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Skeletonless fuselage aircraft with ducted lifting body and design method of fuselage structure

A structural design and aircraft technology, applied in the field of aircraft, can solve the problems of complex fuselage structure and heavy fuselage structure, and achieve the effects of increasing effective load, reducing structural weight, and improving weight efficiency

Active Publication Date: 2020-11-24
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a frameless fuselage structure with a ducted lifting body and its design method to solve the problem that the fuselage structure in the prior art is too complicated, resulting in the overall overweight of the fuselage structure

Method used

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  • Skeletonless fuselage aircraft with ducted lifting body and design method of fuselage structure
  • Skeletonless fuselage aircraft with ducted lifting body and design method of fuselage structure
  • Skeletonless fuselage aircraft with ducted lifting body and design method of fuselage structure

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Experimental program
Comparison scheme
Effect test

Embodiment approach 1

[0045] a) Making an integrated core material by machining or compression molding;

[0046] b) Use dry glass cloth or carbon cloth to glue to the core material at room temperature to form a skin;

[0047] c) Embedded support structures embedded in rotor or equipment installations.

Embodiment approach 2

[0049] a) Making block core materials by machining or compression molding;

[0050] c) bonding the segmented core materials together by means of cementation to form a complete core material;

[0051] c) Glass cloth prepreg or carbon cloth prepreg is glued to the core material to form a skin under heating and pressure;

[0052] d) Embedded support structures embedded in rotor or equipment installations.

Embodiment approach 3

[0054] a) Making an integrated core material by machining or compression molding;

[0055] b) Glass cloth prepreg or carbon cloth prepreg is glued to the core material to form a skin under heating and pressure;

[0056] c) Embedded support structures embedded in rotor or equipment installations.

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Abstract

The invention relates to a skeleton fuselage-free aircraft with a ducted lift body. The skeleton fuselage-free aircraft comprises a fuselage structure, a supporting structure and rotating wings. The fuselage structure is manufactured by a solidification technology of a core material and a skin attached to the surface of the core material. The fuselage structure is provided with wings used for providing lifting force for the aircraft and ducts used for installing the rotating wings. The supporting structure is embedded in the ducts of the fuselage structure. The supporting structure adopts thesolidification technology of core material arranging before or after the skin is solidified at the core material. The rotating rings are mounted in the ducts, are connected with the fuselage by the supporting structure, and are used for providing the aircraft with power. Through design of the fuselage structure, the physical design can be light-weighted through the efficient aircraft, structure weigh can be effectively reduced, effective load of the aircraft can be increased, weight efficiency can be improved, and the manufacturing cost can be lowered.

Description

technical field [0001] The invention relates to the field of aircraft, in particular to a frameless fuselage structure with a ducted lifting body and a design method thereof. Background technique [0002] Aircraft in the prior art are generally divided into two types, one is a fixed-wing aircraft, and the other is a rotary-wing aircraft. Compared with a rotary-wing aircraft, a fixed-wing aircraft has advantages such as long range, fast speed, and heavy load. But for fixed-wing aircraft, its fuselage and wing structure weight generally account for more than 30% of the total weight of the aircraft. If the fuselage structure-to-weight ratio is too large, the power efficiency will be reduced. [0003] However, the existing aircraft structure is not highly integrated, requiring many parts to be riveted or cemented, which increases the weight of the structure, increases the complexity of processing and assembly, and increases the production cost. Contents of the invention [0...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/20B64C39/10B64F5/00
CPCB64C27/20B64C39/10B64F5/00
Inventor 刘衍涛曹元宝曾加刚王磊
Owner CHINA HELICOPTER RES & DEV INST
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