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A FEM-Based Analysis Method for Aircraft Door Sealing Load

A finite element and aircraft technology, applied in the direction of instruments, calculations, electrical digital data processing, etc., can solve problems such as torque calculations, and achieve the effect of improving solution efficiency

Active Publication Date: 2018-07-06
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to overcome the deficiencies in the prior art, provide a kind of method based on finite element method for analysis of aircraft hatch seal load, solve the problem of torque calculation caused by sealing in the process of automatic opening and closing of aircraft hatch

Method used

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  • A FEM-Based Analysis Method for Aircraft Door Sealing Load
  • A FEM-Based Analysis Method for Aircraft Door Sealing Load
  • A FEM-Based Analysis Method for Aircraft Door Sealing Load

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Embodiment 1

[0054] The material properties of each part of a hatch are shown in Table 1. The inner diameter of the section of the sealing strip is 7mm, the outer diameter is 10mm, and the compression amount is 5mm. Using the above-mentioned relay solution method for seal load design, the deformation and stress of the seal strip are obtained. The compression force of the seal strip is 0.8274N / mm; the door seal load moment is 151.6N·m.

[0055] Table 1

[0056]

[0057] The method of the invention has been applied to model design, and the air vehicle door sealing load calculated by the method provides a design basis for the aircraft door opening and closing mechanism.

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Abstract

The invention relates to a method for calculating the sealing load of an aircraft cabin door based on the finite element method, which simplifies the stress of the sealing strip into a plane strain state, models, loads and defines the contact of the sealing strip, bracket and hatch, and obtains the unit length sealing The force required for strip compression, the sealing strip is between the bracket and the hatch; the rotary joint is defined at the hinge of the hatch and the rotational angular displacement is constrained, and at the same time, a pressure equivalent to the sealing compression force per unit length is applied to the hatch at the sealing position, so that The supporting reaction moment of the hinge is obtained, which is the door sealing load. The calculation method of the invention solves the moment calculation problem caused by the sealing during the automatic opening and closing process of the aircraft cabin door, and provides design basis for the design of the automatic opening and closing mechanism of the cabin door, which is the first in China.

Description

technical field [0001] The invention relates to a method for analyzing the sealing load of an aircraft cabin door based on finite elements, and belongs to the field of aircraft mechanism design. Background technique [0002] The hatch is an important part of the aircraft. It consists of two large-scale, space-curved open hatches and an opening, closing, and locking mechanism. It can automatically repeat opening, closing, and locking, and has a good seal. performance. The boundary seal of the hatch door generates a load moment on the opening and closing mechanism and the locking mechanism during the closing process of the hatch door. How to accurately calculate the load moment of the hatch door seal is one of the key technologies in the design of the hatch mechanism. On the one hand, the sealing load is an input condition for the design of the door mechanism, which must be carried out in the early stage of design; on the other hand, the door sealing includes the interaction ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 郭爱民穆星科吴迪刘维玮王悦肖凯王月苏玲姚世东李永俊邓云飞
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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