Composite material wing spar with high-precision curved surface and large length-diameter ratio and preparation method thereof

A composite material, large aspect ratio technology, applied in aircraft assembly, fuselage, weight reduction, etc., can solve the problem that the molding process cannot be applied to the wing spar, avoid secondary bonding and curing, reduce production costs, and improve connection. The effect of reliability

Active Publication Date: 2021-03-23
SHANGHAI COMPOSITES SCI & TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, it needs to be pointed out that in the technical solution disclosed in this patent document, its molding process cannot be applied to spars with high precision and large aspect ratio.
In addition, in the technical solution disclosed in this patent document, when making the beam mold assembly and the beam blank, it actually uses a pre-curing step, followed by post-assembly molding and curing. Therefore, in practice, the technical solution is not completely One curing, which actually has two curing cycles

Method used

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  • Composite material wing spar with high-precision curved surface and large length-diameter ratio and preparation method thereof
  • Composite material wing spar with high-precision curved surface and large length-diameter ratio and preparation method thereof
  • Composite material wing spar with high-precision curved surface and large length-diameter ratio and preparation method thereof

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Embodiment 1

[0048] In this embodiment, the specific structure of the composite spar with high-precision curved surface and large aspect ratio can be referred to figure 1 to Figure 4 .

[0049] Such as figure 1 shown, and refer to the Figure 4 , in this embodiment, the composite material spar is an integral molding, wherein the composite material spar includes an integral beam box 1 and reinforcing ribs 2, the outer side of the lower end surface of the integral beam box 1 has a high-precision curved surface I, and the integral beam box 1 There is a guide groove 11 near the lower end surface of the box body side.

[0050] further combined figure 1 It can be seen that the overall beam box 1 is slender; the guide groove 11 is linear, the cross section of the guide groove 11 is "C" shaped, and the cross section of the structure formed by the guide groove 11 and the high-precision curved surface I is type.

[0051] Also, further reference figure 1 It can be seen that the reinforcing ...

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Abstract

The invention discloses a composite material wing spar with a high-precision curved surface and a large length-diameter ratio; the composite material wing spar is an integrally formed part and comprises an integral beam box and reinforcing ribs, the lower end face of a box body of the integral beam box is provided with the high-precision curved surface, and the lower end face of the box body of the integral beam box is provided with a guide groove. In addition, the invention further discloses a preparation method of the composite material wing spar with the high-precision curved surface and the large length-diameter ratio. Aiming at the high-precision and large-length-diameter-ratio composite material wing spar, the invention adopts an integral laying and co-curing forming method, that isto say, the whole wing spar is formed at one time and is a part, so that the subsequent gluing and curing of reinforcing ribs are avoided, the connection reliability of the product is improved, and the curved surface precision control, deformation control and light weight of the large wing spar are realized.

Description

technical field [0001] The invention relates to the technical field of composite material load-bearing parts and their forming, in particular to a high-precision curved surface and large length-to-diameter ratio composite wing spar and its integrated forming method. Background technique [0002] Various main load-bearing spar structures are used in the wing spar and hatch docking mechanisms of large aerospace and aerospace vehicles. For the main load-bearing spar structures on aerospace vehicles, in addition to high strength and excellent mechanical properties In addition, it also needs to have excellent aerodynamic shape surface and docking datum. At present, this type of main load-bearing spar generally adopts a box-shaped stiffener structure to meet the main requirements of the whole machine structure. [0003] By searching the patent literature and non-patent literature, the patent literature related to the spar is for example: the publication number is CN101055344A, th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/06B64F5/10B29C70/34B29C70/54
CPCB64C1/06B64F5/10B29C70/342B29C70/54B64C2001/0072Y02T50/40
Inventor 毕华阳吴鑫锐潘韵周科旭谢钟清张志斌常舰张砚达陈志成徐云研刘图远赵丁丁
Owner SHANGHAI COMPOSITES SCI & TECH CO LTD
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