Truss type ultralight overall wing structure

A wing structure and truss-type technology, applied in the direction of wings, aircraft parts, chords/stringers, etc., can solve problems such as difficult to achieve weight index requirements, obvious overweight, etc., achieve obvious weight reduction benefits and reduce structural weight , the effect of higher than the stiffness

Active Publication Date: 2018-01-12
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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AI Technical Summary

Problems solved by technology

[0003] At present, the design and material selection scheme of the conventional wing structure basically adopts the structure of hard skin, metal or composite m

Method used

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  • Truss type ultralight overall wing structure
  • Truss type ultralight overall wing structure
  • Truss type ultralight overall wing structure

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Embodiment Construction

[0029] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention.

[0030] Aiming at the characteristics of low-speed small wing loads of near-space unmanned aerial vehicles, the present invention proposes a truss-type ultra-light integral wing structure design scheme, which adopts a new layout method of "film skin-sandwich skeleton", and the entire wing structure It mainly includes front beam 1, rear beam 2, wing rib 3, hard skin 4 and flexible skin 5, etc.

[0031] Such as figure 1 As shown, the spar is a span-wise component, which is divided into front spar 1 and rear spar 2. The front spar 1 is arranged in the area with high airfoil height, and the rear spar 2 is close to the trailing edge. The spar is the main load-bearing component of the wing. T...

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Abstract

The invention relates to a truss type ultralight overall wing structure, and belongs to the technical field of aircraft structure design. The truss type ultralight overall wing structure includes a front beam, a back beam, at least two wing ribs, a hard skin and a flexible skin, wherein the front beam and the back beam are in parallel and are arranged in the flight direction; each wing rib includes a front wing rib and a back wing rib, the front wing ribs are arranged between the front beam and the back beam, the back wing ribs are fixed to the front beam and provided with wing-shaped camberedsurfaces, and the wing ribs are in parallel. The hard skin is installed on the windward side between the front beam and the leading edge of a wing. The hard skin is provided with a wing-shaped cambered surface. The flexible skin is installed on the front beam, the back beam and the hard skin in a paved mode to maintain aerodynamic configuration. According to the truss type ultralight overall wingstructure, a novel layout mode of 'thin film skin-sandwich skeleton' is put forward in layout, and strict weight index requirements are met on the basis of meeting requirements of strength and rigidity.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure design, in particular to a truss type ultra-light integral wing structure. Background technique [0002] Unmanned aerial vehicles flying at near-space altitudes require long-lasting flight capabilities. Under the premise of ensuring effective mission loads, in order to meet flight performance, strict weight requirements are put forward for wing structure design. A foreign near-space The weight index proposed by the solar drone for the wing structure is: surface density ≤ 1kg / m2. [0003] At present, the design and material selection scheme of the conventional wing structure basically adopts the structure of hard skin, metal or composite material skeleton, and adopts the combination form of mechanical connection, which is obviously overweight and difficult to meet the weight index requirements. Contents of the invention [0004] The purpose of this invention is to solve the above-ment...

Claims

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Application Information

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IPC IPC(8): B64C3/18B64C3/26
Inventor 左林玄付建伟钟小丹包飞王进孙彦鹏
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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