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A method for designing lateral stiffness of an aircraft large-opening structure

A technology of lateral stiffness and design method, applied in the direction of calculation, special data processing applications, instruments, etc., can solve the problem of no theoretical basis for the design of large opening fuselage, and achieve the effect of simple method

Pending Publication Date: 2019-05-03
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

[0003] Purpose of the invention: To solve the dilemma that there is no theoretical basis for the design of large-opening fuselage, and to propose a design method for the lateral stiffness of aircraft large-opening structures

Method used

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  • A method for designing lateral stiffness of an aircraft large-opening structure
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  • A method for designing lateral stiffness of an aircraft large-opening structure

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Embodiment Construction

[0032] See attached Figure 1-4 , a method for designing the lateral stiffness of an aircraft large opening structure, comprising the following steps:

[0033] (1) Simplification of the large opening structure model of the aircraft

[0034] For the large opening structure of the aircraft, a girder is usually arranged at the opening for reinforcement. Typical large opening structures of the fuselage are as follows: figure 1 As shown in (a); during the calculation, the area of ​​the stringer is converted into the thickness of the skin, and the simplified calculation model is as follows figure 1 (b) shown.

[0035] figure 1 middle:

[0036] R - fuselage radius;

[0037] f ch — the cross-sectional area of ​​the girder;

[0038] 2ψ——large opening angle;

[0039] f b — the area of ​​the reinforced truss girder at the opening;

[0040] δ mp - skin thickness;

[0041] δ x - the reduced thickness of the skin,

[0042] the s k — the length of the perimeter of the cross ...

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Abstract

The invention belongs to the technical field of aircraft structure design, and particularly relates to a lateral rigidity design method for an aircraft large-opening structure. The method is realizedthrough the following steps: simplifying an airplane large-opening structure model; calculating the lateral bending rigidity EIz of the large opening structure of the aircraft; the lateral bending stiffness ratio of the aircraft non-opening structure is shown in the specification; the lateral bending stiffness ratio of the aircraft non-opening structure is shown in the specification; the lateral bending stiffness ratio of the aircraft non-opening structure to the lateral bending stiffness ratio of the aircraft non-opening structure to the lateral bending stiffness ratio is shown in the specification; and how to reinforce the structure under the condition of meeting the lateral stiffness requirement can be determined according to the expression of the lateral bending stiffness ratio.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure design, and in particular relates to a method for designing the lateral stiffness of an aircraft large opening structure. Background technique [0002] The large opening area of ​​the cargo door of a transport aircraft not only bears the load of the cargo door itself, but also bears and transmits the load of the empennage and the rear fuselage. Because the large opening of the fuselage changes the rigidity of the structure rapidly, resulting in discontinuous deformation and other problems, the strengthening design of the large opening of the fuselage has become the focus and difficulty of the design of transport aircraft. In order to minimize the impact of the large opening area on the fuselage and meet the requirements of continuous stiffness and coordinated deformation, the opening area must be strengthened. However, the technical information on the design of the large opening of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 苏雁飞薛应举赵占文
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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