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CFRP fuselage frame fixed to vertical tail

A technology of fuselage frame and vertical tail, which is applied in the direction of fuselage, aircraft assembly, aircraft stability, etc., and can solve the problems of aluminum fuselage frame corrosion, fatigue, material differences, etc.

Pending Publication Date: 2022-02-22
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] There are concerns about corrosion in aluminum fuselage frames with aluminum frames attached to the aircraft's composite fiber reinforced polymer ("CFRP") skin
Furthermore, for example, in the case of construction of an aircraft from an aluminum frame with a CFRP skin, fatigue problems arise due to material differences and their different thermal expansion effects

Method used

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  • CFRP fuselage frame fixed to vertical tail
  • CFRP fuselage frame fixed to vertical tail
  • CFRP fuselage frame fixed to vertical tail

Examples

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Embodiment Construction

[0017] refer to figure 1 , the aircraft 10 includes a fuselage assembly 12 , a wing assembly 14 and a vertical tail assembly 16 . When aircraft 10 is manufactured, vertical tail assembly 16 includes a spar and rib support structure (not shown) secured to skin 18 of aircraft 10 . Vertical tail assembly 16 is further secured to fuselage assembly 12 of aircraft 10 when attached to the fuselage frame. As previously discussed, in constructing aircraft 10, manufacturers have utilized metals such as aluminum to construct the fuselage frame. Metal fuselage frame with such as from Figure 2 to Figure 4 The fuselage frames of the first fuselage frame 20a, the second fuselage frame 20b, the third fuselage frame 20c, and the fourth fuselage frame 20d seen in FIG. The number of fuselage frames to which vertical tail assembly 16 is secured can vary depending on the design of a particular aircraft 10 .

[0018] As previously discussed with respect to metal fuselage frames, in the present...

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Abstract

The invention relates to a CFRP fuselage frame fixed to a vertical tail. A securing assembly for securing a vertical tail assembly to an aircraft includes a first lug member secured to the vertical tail assembly. The fixation assembly further includes a first U-joint member. The first U-joint member includes a first end of the first U-joint member joined to the first lug member. The second end of the first U-joint member is secured to a first fuselage frame made of composite material with a first fastener extending through the second end and the first fuselage frame in a first direction transverse to the first fuselage frame.

Description

technical field [0001] The present disclosure relates to securing vertical wing assemblies of aerospace vehicles to aerospace vehicles, and more particularly, to securing vertical wing assemblies to fuselage frames of aircraft. Background technique [0002] There are problems with corrosion of aluminum fuselage frames with aluminum frames attached to composite fiber reinforced polymer ("CFRP") skins of the aircraft. Furthermore, fatigue problems arise due to material differences and their different thermal expansion effects, for example in the case of construction of aircraft from aluminum frames with CFRP skins. For example, aluminum has a larger coefficient of thermal expansion than that of CFRP. Aluminum undergoes contraction in the cold state and expansion in the hot state relative to the CFRP material (which is thermally neutral by comparison). Due to the different materials used for the frame and skin structures, these structures experience compression and tension as...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C5/06
CPCB64C5/06B64C1/26B64C1/061B64C2001/0072Y02T50/40B64F5/10
Inventor 保罗·迪普·博塞尔菲延·T·帕姆
Owner THE BOEING CO