Transient wavefront test platform and system based on hypersonic pulse tunnel
A hypersonic, test platform technology, used in machine/structural component testing, measuring devices, aerodynamic tests, etc., can solve problems affecting test results and test models, and achieve the effect of ensuring reliability
Active Publication Date: 2018-10-16
NAT UNIV OF DEFENSE TECH
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Problems solved by technology
[0004] The present invention provides a transient wave front test platform and system based on a hypersonic pulse wind tunnel to solve the problem that the installation position of the laminar flow partition in the existing test platform makes the test model unable to be located in the effective rhombus of the axisymmetric nozzle test flow field. Technical issues in the area causing impact on test results
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[0034] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0035] refer to Figure 1 to Figure 4 , a preferred embodiment of the present invention provides a transient wavefront test platform based on a hypersonic pulse wind tunnel, including an experimental cabin 1 , an axisymmetric nozzle 2 and a diffuser 3 . The experiment chamber 1 has a front wall 10 and a rear wall 11 opposite to each other, and a left side wall 12 and a right side wall 13 opposite to each other. The experiment chamber 1 is provided with at least two correspondingly arranged first optical windows 14 . The nozzle end section 20 of the axisymmetric nozzle 2 extends through the front wall 10 into the experimental chamber 1 . A nozzle extension section 4 is connected to the rear en...
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The invention discloses a transient wavefront test platform and system based on a hypersonic pulse tunnel. The test platform comprises an experiment module, an axisymmetric nozzle and a diffuser; theexperiment module is provided with opposite front and rear walls, and opposite left side wall and right side wall; the experiment module is provided with at least two corresponding first optical windows; a tail section of the nozzle of the axisymmetric nozzle extends through the front wall and goes into the experiment module, and the diffuser is disposed on the rear wall; a nozzle extension section is connected to the rear end of the tail section of the nozzle; a mounting position is provided on one side, directly facing the left side wall, of the nozzle extension section, a laminar flow flatplate with a second optical window is installed in the mounting position, and at least two first optical windows and a second optical window are located on the same optical path. The transient wavefront test platform realizes the moving downstream of a test diamond zone to a flow field by extending the rear end of the original axisymmetric nozzle, so that a test model can be located in an ideal test diamond zone of the axisymmetric nozzle to ensure the test state and the reliability of the result.
Description
technical field [0001] The invention relates to the experimental field of transient aero-optical effect wavefront measurement, in particular to a transient wavefront test platform and system based on a hypersonic pulse wind tunnel. Background technique [0002] When a new generation of high-speed imaging-guided missiles flies at high speed in the atmosphere, affected by the change of flow field density near the guidance window, the target image received by the detector will appear offset, shake and blur, which is commonly known as the aero-optical effect. This effect will reduce the accuracy of imaging guidance, thereby affecting the damage effect. In order to correct the above phenomena, it is necessary to conduct in-depth research on the aero-optic effect, and one of the most feasible methods is to build an aero-optic effect test platform on the ground that may be comparable to the flight environment, and analyze the transient aero-optic wavefront Make reliable measuremen...
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IPC IPC(8): G01M9/04G01M9/06
CPCG01M9/04G01M9/06
Inventor 易仕和丁浩林葛勇陆小革赵鑫海何霖
Owner NAT UNIV OF DEFENSE TECH