Method for measuring bending moment of high-aspect-ratio wing surface by using angular velocity sensor

An angular velocity sensor, angular velocity technology, applied in the direction of velocity/acceleration/shock measurement, measurement device, measurement acceleration, etc., to achieve the effect of solid theoretical basis, long-term monitoring, and simple system architecture

Active Publication Date: 2019-11-22
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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[0004] The purpose of this application is to provide a method for measuring the bending moment of a lar

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  • Method for measuring bending moment of high-aspect-ratio wing surface by using angular velocity sensor
  • Method for measuring bending moment of high-aspect-ratio wing surface by using angular velocity sensor
  • Method for measuring bending moment of high-aspect-ratio wing surface by using angular velocity sensor

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[0022] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of the application will be described in more detail below in conjunction with the drawings in the embodiments of the application. In the drawings, the same or similar reference numerals indicate the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of the present application, rather than all of the embodiments. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the application, but should not be understood as a limitation to the application. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of this application. The embodiments of the present applic...

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Abstract

The application belongs to the field of aircraft strength design and particularly relates to a method for measuring the bending moment of a high-aspect-ratio wing surface by using an angular velocitysensor. The method comprises the steps of (1) acquiring the bending rigidity of an attention section, (2) setting the angular velocity sensor on the attention section and measuring the angular velocity of the attention section through the angular velocity sensor, (3) processing the angular velocity of the attention section to obtain the roll angle acceleration of the attention section, and (4) obtaining the bending moment of the attention section according to the bending rigidity and the roll angle acceleration. The angular velocity sensor parameters of the invention can be directly entered into a flight parameter recording system, the additional modification of an aircraft test system is not needed in all bending moment measurement with the angular velocity sensor, the system architecture is simple, the bending moment of the wing surface can be accurately and effectively monitored in long term, a large amount of flight test data can be accumulated, and a data support is provided forimproving design and compiling a load spectrum.

Description

technical field [0001] The application belongs to the field of aircraft strength design, in particular to a method for measuring the bending moment of a large-aspect-ratio wing by using an angular velocity sensor. Background technique [0002] Wing surface load is an important input in the process of aircraft design. During the flight test, the actual flight load needs to be measured to provide a basis for load calibration and perfect design. In order to achieve the unification of flight, load and strength design and reduce the risk of development, it is necessary to accurately obtain the load of specific parts. Conventional load measurement methods include strain measurement and pressure measurement, and the load measurement system is relatively complicated. [0003] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art. Contents of the invention [0004] The purpose of th...

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Application Information

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IPC IPC(8): G01M13/00G01M5/00G01P15/00B64F5/60
CPCG01M13/00G01M5/0016G01P15/00B64F5/60
Inventor 李伟郭敬闫雨哲
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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