Sonic boom measurement test device based on temporary impact type supersonic wind tunnel, and measurement method
A technology of wind tunnel test and test device, applied in the field of aerospace wind tunnel test, can solve the problem of low accuracy of test results, and achieve the effects of reducing interference factors, improving consistency, and ensuring consistency
Pending Publication Date: 2019-08-16
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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[0035] The purpose of the present invention is to provide a temporary supersonic wind tunnel to overcome the problem of low accuracy of the test results when using a probe to carry out the sonic boom measurement test in the sonic boom measurement test using a temporary supersonic wind tunnel. Wind Tunnel Sonic Boom Measurement Test Device and Measurement Method
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Embodiment 1
[0069] As shown in the figure, the temporary supersonic wind tunnel sonic boom measurement test device of the present embodiment includes the wall plate of the first wind tunnel test section, the wall plate of the second wind tunnel test section, a measuring probe, a connecting device for the measuring probe, For the model connecting device, reference probe, and reference probe fixing device connected to the model to be tested, the wall plate of the first wind tunnel test section is set opposite to the wall plate of the second wind tunnel test section, and the wall plate of the first wind tunnel test section is connected to the wall plate of the second wind tunnel test section. The temporary supersonic wind tunnel test section is formed between the wall panels of the second wind tunnel test section. In this embodiment, the wall plate of the first wind tunnel test section is the upper wall plate of the wind tunnel test section, and the wall plate of the second wind tunnel test sec...
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The invention discloses a sonic boom measurement test device based on a temporary impact type supersonic wind tunnel, and a measurement method, and aims to solve the problem that the accuracy of a test result is not high when a probe is used for carrying out a sonic boom measurement test in a process of adopting the temporary impact type supersonic wind tunnel for carrying out the sonic boom measurement test at present. The sonic boom measurement test device based on the temporary impact type supersonic wind tunnel comprises a first wind tunnel test section wall plate, a second wind tunnel test section wall plate, a measuring probe, a measuring probe connecting device, a model connecting device, a reference probe, a reference probe fixing device and the like. By adopting the device disclosed by the invention, a model, the measuring probe and a supporting device of the measuring probe can be effectively protected from being deformed due to a large impact load in a starting / stopping stage of the supersonic wind tunnel; and a small-range differential pressure sensor is protected from being damaged. Meanwhile, by the adoption of the device, on the premise of keeping the overall layoutof the test unchanged, the sonic boom measurement test is carried out by moving the model and moving the measuring probe, so that the accuracy of the sonic boom measurement result is effectively improved.
Description
technical field [0001] The invention relates to the field of aerospace wind tunnel tests, in particular to a temporary surge type supersonic wind tunnel sonic boom measurement test device and a measurement method. Background technique [0002] Sonic boom means that when the speed of the aircraft reaches supersonic speed, a series of wave systems generated by the shape of the aircraft interfere with each other in the process of propagating far away, and finally converge into a front shock wave including the head of the aircraft and a rear shock wave trailing the tail of the aircraft. shock wave. When this wave system propagates to the ground, it is perceived as two loud thunderous noises. [0003] As an independent test technique, the sonic boom measurement test refers to obtaining the characteristics of the sonic boom produced by the aircraft through experiments. The basic idea of the sonic boom measurement test is to change the relative position of the aircraft model an...
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Login to View More IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 杨洋钱丰学林学东毛代勇张长丰魏志刘光远刘志勇邓吉龙叶伟
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT