The invention provides a solar unmanned aerial vehicle wing section structure, and belongs to the technical field of unmanned aerial vehicles. Specifically, the wing section structure comprises a spar and wing ribs, the spar comprises a front beam and a rear beam which are sequentially distributed from the front side to the rear side of the unmanned aerial vehicle wing, the wing ribs comprise multiple rows of front ribs, multiple rows of middle ribs and multiple rows of rear ribs, the middle ribs are located between the front beam and the rear beam, the front ribs are located on the side, back to the rear beam, of the front beam, and the rear ribs are located on the side, back to the front beam, of the rear beam. A plurality of diagonal draw bars are arranged in the areas, close to the upper wing surface and the lower wing surface of the wing, between the front beam and the rear beam, the two ends of each diagonal draw bar are connected with the front beam and the rear beam respectively, the diagonal draw bars extend along the attached wing surfaces, and the diagonal draw bars and the wing ribs are arranged in a crossed mode. According to the treatment scheme, the strength of the wing is improved while the weight of the wing is reduced.
本申请提供了一种太阳能无人机翼段结构,属于无人机技术领域。具体的,翼段结构包括翼梁和翼肋,翼梁包括从无人机机翼的前侧至后侧依次分布的前梁和后梁,翼肋包括多排前肋、多排中肋和多排后肋,中肋位于前梁和后梁之间,前肋位于前梁背对后梁的一侧,后肋位于后梁背对前梁的一侧,在前梁和后梁之间贴近机翼的上翼面和下翼面的区域均设有若干个斜拉杆,斜拉杆的两端分别连接前梁和后梁,斜拉杆沿所贴近的翼面延伸,且斜拉杆和翼肋交叉设置。通过本申请的处理方案,减轻机翼重量的同时提高机翼的强度。
Solar unmanned aerial vehicle wing section structure
一种太阳能无人机翼段结构
2024-02-02
Patent
Electronic Resource
Chinese
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