Stressed-skin construction capable of implementing large area deformation

A large-area skinning technology, applied in the field of aircraft skinning, can solve problems such as limited deformability, increased resistance to skeleton deformation, and difficulty in co-deformation

Inactive Publication Date: 2009-02-18
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the collaborative deformation of the skin becomes very difficult, because if it changes from one shape to another, the skin is still fixed according to the original constraint method. Although the skin itself has a certain degree of flexibility, it can be deformed. The extent is very limited. Under such condition

Method used

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  • Stressed-skin construction capable of implementing large area deformation
  • Stressed-skin construction capable of implementing large area deformation
  • Stressed-skin construction capable of implementing large area deformation

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Embodiment Construction

[0018] Below in conjunction with accompanying drawing and specific embodiment the present invention will be further described:

[0019] to combine figure 2 , the present embodiment is composed of skin overlapping structures 2 grid-like weaving, each skin overlapping structure 2 is close to no gap, and the side of the skin overlapping structure 2 is provided with a skin retractable structure 1. The skin overlapping structure is composed of a single skin overlapping, which is a multi-layer slideway structure and makes the multi-layer flexible skin completely overlap into one layer; the skin retractable structure is that the skin can be rolled in and out of the retractable structure, including rollers and the skin storage compartment, the skin overlapping structure connects the rollers.

[0020] In this embodiment, in order to realize large-area deformation, a braided structure is used to realize it. When the wing area needs to change greatly, this change is often in two direc...

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Abstract

The invention provides a skin structure which can realize large-area deformation. The skin structure is formed by grid-knitted skin overlapped structures. Skin overlapped structures clings to each other tightly without any clearance; the side of the skin overlapped structure is provided with a skin take up-pay off structure. The skin structure uses a knitting structure to realize the extensive deformation. In the skin take up-pay off structure, a roller and a skin storage room are used to make the flexible skin roll into or out of the skin take up-pay off structure; in the skin overlapped structure, a multi-slideway structure is adopted to make more layers of flexible skin overlapped into one layer entirely; a skin unit is flexible membrane material and the overlapped skins are in same size; when geometry shape complicated changes happen on the surface of the skin, the skin can be stretched or compressed at large scale without folds or damage simultaneously.

Description

(1) Technical field [0001] The invention relates to aircraft skin technology, in particular to a skin structure capable of large-area deformation. (2) Background technology [0002] At present, the winged aircraft currently in service in various countries in the world basically have immutable wing structures. Only a few models such as the F-111 and F-14 of the United States and the MiG-23 of Russia have variable sweep angles. of. Aircraft with variable wing area that is truly independent of sweep angle do not yet exist. The limited change of the wing area of ​​the above-mentioned several types of aircraft is realized by making a part of the wing surface retract or move out of the fixed part of the wing or the fuselage after the change of the sweep angle. [0003] To realize the deformation of the wing plane, the following two key processes must be the basis: 1. Skeleton deformation; 2. Skin coordination. The internal skeleton structure of the wing is not only the main loa...

Claims

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Application Information

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IPC IPC(8): B64C3/26
Inventor 张博明于东梁军戴福洪赵海涛解维华
Owner HARBIN INST OF TECH
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