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Film covering device and method of wing structure surface

A technology of wing structure and film, applied in the field of large-scale lightweight aircraft structure manufacturing, can solve the problems of poor environmental resistance and low mechanical properties of heat-shrinkable film, and achieve the effect of easy operation

Active Publication Date: 2013-04-17
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Heat-shrinkable films have low mechanical properties and poor environmental resistance, so they are not suitable as wing skins

Method used

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  • Film covering device and method of wing structure surface
  • Film covering device and method of wing structure surface
  • Film covering device and method of wing structure surface

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Embodiment

[0023] a kind of like figure 1 , figure 2 , image 3 The covering device of the wing structure surface film of the present invention is shown, the covering device includes a film tensioning mechanism 1 and a wing supporting device for pressing the wing structure frame 6 against the tensioned polyester film 7 . The wing supporting device of this embodiment is a lifting platform 2, and the top of the lifting platform 2 is provided with a support surface capable of fixing the wing structure frame 6. There is a certain distance between the supporting surface of the lifting platform 2 and the film fixing surface of the film tensioning mechanism 1, and the supporting surface and the film fixing surface can be continuously approached by the relative displacement and realize the tension of the wing structure frame 6 to the tensioned polyester film 7. lean on.

[0024] The film tensioning mechanism 1 of this embodiment includes movable spanwise end plates 3 located on both sides. T...

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Abstract

The invention discloses a film covering device and a method of a wing structure surface. A film covering device comprises a film tension mechanism and a wing supporting device which is used for abutting a wing structure frame to a tensioned polyester film, distance is formed between a supporting face of the wing supporting device and a film fixing face of the film tension mechanism, and the supporting face and the film fixing face are constantly close to each other by opposite movement to achieve attachment of the wing structure frame to the tensioned polyester film. The film covering method comprises the following steps of assembling the covering device; fixedly arranging the polyester film on the film fixing face in a pasting mode; exerting pre-tension force on the film by adjusting span-dominated endplates in a separation mode; coating adhesives on the film portions to be pasted with the wing structure film, lifting a lifting platform until the wing structure frame is closely joint to the film and obtaining the wing structure covering with film on the surface after cutting edges and finishing. The film covering device and the method of the wing structure surface have the advantages of simple structure, convenience utilization, simple production, good film covering effect and the like.

Description

technical field [0001] The invention belongs to the technical field of large-scale lightweight aircraft structure manufacturing, and in particular relates to a treatment device and method for the surface of a wing structure with a large wingspan structure feature and high requirements for structural weight reduction. Background technique [0002] In order to maximize the energy utilization rate of modern solar-powered aircraft, realize long-time climb and flight across day and night, structural weight reduction is the key. Usually the wing surface of this type of aircraft is covered with polyester film as the wing skin to save structural weight to the greatest extent. The solar-powered high-altitude and long-endurance aircraft developed in the United States, the United Kingdom and other countries all use this wing structure. Heat-shrinkable films have low mechanical properties and poor environmental resistance, so they are not suitable as wing skins. The mechanical properti...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00B64F5/10
Inventor 鞠苏江大志曾竟成肖加余杜刚石刚黄春芳
Owner NAT UNIV OF DEFENSE TECH
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