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A Design Method for Technological Rigid Parts Used in Aircraft Parts

A technology of aircraft parts and design methods, which is applied in the directions of aircraft parts, ground equipment, transportation and packaging, etc., can solve the problems of unreasonable design of process stiffening parts, increase the weight of aircraft structure, and fail to meet the effect of stiffening, so as to avoid design Blind spots, strong traceability, effects of improved accuracy and effectiveness

Active Publication Date: 2022-01-25
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Abstract
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  • Claims
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Problems solved by technology

[0004] Aiming at the defects of unreasonable design and poor stiffening effect in the prior art, the invention discloses a design method of a craft stiffener for aircraft parts, and the process stiffener can be optimized by adopting the method of the invention The design process of the parts, while avoiding the defect that the weight of the aircraft structure cannot be satisfied while increasing the rigidity effect

Method used

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  • A Design Method for Technological Rigid Parts Used in Aircraft Parts
  • A Design Method for Technological Rigid Parts Used in Aircraft Parts
  • A Design Method for Technological Rigid Parts Used in Aircraft Parts

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Embodiment approach 1

[0062] The present embodiment is a basic embodiment of the present invention, which discloses a design method of aircraft component process gangnifu, in the present embodiment, the aircraft body belly structural component 1 is a gylic object, and its structure figure 2 As shown, it is known from the related process standard that the aircraft body belly structural member 1 is placed in the abdomen in the abdomen, which is not more than 0.1 mm from the self-weight structure.

[0063] like figure 1 As shown, the design method of the process gangnifu according to the present embodiment includes the following steps:

[0064] S1, according to the structural strength, divide the aircraft components into a strong rigid region where the process gigm is required and the strength of the process gigm is required;

[0065] The aircraft structural component is simulated using a finite element analysis method to simulate the deformation of the specified operating conditions, and the amount of de...

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Abstract

The invention discloses a method for designing process stiffening parts for aircraft parts, including the delineation of the area to be stiffened, the determination of the installation point of the process stiffening parts, the material selection of the process stiffening parts, the design of process parameters and the process of stiffening The optimization iteration of parts; the invention standardizes the design process of process stiffening parts, so that technicians can quickly and accurately complete the design of process stiffening parts, and the standardized design process can not only effectively avoid design blind spots, but also has a strong Traceability, when an error occurs, the cause of the error can be quickly and accurately locked, which improves work efficiency and design quality; at the same time, the process stiffening part is connected to the area to be stiffened and the area with high rigidity, effectively ensuring that the process stiffening part is always consistent with the same The rooting point whose strength is higher than that of the area to be stiffened is stably connected to ensure the effective stiffening of the area to be stiffened, avoiding the slipping or even collapse of the process stiffened part under the action of external force, which will cause the stiffness to fail, and improve the stability of the process stiffened part sex and reliability.

Description

Technical field [0001] Technical Field The present invention relates to the assembly, particularly to a method of designing an aircraft component using increasingly rigid member. Background technique [0002] The main role of the aircraft and the structural member is subjected to transfer of each load condition of the aircraft, and the system provides a fixed member, a support, and other transmission carrier, aircraft structural component and therefore meet the accuracy requirements in the manufacture and assembly techniques during the entire aircraft manufacturing process the important part, is an important determinant of the technical requirements of the aircraft can meet. Aircraft structural member or component assembly process is performed, part of the aircraft structural member stiffness is weak, such as the cantilever, the cantilever plate, and the support-frame can not provide support for these areas, when the aircraft is in a certain posture member (e.g. flat state , stan...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00
CPCB64F5/00
Inventor 陈清良冯若琪骆金威陈雪梅舒阳刘元吉潘雨叶翔宇
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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