A device for reducing the working force of the rotating continuous adjustable wind tunnel nozzle
A technology of nozzle adjustment and wind tunnel, which is applied in the direction of measuring device, aerodynamic test, machine/structural component test, etc. It can solve the problem of wide range of actuation force variation, precise control of the influence of nozzle throat height, actuation force Large and other issues, to achieve the effect of avoiding large changes
Active Publication Date: 2018-04-17
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
[0004] Purpose of the invention: In order to overcome the deficiencies in the prior art, the present invention proposes a device for reducing the adjusting power of the nozzle of the continuously adjustable wind tunnel with profile rotation, which is used to solve the problem of the existing wind tunnel with continuously adjustable profile rotation During the adjustment process of the nozzle, the force required to rotate the wall of the nozzle is too large, and the range of change of the force is wide, which affects the precise control of the nozzle throat height and the technical problems of the practical application and promotion of the wind tunnel nozzle
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[0020] The present invention will be further described below in conjunction with the accompanying drawings.
[0021] Such as figure 1 As shown, a reduced-profile rotating continuously adjustable wind tunnel nozzle regulating power device according to the present invention includes a cylinder 1 , a piston upper rod 2 , a piston 3 , a piston lower rod 4 and a sealing ring 5 . During the nozzle test, the incoming high-pressure gas 7 flows into the wind tunnel nozzle, and part of it flows into the cylinder 1 through the high-pressure conduit 6, so that the closed space formed by the cylinder 1 and the piston 3 is filled with high-pressure gas, and the lower end of the piston 3 is the nozzle The back pressure of the outlet environment, thus forming a pressure difference between the upper and lower ends of the piston 3, that is, P*-P b .
[0022] The moment M of the nozzle wall surface acting on the nozzle expansion wall surface of the wind tunnel nozzle rotating part 8 by the gas...
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The invention discloses a device used for reducing profile rotation continuously adjustable wind tunnel nozzle adjusting actuating force. The device comprises a cylinder and an actuating piston, and the actuating piston comprises a piston, a piston upper end rod, a piston lower end rod, and a sealing ring. The actuating piston is disposed in the cylinder, and the piston lower end rod is connected with a nozzle adjusting part. The piston upper end rod is connected with a driving system, and the closed space formed by the cylinder and the piston is filled with the wind tunnel nozzle incoming flow high pressure gas. The nozzle lower surface is the nozzle outlet environmental backpressure. The upper surface and the lower surface of the piston of the system are disposed in different pressure environments, the pressure difference between the upper surface and the lower surface of the piston can be formed, and then the downward action force can be applied on the piston, and then can be transmitted to the wind tunnel nozzle rotating part by the piston lower end rod to offset most of the upper differential pressure force applied on the nozzle wall surface caused by the inside-outside pressure difference, and therefore according to the driving system, the nozzle wall surface can be driven to actuate by the small driving force via the force-reducing device.
Description
technical field [0001] The invention relates to the field of wind tunnel design and testing, in particular to an actuating device for adjusting the wall surface of a nozzle in a wind tunnel with continuously adjustable surface rotation. Background technique [0002] With the rapid development of the aerospace field, many cutting-edge issues require that the Mach number of the wind tunnel test section cannot always be kept at a single Mach number during aerodynamic tests. It is the key point in the research and development process of various aircraft, and in many cases they limit the overall performance of the aircraft. For example, the problem of not starting the inlet of the hypersonic vehicle during the acceleration process, the performance change of the TBCC combined engine during the conversion process, etc. These problems are the focus and difficulty in the development of the aircraft. Only by solving these difficulties can the performance of the aircraft be broken thr...
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IPC IPC(8): G01M9/04
CPCG01M9/04
Inventor 徐惊雷齐伟呈范志鹏俞凯凯吕郑莫建伟
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS