Supporting component used for wind tunnel test

Abstract

The invention provides a supporting component used for a wind tunnel test, and relates to the field of the wind tunnel test. According to the supporting component, a curved tail supporting rod supporting structure is provided, and the tail supporting rod is designed into at least three sections which are different in axis so that the airflow obstruction reverse interference of the tail supporting rod for a test model can be reduced, and the pneumatic data of the test model can be more accurately measured; the angle and the length of each section of the tail supporting rod are changed so that the tail supporting rods of a separating test model and a separated test model which are close to each other are enabled to maintain a large distance in space, and mutual interference in the separating test process can be avoided and influence on the test result can be avoided; meanwhile, a tail supporting rod fixing part matched with the tail supporting rod is designed, a measurement component of certain height is fixedly installed, and measurement of the distance between the model reference center of gravity and the balance calibration center of the wind tunnel test model can be realized through the measurement component and the measurement accuracy of the whole device can be guaranteed within 0.1mm.

Description

technical field [0001] The invention relates to a support assembly for wind tunnel tests, belonging to the technical field of wind tunnel tests. Background technique [0002] In the process of designing the aerodynamic shape of various aircraft, the wind tunnel test has been and is always the purpose of discovering and confirming the flow phenomenon, exploring and revealing the flow mechanism, seeking and understanding the flow law, and providing excellent aerodynamic layout and aerodynamics for the aircraft. Primary means of characterizing data. It is precisely because of the importance of the wind tunnel test that the precision control and efficiency control of each technical link of the wind tunnel test can ensure the high quality, high efficiency and smooth progress of the test. [0003] In the wind tunnel test program, whether the preparation before the test is sufficient or not is related to the difficulty of data processing during and after the test, and the force te...

AI Technical Summary

Problems solved by technology

However, with the diversified development of aircraft dimensions and functions, the straight strut tail support structure can no longer meet the requirements of all tests. For example, in the wind tunnel multi-body separation and delivery (CTS) test, the separation model will The airflow of the strut interferes, and when it is supported by a straight strut, it will collide with the parent machine model. Therefore, a non-straight strut type tail support structure that meets the test requirements is urgently needed. For the non-straight strut type Structure, when measuring L0 with the above method, not only will there be reading errors, but also large measurement operation errors will occur. When L0 is small, for example, only a dozen millimeters, the above errors will cause a large error in the final result test data

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