Finite element method based aircraft cabin door seal load computing method

A finite element and aircraft technology, which is applied in the field of aircraft door seal load calculation, can solve problems such as moment calculation, and achieve the effect of improving solution efficiency and ease of use

Active Publication Date: 2016-01-20
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Abstract
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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 aircraft door sealing load calculation method based on the finite element method, solve the problem of moment calculation caused by the sealing in the automatic opening and closing process of the aircraft door

Method used

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  • Finite element method based aircraft cabin door seal load computing method
  • Finite element method based aircraft cabin door seal load computing method
  • Finite element method based aircraft cabin door seal load computing method

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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 finite element method based aircraft cabin door seal load computing method. The sealing strip stress condition is simplified to be a plane strain state; modeling, loading and definition contact are performed on a sealing strip, a support and a cabin door, so as to resolve the stress for compression of the sealing strip per unit length, and the sealing strip is between the support and the cabin door; a revolute pair is defined at a hinge of the cabin door and rotation angular displacement is restrained, and pressure equivalent to the sealing compression force of per unit length is applied on the cabin door at the sealing position, so as to obtain bending moment of the hinge, namely, the cabin door seal load. The method solves the problem of moment computation caused by sealing in automatic closing and opening of the aircraft cabin door, provides design basis for design of an automatic closing and opening mechanism of the cabin door, and is initiative at home.

Description

technical field [0001] The invention relates to a method for calculating the sealing load of an aircraft cabin door based on a finite element method, 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 in...

Claims

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Application Information

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Patent Type & Authority Applications(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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