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Method for determining structural parameters of circular-arch-shaped reinforcing frame bearing symmetrical concentrated loads

A technology for concentrating loads and structural parameters, applied in electrical digital data processing, special data processing applications, instruments, etc., can solve problems that affect the accuracy of structural parameters and the simulation of boundary conditions is not accurate enough

Active Publication Date: 2021-04-30
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Description
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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for determining structural parameters when the circular arch fuselage reinforcement frame is subjected to symmetrical concentrated loads, so as to overcome the inaccurate simulation of boundary conditions when the traditional method does not consider the bending moment at the support end surface, which affects the structural parameters The problem of precision in optimal design

Method used

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  • Method for determining structural parameters of circular-arch-shaped reinforcing frame bearing symmetrical concentrated loads
  • Method for determining structural parameters of circular-arch-shaped reinforcing frame bearing symmetrical concentrated loads
  • Method for determining structural parameters of circular-arch-shaped reinforcing frame bearing symmetrical concentrated loads

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Embodiment

[0096] Taking the empennage connection frame 72 in the "big opening" area of ​​the rear body of a certain type of transport aircraft as an example, the preliminary strength design of the structural parameters of the "round arch" fuselage reinforcement frame is carried out. Among them, the empennage connection frame 72 frame height H=590mm, the concentrated load action point angle α=9°, the “big opening” angle 2β=132°, the fuselage radius R=2330mm; the reinforcement frame material 7050-T7451, σ b =485MPa, σ 0.2 = 415 MPa.

[0097] Step 1: Calculation of internal force values ​​such as bending moment and shear force at any section of the "circular arch" fuselage reinforcement frame:

[0098] Symmetrical load 102697 working condition, concentrated load P / 2=-412430.1N.

[0099] First, according to the analytical solution of the reaction force of the support end face in step 2 of the present invention, the horizontal reaction force H at the support end face of B can be calculated...

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Abstract

The invention discloses a method for determining structural parameters of an arched reinforcing frame bearing symmetric concentrated loads, which comprises the following steps of: establishing a mathematical model of the arched reinforcing frame, and determining a stress state and a deformation coordination condition of the arched reinforcing frame when the arched reinforcing frame bears the symmetric concentrated loads; The symmetrical concentrated loads are vertical concentrated symmetrical loads applied to the top of the reinforcing frame at the connecting intersection point of the fuselage and the empennage, and when the symmetrical concentrated loads are borne, bending moment in the clockwise or anticlockwise direction is generated on the supporting end face; Determining expressions of bending moment and shearing force of any section of the circular-arch-shaped reinforcing frame; And according to the corner corresponding to any section of the reinforcing frame, the web thickness of any section of the reinforcing frame is determined, and the frame edge strip area of any section of the reinforcing frame is determined. According to the method, the problems that when the bending moment effect is not considered at the supporting end face in a traditional method, boundary condition simulation is not accurate enough, and the accuracy of structural parameter optimization design is affected are effectively solved.

Description

technical field [0001] The invention relates to the field of structural strength design, in particular to a method for determining structural parameters when a circular arch fuselage reinforcement frame bears symmetrical concentrated loads. Background technique [0002] In modern aircraft design, the scheme design, structural layout, and parameter optimization of key connection areas require the intervention of strength designers in advance. Usually, under the condition that the whole aircraft finite element stress solution is not available, the connection is actively designed according to the preliminary load or the load of the same type of aircraft. Preliminary parameters of the typical structure of the area to reduce iteration steps, improve design efficiency, and then grasp the design and optimization direction of the key connection area structure. [0003] Large-scale transport aircraft at home and abroad usually have a large cargo door on the rear fuselage to meet the ...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/20G06F113/28G06F119/14
CPCG06F30/15G06F30/20G06F2113/28G06F2119/14
Inventor 张洪智刘彦杰张彬
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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