Measuring device and method for surface pressure of aircraft seam wing skin
A surface pressure measurement and slat technology, which is applied in the direction of aircraft component testing, etc., can solve the problems of affecting the heat transfer characteristics of the internal flow field distribution of the aircraft, affecting the validity of the measurement data, and requiring too high processing technology, so as to save manpower The effect of cost and economic cost, guarantee accuracy and effectiveness, simple operation
Inactive Publication Date: 2017-10-20
COMAC +1
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Problems solved by technology
[0006] The technical problem to be solved by the present invention is to overcome the measurement method of the aircraft slat surface pressure in the prior art, which will affect the distribution of the internal flow field and the heat transfer characteristics of the internal flow field of the aircraft, resulting in deviation of the measurement results, and the requirements for the processing technology It is too high, and the pressure measuring tube is easy to fall off, which affects the validity of the measurement data. A device and method for measuring the surface pressure of the aircraft slat skin is proposed.
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[0028] The preferred embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings. The following descriptions are exemplary and not limiting to the present invention. Any other similar situations also fall within the protection scope of the present invention.
[0029] In the following detailed description, directional terms, such as "left", "right", "upper", "lower", "front", "rear", etc., are used with reference to directions described in the drawings. Components of embodiments of the present invention may be positioned in a variety of different orientations, and directional terms are used for purposes of illustration and not limitation.
[0030] refer to figure 1 As shown, the surface pressure measuring device of an aircraft slat skin according to a preferred embodiment of the present invention includes a flexible pad 1, a pressure signal collector 3 and a plurality of pressure measuring tubes. A series of pres...
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The invention discloses a measuring device and method for the surface pressure of aircraft seam wing skin. The measuring device for the surface pressure comprises a flexible pad, a pressure signal collector and a plurality of pressure measuring pipes; the upper surface of the flexible pad is provided with a series of pressure measuring holes; the pressure measuring pipes are embedded inside the flexible pad in a mutually separated mode; one end of each pressure measuring pipe communicates to the corresponding pressure measuring hole; the other ends of the pressure measuring pipes are guided out from one side face of the flexible pad, so that pressure measuring pipe connecting heads are exposed; the pressure signal collector is provided with a plurality of connectors matched with the pressure measuring pipe connecting heads; and the pressure measuring pipe connecting heads are used for being connected with the connectors in a one-to-one correspondence mode. According to the measuring device and method for the surface pressure of the aircraft seam wing skin, operation is easy, the measuring device can be disassembled and reused, and the accuracy and validity of measured data can be guaranteed to the maximum extent.
Description
technical field [0001] The invention relates to the technical field of aircraft surface pressure measurement, in particular to an aircraft slat skin surface pressure measurement device and method. Background technique [0002] At present, some tests including aircraft ice wind tunnel test technology are becoming more and more important, and the accuracy and rationality of test parameter measurement is an important guarantee for test reliability, and one of the important aspects involves the measurement of surface pressure. Taking the relevant tests of the anti-icing system as an example, in order to verify the performance of the anti-icing system in the ice wind tunnel certification test and flight test of the anti-icing system, it is necessary to simulate and obtain the skin pressure and temperature of the anti-icing leading edge of the system as much as possible. Data, it is necessary to minimize the impact of the installation method of the measurement device for test data...
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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 彭莹霍西恒曾飞雄南国鹏李革萍季佳佳韩志熔
Owner COMAC