Plate-type hinge moment balance

A hinge torque and balance technology, applied in the field of plate hinge torque balance, achieves the effects of reliable positioning, high rigidity and reliable connection

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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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The shape of the aircraft and the structural form of the control rudder are various. At present, there is no general structure of the hinge moment test balance that can meet the test requirements of the hinge moment of all aircraft rudder surfaces. The present invention is mainly aimed at small radial dimensions and large ax

Method used

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Embodiment Construction

[0039] 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.

[0040] 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.

[0041] 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 plate-type hinge moment balance. The balance comprises: a model end which is of a cuboid structure, is provided with a rectangular groove, and is fixedly connected with a measurement rudder; measuring elements comprising a measuring element I and a measuring element II, wherein the measuring element I is fixedly connected with the model end; and a fixed end which is of a concave structure, and is fixedly installed on the model body, wherein the opening side of the concave structure of the fixed end faces the measuring element II, the fixed end is fixedly connected with the measuring element II, and a partition plate is fixedly connected between the measuring element I and the measuring element II. The front edge of the fixed end is flush with the front edge of the partition plate, and a gap is formed between the inner wall of the fixed end and the partition plate. The advantage that the model is large in axial size along the control surface is fully utilized, and the defect that the radial size along a control surface rotating shaft is small is overcome; the rudder deflection angle is simple to replace and reliable to position; and the five-component hinge moment balance is simple in structure and high in rigidity, measuring elements adopt equal-strength beams, and a strain uniform area is large.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, and more specifically, the invention relates to a plate hinge moment balance. Background technique [0002] The hinge moment balance is the core component of the hinge moment wind tunnel test. The connection mode between the balance and the rudder surface, the connection mode between the balance and the main body of the model, and the angle transformation method of the rudder surface are all closely related to the accuracy of the test data. [0003] The shape of the aircraft and the structural form of the control rudder are various. At present, there is no general structure of the hinge moment test balance that can meet the test requirements of the hinge moment of all aircraft rudder surfaces. [0004] At present, there are two main installation and positioning methods for measuring rudders: (1) taper fit, flat key positioning, and wedge key tensioning; (2) measuring rudder and balance...

Claims

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Application Information

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IPC IPC(8): G01M9/06B64F5/60
CPCG01M9/062B64F5/60Y02T90/00
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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