Large-flow reverse jet flow test device and method for hypersonic aircraft

A test device, hypersonic technology, applied in the field of large flow reverse jet flow test device, to achieve the effect of improving test efficiency, high measurement accuracy and avoiding adverse effects

Active Publication Date: 2021-12-07
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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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0002] When carrying out flight tests of hypersonic vehicles, if the required test range is very long, it is impossible to test the whole process within the territory of the country

Method used

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  • Large-flow reverse jet flow test device and method for hypersonic aircraft
  • Large-flow reverse jet flow test device and method for hypersonic aircraft
  • Large-flow reverse jet flow test device and method for hypersonic aircraft

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Embodiment 1

[0069] The large-flow reverse jet flow test device for hypersonic aircraft in this embodiment has four test nozzles 6 and one debugging nozzle 9, and the debugging nozzle 9 can replace any one of the testing nozzles 6.

[0070] The high-flow reverse jet flow test method for hypersonic aircraft in this embodiment uses high-pressure air as the jet flow medium, the wind tunnel wall air source adapter is externally connected to the high-pressure air source, the wind tunnel wall air source adapter, and the middle bracket The upper Φ15mm interface and the air inlet 2 are connected by a Φ19×2mm copper tube, and the high-pressure air enters the airflow channel from the air inlet 2, and is ejected from the corresponding test nozzle 6 through the branch pipes. The ventilation area of ​​the anti-jet engine chamber formed by each branch pipe is 78.5mm 2 , the Laval nozzle throat area of ​​test nozzle 6 is 15.9mm 2 , the flow velocity of high-pressure air in the branch pipeline is about 4...

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Abstract

The invention discloses a large-flow reverse jet flow test device and a method thereof for a hypersonic aircraft. The test device includes several test nozzles evenly distributed on the windward surface of the orbit control cabin, with a Laval nozzle inside and facing the incoming flow; it includes a balance pole for supporting the model and balance and providing an air intake channel; It also includes the balance and heat insulation cover I and heat insulation cover II for protecting the balance. The high-pressure air enters the airflow channel from the air inlet, and then sprays out from the corresponding test nozzles through the branch pipes. This test method uses a special test model and a balance to measure the aerodynamic force, takes pictures of the flow field display, and comprehensively evaluates the technical effect of the large-flow reverse jet flow.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel tests, and in particular relates to a large-flow reverse jet flow test device and method for hypersonic aircraft. Background technique [0002] When conducting flight tests of hypersonic vehicles, if the required test range is very long, it is impossible to test the flight within the territory of the country. At present, there is an urgent need to develop a large-flow reverse jet flow test device and method for hypersonic vehicles. Install the reverse jet flow device on the test vehicle. When the flight test data of the hypersonic vehicle is obtained, it will be turned on immediately. The large-flow reverse jet flow test device decelerates the hypersonic vehicle to shorten the test voyage. Contents of the invention [0003] A technical problem to be solved by the present invention is to provide a large flow reverse jet test device for hypersonic aircraft, and another technical pr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/02G01M9/06B64F5/60
CPCG01M9/02G01M9/06G01M9/062B64F5/60
Inventor 邱华诚杨彦广石义雷李杰龙正义孙良宝贺江峰强慢
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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