Electromagnet suspension throwing device for free flight test of hypersonic wind tunnel model

A hypersonic and delivery device technology, applied in the direction of measuring devices, aerodynamic tests, machine/structural component testing, etc., can solve problems such as obvious interference of the support system, influence of test results, and difficult to eliminate, so as to achieve accurate flight trajectory, The effect of compact mechanical design and high efficiency

Active Publication Date: 2021-01-29
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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  • Abstract
  • Description
  • Claims
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Problems solved by technology

When the model is constrained, the interference generated by the support syste...

Method used

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  • Electromagnet suspension throwing device for free flight test of hypersonic wind tunnel model
  • Electromagnet suspension throwing device for free flight test of hypersonic wind tunnel model
  • Electromagnet suspension throwing device for free flight test of hypersonic wind tunnel model

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Embodiment 1

[0048] The working process of this embodiment is as follows:

[0049] a. the electromagnet suspension throwing device for hypersonic wind tunnel model free flight test of the present invention is fixed on the upper angle-of-attack mechanism of the hypersonic wind tunnel test section angle-of-attack mechanism by installing the upper end of support plate 1;

[0050] b. Power on the adsorption electromagnet 3, adsorb the model 4 on the model adaptation interface 302 of the adsorption electromagnet 3, adjust the position of the model 4, measure and ensure that the axial position of the model 4 is accurate;

[0051] c. Hold the handle at the bottom of the model rack, lift the model 4 from bottom to top, and place the model 4 in the inner conical surface of the inner cavity of the model rack. On the interface 302, measure and ensure that the axial position of the model 4 is accurate, and the adsorption electromagnet 3 is powered off;

[0052] d. In the preparation process of the hy...

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Abstract

The invention discloses an electromagnet hanging and throwing device for a free flight test of a hypersonic wind tunnel model. The device comprises a mounting support plate, a mounting base and an adsorption electromagnet which are sequentially connected from top to bottom, wherein the upper end of the mounting support plate is fixed on an upper attack angle mechanism of a hypersonic wind tunnel test section attack angle mechanism, and the lower end of the adsorption electromagnet adsorbs a model. The device also comprises a driver which is fixed on the mounting support plate, the model fixingdevice is fixed on the mounting base, and the driver controls the model fixing device to clamp or release the model. During test preparation, a power supply for adsorbing the electromagnet is turnedoff, and the model fixing device clamps and fixes the model; before testing, a power supply of the adsorption electromagnet is turned on, the model fixing device is withdrawn, and the adsorption electromagnet adsorbs and fixes the model; in the test process, the electromagnet is adsorbed to power off and release the model. The device is compact in structure, reasonable in layout, good in stabilityand high in reliability, and can meet the requirement of quickly putting the model in the free flight test process of the hypersonic wind tunnel model.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel model free flight test, and in particular relates to an electromagnet suspension delivery device used for hypersonic wind tunnel model free flight test. Background technique [0002] With the expansion of the flight envelope of modern fighter jets and missiles, the nonlinear flow phenomena that appear during maneuvering at high angles of attack and with sideslips will have a strong impact on the dynamic stability of the aircraft. To predict the dynamic characteristics of the aircraft, it is necessary to establish a dynamic model of the aircraft and obtain the dynamic stability derivative, which is an important prerequisite and basis for effective aircraft control system design, flight quality evaluation and ground simulation. [0003] The dynamic stability research of aircraft mainly relies on flight test and wind tunnel simulation test at present. The wind tunnel test methods for ...

Claims

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Application Information

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IPC IPC(8): G01M9/02G01M9/04G01M9/08
CPCG01M9/02G01M9/04G01M9/08
Inventor 何超谢飞许晓斌舒海峰张德炜吴友生唐友霖
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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