The invention belongs to the technical field of aircraft design, and particularly relates to a wing leading edge for relieving thermal stress, the wing leading edge comprises a plurality of leading edge ribs (1) which are arranged side by side along the spanwise direction of a wing, each leading edge rib extends from the inside of the wing to a leading edge wingtip along the chordwise direction, the leading edge ribs (1) extend in a corrugated structure form, and the leading edge ribs (1) are connected with the leading edge ribs (1). The upper portion and the lower portion of each front edge rib (1) are respectively provided with a skin (2) in a supporting mode, the two sides of each skin (2) form seam allowances through steps, the adjacent skins (2) located above or below the front edge ribs (1) are in lap joint through the seam allowances, and gaps (3) are reserved at the seam allowances. The thermal stress in the spanwise direction and the downstream direction of the aircraft can be effectively released, the thermal stress of the leading edge of the wing can be greatly reduced, and the structural weight of the aircraft can be reduced while the thermal strength design requirement of the aircraft is met.
本申请属于飞机设计技术领域,特别涉及一种用于减缓热应力的机翼前缘,机翼前缘包括沿机翼展向并排设置的多个前缘肋(1),各前缘肋沿弦向自机翼内部向前缘翼尖处延伸,其中,所述前缘肋(1)以波纹结构形式延伸,每个前缘肋(1)上下各支撑有一块蒙皮(2),各所述蒙皮(2)的两侧通过台阶形成止口,位于前缘肋(1)上方或下方的各相邻蒙皮(2)之间通过止口搭接,且在各止口处预留有间隙(3)。本申请能够有效释放飞机展向及顺气流方向的热应力,可使机翼前缘热应力大幅度降低,满足飞机热强度设计需求的同时能够降低飞机结构重量。
Wing leading edge for relieving thermal stress
一种用于减缓热应力的机翼前缘
2024-09-03
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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