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Aircraft fuselage with composite pre-form

A technology of prefabricated parts and fuselage, which is applied in the field of aircraft and can solve problems such as the structural complexity of wide-body fuselages

Pending Publication Date: 2019-10-18
AURORA FLIGHT SCI CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] While widebody airframes offer many efficiency improvements, they introduce structural complexity when compared to tubular and elliptical fuselage designs

Method used

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  • Aircraft fuselage with composite pre-form
  • Aircraft fuselage with composite pre-form
  • Aircraft fuselage with composite pre-form

Examples

Experimental program
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Embodiment Construction

[0046] Preferred embodiments of the present disclosure may be described below with reference to the accompanying drawings. In the following description, well-known functions or constructions are not described in detail since they would obscure the disclosure with unnecessary detail.

[0047] In the following description, it should be understood that terms such as "first", "second", "top", "bottom", "side", "front", "rear" are words of convenience and should not be construed is a restrictive term. Moreover, the use of any and all examples, or exemplary language ("such as", "such as", etc.) provided herein, is intended merely to better illuminate the embodiments and does not pose a limitation on the scope of the embodiments. No language in the specification should be construed as indicating that any claimed element is essential to the practice of the embodiments. For this disclosure, the following terms and definitions will apply.

[0048] The terms "air vehicle" and "aircraf...

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PUM

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Abstract

The present invention relates to an aircraft fuselage with composite pre-form. A wide-body aircraft is disclosed with a fuselage section that includes a set of side-by-side fuselage lobes having a fuselage skin. A first woven composite preform positioned at a first intersection of the set of side-by-side fuselage lobes located at a first cusp of the side-by-side fuselage lobes. A second woven composite preform positioned at a second intersection of the set of side-by-side fuselage lobes located at a second cusp of the side-by-side fuselage lobes. Each of the first and second woven composite preforms are configured to receive a structural component, such that each of the first and second woven composite preforms accommodates vertical load imparted through the structural component.

Description

technical field [0001] The present disclosure relates to advanced fuel-efficient aircraft, more particularly to airframes for advanced fuel-efficient aircraft, and even more particularly to airframes having improved structural support elements such as three-dimensional woven composite preform supports and wide-body fuselage to distribute forces from within the fuselage, and involves the use of such support elements. Background technique [0002] There is a strong economic desire to improve the fuel efficiency of commercial aircraft. However, the basic aircraft platform has not changed substantially since the beginning of the commercial jet age. The main commercial aircraft configuration (tube-wing configuration) is a highly optimized and mature platform from which it becomes increasingly difficult to further improve fuel efficiency. Accordingly, alternative commercial aircraft configurations have been explored. [0003] Instead of the traditional tube-wing configuration, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/00B64C1/06B64C1/12B64F5/10
CPCB64C1/00B64C1/068B64C1/12B64F5/10B64C2001/0072B64C2001/0045B64C1/069B64C1/061B64C2001/0036Y02T50/10Y02T50/40
Inventor C·丘奇J·钱伯斯
Owner AURORA FLIGHT SCI CORP