Method for optimizing local finite element model of aircraft cabin door and fuselage contact area

Abstract

The invention discloses an optimization method for a local finite element model of a contact area of an aircraft cabin door and a fuselage, and the optimization method comprises the steps: firstly obtaining the equivalent stiffness of the aircraft cabin door and the fuselage, then building the local finite element model of the contact area of the aircraft cabin door and the fuselage, and setting a spring unit in the local finite element model; simulating and applying an equivalent load to the local finite element model, and comparing the deformation with the equivalent stiffness to obtain a stiffness coefficient of each spring unit; and finally, adding a stiffness coefficient into the local finite element model to realize optimization of the local finite element model. By introducing the equivalent stiffness of the aircraft cabin door and the fuselage, organic combination of the overall structural characteristics of the aircraft cabin door and the fuselage and the stress state of the aircraft cabin door and the fuselage at the contact point is realized, so that the overall structural stiffness of the aircraft is inherited and reflected in local stress analysis; and the calculation precision of aircraft cabin door and fuselage assembly contact mechanics is improved.

Description

technical field [0001] The application relates to the technical field of aviation manufacturing, in particular to an optimization method for a local finite element model of the contact area between an aircraft door and a fuselage. Background technique [0002] When the aircraft door and the fuselage are assembled together, the door will be opened and closed. Due to the influence of manufacturing, assembly errors and external loads, it may not be possible to achieve no step difference and no gap between the aircraft door and the fuselage after closing. , Interference-free fit; if there is no contact between the aircraft door and the fuselage, there will be a step or gap between the aircraft door and the fuselage, which will affect the aerodynamic performance and appearance of the aircraft, but will not Cause damage and damage; if there is interference and extrusion between the aircraft door and the fuselage, it will cause contact and extrusion deformation between the aircraft...

AI Technical Summary

Problems solved by technology

[0004] The main purpose of this application is to provide an optimization method for the local finite element model of the contact area between the aircraft door and the fuselage, aiming at solving the calculation of the stress, strain and deformation parameters of the local structure after the aircraft door and the fuselage contact in the prior art The defect of low precision

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