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Balance strut for wind tunnel hot jet interference test

A technology of balance poles and poles, which is applied in the field of wind tunnel testing, and can solve the problems of unstable pressure in the jet flow chamber, short effective test time, and low efficiency.

Pending Publication Date: 2019-05-17
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

AI Technical Summary

Problems solved by technology

At present, the research on the jet disturbance wind tunnel test is mainly based on the cold jet disturbance test, and the hot jet disturbance test is less. Stability, low efficiency, short effective test time, etc.

Method used

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  • Balance strut for wind tunnel hot jet interference test
  • Balance strut for wind tunnel hot jet interference test
  • Balance strut for wind tunnel hot jet interference test

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0031] The working process of this embodiment is as follows:

[0032] 1. Install and debug the nozzle 6 to measure the total temperature and pressure, obtain the running state required for the test, remove the debug nozzle 6, and block it;

[0033] 2. Install the test nozzle 8, such as Figure 7 As shown, the model is installed in the wind tunnel, the front end of the main body of the strut is installed on the rear end of the balance through the wedge key and the pin key, the front end of the balance is installed with the wind tunnel test model through the heat insulation sleeve, and the rear end Covered on the test nozzle 8, the surface of the wind tunnel test model corresponding to the test nozzle 8 has a model cover plate 12, and the model cover plate 12 is provided with a test nozzle outlet 11, and the test nozzle 8 protrudes from the test nozzle outlet 11, and the test nozzle 8 is flush with the surface of the model cover plate 12, and there is a gap between the test noz...

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Abstract

The invention discloses a balance strut for a wind tunnel hot jet interference test. The balance strut comprises a strut body, a gas circuit module, a water cooling module, a debugging nozzle and a test nozzle. The strut body is used for installing a balance and a model; the gas circuit module is used for carrying out jet gas intake; the water cooling module is used for cooling the strut, so as toreduce the influence of the high temperature of jet gas on the measurement of the balance. The jet gas intake adopts the mixed gas of carbon tetrafluoride and nitrogen, and the specific heat ratio ofthe mixed gas is adjusted by changing the ratio of the two gases. Before the test, only the debugging nozzle is installed to adjust the total temperature and total pressure of the jet; and the debugging nozzle is taken down during the test, the test nozzle and the model are installed, and the wind tunnel test is performed according to the debugging state. The balance strut for the wind tunnel hotjet interference test provided by the invention is applicable to a wind tunnel hot jet test in a thin atmospheric environment and can measure the influence of jet interferences on the model aerodynamic force.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a balance pole used in wind tunnel thermal jet interference tests. Background technique [0002] With the development of aerospace technology, the flight Mach number of the aircraft is also increasing, which poses a severe challenge to the control of the aircraft. Currently, traditional aerodynamic rudder surface control and jet flow control are widely used. [0003] Jet flow control technology is a new type of control system that uses the jet flow reaction force generated by the micro jet flow engine installed on the aircraft to directly control the aircraft. Compared with the traditional rudder surface control, the jet flow control is suitable for full speed and full Airspace has the advantages of fast response and high efficiency; however, the disturbance caused by the interaction of jet flow and incoming flow is a typical complex flow phenomenon, and th...

Claims

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Application Information

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IPC IPC(8): G01M9/06G01M9/04
Inventor 李杰邱华诚闵夫皮兴才李四新刘祥
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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