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Aircraft structure and crashworthiness analysis method thereof

An aircraft and bulkhead technology, which is applied to instruments, special data processing applications, electrical digital data processing, etc., can solve the problems of poor safety performance of aircraft and poor coordination of component layout, and achieve simple structure, enhanced crashworthiness, The effect of good stability

Pending Publication Date: 2022-03-22
HUNAN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The main purpose of the present invention is to provide an aircraft structure and its crashworthiness analysis method, aiming to solve the technical problems of poor aircraft safety performance and poor coordination between components in the prior art

Method used

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  • Aircraft structure and crashworthiness analysis method thereof
  • Aircraft structure and crashworthiness analysis method thereof
  • Aircraft structure and crashworthiness analysis method thereof

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Embodiment Construction

[0056] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the implementation manners in the present invention, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0057] It should be noted that all directional indications (such as up, down, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship, movement conditions, etc. between the components in a certain posture (as shown in the drawings), If the specific posture changes, the directional indication also changes accordingly.

[0058] In addition, in the present invention, descript...

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Abstract

The invention provides an aircraft structure and a crashworthiness analysis method thereof. The aircraft structure comprises a skin, a bulkhead, a passenger cabin floor, a cross beam, a longitudinal beam and a supporting piece. The skin is arc-shaped, the bulkhead extends along the bending direction of the skin, the cross beam is connected with two ends of the bulkhead, the passenger cabin floor is arranged on the cross beam, and the longitudinal beam is connected with the cross beam; the upper supporting plate is installed at the end, close to the longitudinal beam, of the supporting piece, the lower supporting plate is installed at the end, close to the skin, of the supporting piece, the hinging piece comprises the upper hinging piece and the lower hinging piece, the upper supporting plate is hinged to the longitudinal beam through the upper hinging piece, and the lower supporting plate is hinged to the skin through the lower hinging piece. The aircraft structure is simple in structure, the crashworthiness of an aircraft is enhanced, the aircraft can be gradually damaged in a falling collision accident, and the stability of the crushing process is guaranteed.

Description

technical field [0001] The invention relates to the technical field of fuselage structures, in particular to an aircraft structure and a crashworthiness analysis method thereof. Background technique [0002] Aircraft such as rotorcraft, helicopters, and large and medium-sized civil aircraft have become an indispensable part of people's daily life. Researchers have conducted a lot of research on the structural design of aircraft, and relevant institutions have also formulated relevant regulations on aircraft safety and lightweight design. Airworthiness Regulations. With the gradual maturity of aviation manufacturing technology and the gradual application of advanced composite materials, higher requirements are put forward for the structural design of aircraft. [0003] The fuselage structure is an important part of an aircraft. The fuselage structure not only bears the weight of its own structure such as wings, empennages, and landing gear, but also bears external loads such...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/17G06F30/23G06F119/02
CPCG06F30/15G06F30/17G06F30/23G06F2119/02
Inventor 任毅如吕睿金其多
Owner HUNAN UNIV
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