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Flexible composite skin and manufacturing method and tool structure thereof

A manufacturing method and a flexible technology, applied in the aviation field, can solve problems such as comprehensive performance limitations, increase deformation driving force, and installation difficulty, and achieve modular disassembly, enhanced designability and adjustability, and high reliability. Effect

Active Publication Date: 2020-09-18
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing flexible skins usually only meet the above 1-2 conditions, and their comprehensive performance is greatly limited
In addition, the existing flexible skin structure needs to be pre-stretched to a certain extent to resist deformation and buckling, which increases the deformation driving force and installation difficulty to a certain extent

Method used

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  • Flexible composite skin and manufacturing method and tool structure thereof
  • Flexible composite skin and manufacturing method and tool structure thereof
  • Flexible composite skin and manufacturing method and tool structure thereof

Examples

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Embodiment Construction

[0036] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention.

[0037] see Figure 1-6 Describe this embodiment, a flexible composite skin, which includes a flexible rubber matrix 1, an embedded support structure 2 and a fiber reinforcement 3, and the embedded support structure 2 and fiber reinforcement 3 are shaped in parallel in the flexible rubber matrix 1 , the embedded support structure 2 and the fiber reinforcement 3 are vertically overlapped and arranged to form a uniform independent grid unit inside the flexible rubber matrix 1 . The total deformation area inside the skin structure can be reduced, and the aspect ratio of the unit can be reduced, which can improve the stability of the skin structure and prevent wrinkles during shear deformation.

[0038] The flexible rubber matrix 1 in this embodiment includes a matrix solution and a...

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Abstract

The invention provides a flexible composite skin and a manufacturing method and a tool structure thereof, and belongs to the technical field of aviation, thereby solving a problem that an existing flexible skin is poor in stability and bearing performance. The composite skin comprises a flexible rubber base body, an embedded supporting structure and a fiber reinforcement body. The embedded supporting structure and the fiber reinforcement body are shaped in the flexible rubber base body in parallel, the embedded supporting structure and the fiber reinforcement body are arranged in a mutually perpendicular and overlapped mode, and uniform and independent grid units are formed in the flexible rubber base body. The manufacturing tool structure comprises a metal bottom plate, fiber bundle moldplates, a supporting rod mold plate, a gland plate and a sliding block mold. The metal bottom plate is fixedly connected with a pair of fiber bundle mold plates, the supporting rod mold plate is fixedly installed on the upper surface of the metal bottom plate, the supporting rod mold plate is connected with the pair of fiber bundle mold plates to form a rectangular rail, and the sliding block moldslides along the rectangular rail. The flexible composite skin and the manufacturing method and the tool structure thereof are mainly used for variable sweepback wing quadrilateral shearing module units.

Description

technical field [0001] The invention belongs to the technical field of aviation, and in particular relates to a flexible composite skin, a manufacturing method thereof, and a tooling structure. Background technique [0002] Conventional fixed-wing aircraft are generally designed for the best aerodynamic efficiency in a single flight state, and cannot achieve the best aerodynamic efficiency in each state of the flight envelope. A typical flight mission is generally composed of several different operational links, and the aircraft often needs to complete a variety of combined tasks. It is difficult for conventional fixed-wing aircraft to meet the needs of the aircraft for the ability to perform multiple tasks. The morphing aircraft can expand its aerodynamic flight envelope by changing the aerodynamic shape and structural shape, significantly improve the application range and flight efficiency of the aircraft, and realize the ability of the aircraft to perform multiple tasks. ...

Claims

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Application Information

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IPC IPC(8): B64C1/12B64F5/10B29C70/30B29C70/54
CPCB64C1/12B64F5/10B29C70/30B29C70/54Y02T50/40Y02P70/50
Inventor 郭宏伟杨广蒋华毅肖洪刘荣强邓宗全
Owner HARBIN INST OF TECH
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