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Piece type hinge moment balance

A technology of hinge torque and balance, applied in the field of aerodynamic force measurement in aerospace dynamometer test, to achieve the effect of increasing matching, eliminating measurement error and excellent measurement sensitivity

Inactive Publication Date: 2015-12-02
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to overcome the deficiencies of the existing traditional piece hinge moment balance measurement and improve the accuracy of measurement. The present invention provides a piece hinge moment balance

Method used

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  • Piece type hinge moment balance

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Embodiment Construction

[0027] The piece hinge moment balance of the present invention is an integral piece structure of all steel parts. The hinge moment balance is composed of three parts: a fixed connection end, a balance element and a floating connection end. The two floating connection ends are connected to the measuring rudder of the aircraft through screws and pins. , the balance element is composed of a measuring beam and an adjusting beam, and the fixed connection end is connected with the stabilizer surface of the model through screws and pins. The piece hinge moment balance of the present invention has a single fixed support and double floating symmetrical structure, that is, two floating connection ends and four sets of balance elements are symmetrically arranged on both sides of the fixed connection end; The aerodynamic structure; the measuring beam and the adjusting beam of the hinge moment balance element are arranged horizontally. The bridge assembly method of the hinge moment balance...

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Abstract

The invention discloses a piece type hinge moment balance. The balance is of an all-steel overall piece type integrated structure, and comprises a fixed connection end, four groups of balance components and two floating connection ends, wherein two ends at the same horizontal plane of the fixed connection end are provided with rigid transition sections respectively; the four groups of balance components are distributed at two sides of the rigid transition sections of the fixed connection end; and the inner side of each floating connection end is provided with a rigid transition section, and the two floating connection ends are connected with the balance components. According to the structure of the piece type hinge moment balance, the additional moment of the balance can be reduced, the matching performance of loads is improved, and aerodynamic force measurement with an axial force can be realized. Meanwhile, interference imposed on measurement by wing deformation can be reduced, thereby enabling the uncertainty of measurement to be significantly reduced, and acquiring an aerodynamic force measurement result with high precision and accuracy.

Description

technical field [0001] The invention belongs to the technical field of aerodynamic force measurement for aerospace dynamometer tests. Aiming at the hinge moment wind tunnel dynamometer test of a hypersonic aircraft model, a hinge moment balance with a single fixed support and double floating symmetrical structure is used to complete the alignment of the aircraft. The hinge moment measurement of the wing control control surface improves the measurement accuracy. Background technique [0002] The hinge moment measurement test is a basic wind tunnel force test item. With the development of my country's aerospace technology, especially the development of advanced aircraft development, the quality requirements for hinge torque test data are getting higher and higher. For a long time, limited by the size of the model space, aerodynamic load conditions, and the structure of the balance, the traditional hinge moment balance used to measure the hinge moment of the control surface of...

Claims

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Application Information

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IPC IPC(8): G01M9/06
Inventor 王树民王超潘华烨米鹏谢斌向光伟陈丽唐新武王玉花刘维亮贾巍谭显慧马涛
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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