaust simulation experiment of low-speed wind tunnel aircraft

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Embodiment Construction

[0025] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0026] Any feature disclosed in this specification (including any appended claims, abstract and drawings), unless expressly stated otherwise, may be replaced by alternative features which are equivalent or serve a similar purpose. That is, unless expressly stated otherwise, each feature is one example only of a series of equivalent or similar features.

[0027] Such as figure 1 Shown is a schematic diagram of the installation structure of this embodiment, the ejector module of the present invention is installed on the test model, the ejector is used to replace the engine of the aircraft model, and the dynamic parameters of the real aircraft are simulated in the wind tunnel, thereby realizing Collection of test data.

[0028] This embodiment consists of four parts: the outer frame, the middl...

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Abstract

The invention discloses an ejector module used for an intake-exhaust simulation experiment of a low-speed wind tunnel aircraft. The ejector module comprises an outer frame, a middle frame and an innerframe in sequence from outside to inside, wherein the outer frame, the middle frame and the inner frame are mutually connected to form a sealed cavity; the outer frame is provided with a gas inlet communicated with the sealed cavity, the inner frame is provided with a plurality of nozzle rakes, one end of each nozzle rake is communicated with the sealed cavity, and the other ends of the nozzle rakes are provided with nozzles. An injector is designed into a module of a model structure, and the injector is integrated with the model; the injector module uses a discrete multi-nozzle distributiontype injection mode, and the structure is compact. The discrete multi-nozzle distribution type injection mode greatly increases the mixing degree between high-energy compressed gas and injected low-energy gas, and the injection efficiency is obviously improved.

Description

technical field [0001] The invention relates to the field of wind tunnel tests, in particular to an ejector module used for low-speed wind tunnel aircraft intake and exhaust simulation tests. Background technique [0002] In the low-speed wind tunnel aircraft intake and exhaust simulation test, the simulation of the aircraft's power plant is a key technical link; among them, the ejector is used as the core component to simulate the working conditions of the aircraft's power plant. The purpose of the low-speed wind tunnel aircraft intake and exhaust simulation test is to obtain the data of the influence of the intake effect and exhaust effect on the aerodynamic force of the aircraft when the aircraft power plant is working. [0003] In the low-speed wind tunnel, the original ejection simulator (EPES) used to carry out the simulation test of aircraft intake and exhaust is an independent device. Its structure is relatively simple, and it is easy to install inside the model; th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/04
CPCG01M9/04
Inventor 李东巫朝君胡卜元韩建飞康洪铭马军郝志清张鹏李春霞付华
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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