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Composite-material vertical fin combination method of unmanned aerial vehicle

A vertical stabilizer and composite material technology, which is applied in the field of UAV composite vertical stabilizer combination, can solve the problems of poor assembly accuracy, large number of parts, complex mold modules, etc., to achieve simple mold, improve assembly accuracy, and reduce the number of Effect

Inactive Publication Date: 2015-05-20
HARBIN
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0002] Composite materials are widely used in aircraft structural design because of their high specific strength and specific modulus. The structure of the vertical stabilizer is mainly composed of beams, ribs, and skin. Due to the small opening space of the UAV vertical stabilizer skin , using the co-curing molding method, the mold module is complex and difficult to demould, while the conventional composite vertical stabilizer molding method is mainly to first solidify the beams, ribs, and skins separately, and finally riveted them into a whole by tooling positioning. This molding method The number of parts is large, and a large number of rivets are required to connect, and the assembly accuracy is poor

Method used

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  • Composite-material vertical fin combination method of unmanned aerial vehicle
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  • Composite-material vertical fin combination method of unmanned aerial vehicle

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Embodiment

[0018] A certain type of UAV vertical stabilizer such as image 3 As shown, lay out the front and rear beams on the mould, then lay 1# ribs, 2# ribs, 3# ribs, and 4# ribs on the silicone rubber core and fix them on the mold with tooling clamps. 3233 / CF3011 / 52 bidirectional carbon fiber prepreg cloth is added to the surface on the side where the rear inner surface is in contact with the front and rear beams as a continuous layer, and after vacuuming, it enters the autoclave and co-cures to form a vertical stabilizer skeleton, such as figure 2 As shown, the curing temperature is 125±5°C, and the temperature is kept for 1.5 to 2 hours. Then, the frame of the vertical stabilizer and the leading edge rib, the reinforcement frame of the cover, and the skin glue-riveting are formed, and the connection between the skin and the frame is strengthened with 3233 / CF3011 / 52 bidirectional carbon fiber prepreg cloth. Because of the wingtip cover, 1 The # and 2# covers need to be dismantled ...

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Abstract

The invention belongs to the technical field of aircraft structure design and relates to a composite-material vertical fin combination method of unmanned aerial vehicle. The vertical fin comprises a skin, a wingtip cover, a front rib, a first covering cap, a second covering cap, a covering cap reinforcing frame, a front beam, a rear beam, a first rib, a second rib, a third rib and a fourth rib. According to the invention, the beams and the ribs are jointly cured to form a vertical fin framework, and then the vertical fin framework, the skin and the like are subjected to gluing and riveting formation. According to the method disclosed by the invention, the mould is simple, the numbers of parts and connecting rivets are reduced, assembly accuracy is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure design, and relates to a composite vertical stabilizer combination method for an unmanned aerial vehicle. Background technique [0002] Composite materials are widely used in aircraft structural design because of their high specific strength and specific modulus. The structure of the vertical stabilizer is mainly composed of beams, ribs, and skin. Due to the small opening space of the UAV vertical stabilizer skin , using the co-curing molding method, the mold module is complex and difficult to demould, while the conventional composite vertical stabilizer molding method is mainly to first solidify the beams, ribs, and skins separately, and finally riveted them into a whole by tooling positioning. This molding method The number of parts is large, and a large number of rivets are required to connect, and the assembly accuracy is poor. Contents of the invention [0003] The purpose of th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C65/72
Inventor 王松曹景斌章强郝钢凝王乃文
Owner HARBIN
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