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Design and use method of device for testing simultaneous deflection angle of balance and control surface

A technology of deflection angle and test device, which is applied in the field of wind tunnel test to achieve the effect of ensuring installation and positioning, reducing temperature effects, and avoiding coordinate system conversion

Active Publication Date: 2022-02-01
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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  • Design and use method of device for testing simultaneous deflection angle of balance and control surface
  • Design and use method of device for testing simultaneous deflection angle of balance and control surface
  • Design and use method of device for testing simultaneous deflection angle of balance and control surface

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[0047] The present invention will be further described in detail below in conjunction with the accompanying drawings, so that those skilled in the art can implement it with reference to the description.

[0048] It should be understood that terms such as "having", "comprising" and "including" used herein do not exclude the presence or addition of one or more other elements or combinations thereof.

[0049] It should be noted that in the description of the present invention, the orientation or positional relationship indicated by the term is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply No device or element must have a specific orientation, be constructed, and operate in a specific orientation and therefore should not be construed as limiting the invention. In addition, the terms "first" and "second" are used for desc...

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Abstract

The invention discloses a design and use method of a device for testing the simultaneous deflection angle of a balance and a control surface. The device comprises: a model body which is provided with a cylindrical hole, wherein two reference circles which take the central point of the cylindrical hole as the center of a circle are respectively provided with a circle of taper pin holes I; and a hinge moment balance comprising a model end, wherein the lower end of the model end is integrally provided with a measuring element, and the upper end of the model end is connected with a measuring rudder; a fixed end is integrally processed at the lower end of the measuring element; and the fixed end is provided with a fan-shaped flange face coaxial with the measuring element, the fan-shaped flange face is provided with two circles of taper pin holes II, the diameter of a reference circle where the two circles of taper pin holes II are located is correspondingly equal to the diameter of a reference circle where the two circles of taper pin holes I are located, and the bottom of the fan-shaped flange face is provided with a cylindrical section. According to the invention, the conversion of the rudder deflection angle can be realized by aligning the taper pin hole II with the taper pin hole I of the model body in a model space with a smaller axial size and a larger radial size, so that the conversion of a coordinate system is avoided, and the conversion efficiency of the rudder deflection angle is improved.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel test, and more specifically, the invention relates to the design and use method of a test device for the simultaneous deflection angle of a balance and a rudder surface. Background technique [0002] The hinge moment test of the model rudder surface is one of the important wind tunnel test items in the development stage of the aircraft. and provide a basis for structural design. [0003] When carrying out the hinge moment test, the reliable transformation of the rudder deflection angle has a decisive influence on the test data. At present, the commonly used rudder deflection angle transformation methods mainly include the following two methods: (1) angle piece positioning, screw compression; (2) fixed deflection angle overall processing. The first method requires the model to have enough axial space, and the angle piece and the compression screw are placed on the premise of ensuring sufficie...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/00G01M9/06G01M9/08B64F5/60
CPCG01M9/00G01M9/062G01M9/08B64F5/60Y02T90/00
Inventor 舒海峰向立光许晓斌
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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