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A transient jet test device for pulse wind tunnel

A test device and jet flow technology, which is applied in the field of hypersonic pulsed wind tunnel test equipment, can solve the problems of local high heat flow, complex thermal environment in the interference area, difficulties in thermal environment prediction and heat protection design, etc.

Active Publication Date: 2022-02-25
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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Problems solved by technology

[0003] However, during hypersonic flight, the RCS jet flow and the flow around the aircraft interfere with each other, and the thermal environment in the interference area is very complex, resulting in local high heat flow, which makes it difficult to predict the thermal environment and design thermal protection

Method used

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  • A transient jet test device for pulse wind tunnel
  • A transient jet test device for pulse wind tunnel
  • A transient jet test device for pulse wind tunnel

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Embodiment 1

[0054] In this embodiment, the gas cylinders supplied by the gas source are 4 bottles of 13MPa, 40L bottled nitrogen, and 2 bottles of 13MPa, 40L bottled helium; the gas cylinders are connected to the gas storage pipe 1 through a stainless steel high-pressure pipe, and an integrated control is set between the two Each gas cylinder is equipped with a pressure reducing valve, and the connecting pipeline between the gas cylinders is equipped with a safety pressure relief valve. At the same time, a bottle of high-pressure gas is used alone in the gas cylinder group to provide a pilot gas source for the fast solenoid valve 3 .

[0055] The gas storage pipe 1 is made of 304 stainless steel, with an inner diameter of 90 mm and a length of 10 m. The stable gas supply time is about 60 ms when using nitrogen gas. The air pipe 2 is connected; the other end of the small-diameter air pipe 2 is connected to the fast solenoid valve 3 . The fast electromagnetic valve 3 is connected with the ...

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Abstract

The invention discloses a transient jet flow test device used in a pulse wind tunnel. The transient jet flow test device includes a jet flow test model, an air source supply system, a fast synchronous control system and a jet flow parameter measurement device; the jet flow test model ejects a stable jet flow; the air source supply system provides the required Stable air source, fast synchronous control system to ensure that the formation time of the stable jet flow is synchronized with the formation time of the main flow of the pulse wind tunnel; at the same time, the air source supply system ensures that the duration of the stable jet flow exceeds the effective test time of the main flow of the pulse wind tunnel, and the fast synchronous control system is in The air source supply system is automatically turned off after the set stable jet flow time is reached; the jet flow parameter measuring device is used to measure the flow field parameters of the stable jet flow from the model before the jet flow test. The transient jet flow test device can provide jet flow with accurate parameters, good stability and repeatability to evaluate the influence of jet flow disturbance on the aerodynamic characteristics of the aircraft, and can quickly complete the jet flow preparation and accurately control the injection time.

Description

technical field [0001] The invention belongs to the field of hypersonic pulse wind tunnel test equipment, and in particular relates to a transient jet flow test device used in a pulse wind tunnel. Background technique [0002] Lateral jet control is a control method to control the attitude of the aircraft or provide direct maneuvering force by means of the jet reaction force and the disturbance force generated by the interaction between the jet and the incoming flow. Compared with the traditional aerodynamic rudder control, the lateral jet control is applicable to the full speed range and the whole airspace, and has the remarkable characteristics of fast response and high efficiency, which is conducive to reducing the aerodynamic control surface, weight and drag of the aircraft. Non-lift re-entry vehicles (such as spacecraft return capsule), lift-type re-entry vehicles (such as space shuttle, X-37B, X-38, HTV-2, etc.) and high-speed interceptor missiles (such as PAC-3, THAAD...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/00G01M9/06G01M9/08
CPCG01M9/00G01M9/06G01M9/08
Inventor 龚红明孔小平秦峰吕明磊
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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