High-temperature combustion-gas flow supersonic wind tunnel test system

A high-temperature gas flow and wind tunnel test technology, which is applied in aerodynamic tests, machine/structural component testing, measuring devices, etc., can solve the problem of not having hundreds of megawatts of power, and achieve the effect of using a large volume

Active Publication Date: 2017-04-19
BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At present, there is no thermal wind tunnel test system with a power of 100 megawatts in China

Method used

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  • High-temperature combustion-gas flow supersonic wind tunnel test system
  • High-temperature combustion-gas flow supersonic wind tunnel test system
  • High-temperature combustion-gas flow supersonic wind tunnel test system

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Embodiment Construction

[0024] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0025] The invention provides a high-power, large-scale aircraft heat-proof ground test assessment wind tunnel. The total power of the high-temperature gas flow supersonic wind tunnel test system is greater than 200MW, and the temperature is 2900-3700K; the stable working time is greater than 1000s; the aircraft heat protection is realized Systematic large-scale model high-power assessment.

[0026] Such as figure 1 Shown is a schematic diagram of a high-temperature gas flow supersonic wind tunnel. It can be seen from the figure that a high-temperature gas flow supersonic wind tunnel test system includes a heater 1, a supersonic nozzle 2, a test chamber 3, a diffuser 4 and an exhaust system 5 Wherein, one end of the heater 1 is connected with the external energy system; one end of the supersonic nozzle 2 is fixedly connected with the heater 1, ...

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Abstract

The invention provides a high-temperature combustion-gas flow supersonic wind tunnel test system and relates to the technical field of aircraft thermal protection ground test. The system comprises a heater, a supersonic nozzle, a test cabin, a diffuser and an exhaust system. One end of the heater is connected with an external energy system; one end of the supersonic nozzle is fixedly connected with the heater, and the other end of the supersonic nozzle is fixedly connected with the test cabin; the diffuser is fixedly arranged at one end of the test cabin; and one end of the exhaust system is fixedly connected with the diffuser, and the other end of the exhaust system is connected with the outside world directly. The high-temperature combustion-gas flow supersonic wind tunnel test system is a system having hundred-megawatt power and meter-scale jet size, and the power thereof reaches more than 200 megawatts, and the jet size reaches 1.5 m; and aircraft thermal protection system global and regional 1:1 large-size model heat check can be realized.

Description

technical field [0001] The invention relates to the technical field of aircraft heat-resistant ground tests, in particular to a high-temperature gas flow supersonic wind tunnel test system. Background technique [0002] Hypersonic aircraft will be subjected to severe aerodynamic heating during flight, and the heat protection system plays a decisive role in the development of the aircraft. It is an indispensable link in the development process of the aircraft heat protection system to carry out thermal environment simulation assessment and verification on the ground test of the aircraft heat protection system. [0003] At present, the domestic test systems for thermal assessment of aircraft heat protection systems mainly include arc wind tunnels and gas flow free jet test benches. The power of the arc wind tunnel is on the order of ten megawatts, the scale of the gas flow free jet test bench is small, and the outlet pressure of the nozzle is generally atmospheric pressure. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/02
CPCG01M9/02
Inventor 邹样辉田宁齐斌张利嵩岳晖张凯那伟杨驰李彦良赵玲王镭夏吝时曹知红肖泽娟张昕曹宇清姜一通李文浩鲁宇朱广生李建林孟刚周岩水涌涛张岩陈卫国刘召军
Owner BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE
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