A truss-type ultra-light integral 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: 2021-05-25
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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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 material skeleton, and adopts the combination form of mechanical connection. The overweight is obvious, and it is difficult to meet the weight index requirements.
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[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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The invention relates to a truss-type ultra-light integral wing structure, which belongs to the technical field of aircraft structure design, and comprises: a front beam and a rear beam, the front beam and the rear beam are arranged in parallel and along the flight direction; at least two wing ribs, the wing ribs It includes a front rib and a rear rib, the rear rib is placed between the front beam and the rear beam, the front rib and the front beam are fixed and have an airfoil arc surface, and the ribs are arranged in parallel; the hard cover The hard skin is arranged on the windward side between the front beam and the leading edge of the wing, and the hard skin has an airfoil arc surface; the flexible skin is laid on the front beam, the rear beam and the On rigid skins to maintain an aerodynamic shape. The truss-type ultra-light integral wing structure of the present invention proposes a new layout method of "film skin-sandwich skeleton" in terms of layout, which meets the strict weight index requirements on the basis of meeting the requirements of strength and stiffness.
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...
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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