The invention relates to a large-size heat-proof bearing integrated aircraft wing, and belongs to the technical field of aircraft structures, the large-size heat-proof bearing integrated aircraft wing comprises an aircraft body shell, a first mounting groove and a second mounting groove are formed in the two sides of the aircraft body shell, a first groove is formed in the end, facing a middle wing, of a front wing, and a second groove is formed in the end, facing the middle wing, of the front wing; a first supporting lug inserted into the first groove in a matched mode is arranged on the middle wing, a second groove is formed in the end, facing the rear wing, of the middle wing, a second supporting lug inserted into the second groove in a matched mode is arranged on the rear wing, and the front wing, the middle wing and the rear wing are connected with the first installation groove and the second installation groove through a front support and a rear support. The heat-proof putty is arranged in the butt joint of the front wing, the middle wing and the rear wing; the rear support can be movably mounted, so that a connecting structure between the rear support and the aircraft body shell can be matched in a thermal deformation manner, and the situation that the wings cannot be synchronously stretched when subjected to thermal deformation in a completely fixed mounting manner, and consequently the wings are prone to being damaged is avoided.
本申请涉及一种大尺寸防热承载一体飞行器机翼,属于飞行器结构技术领域,大尺寸防热承载一体飞行器机翼,包括机体壳体,机体壳体的两侧均开设有第一安装槽和第二安装槽,前翼朝向中翼的一端开设有第一凹槽,中翼上设置有与第一凹槽配合插入的第一支耳,中翼朝向后翼的一端开设有第二凹槽,后翼上设置有与第二凹槽配合插入的第二支耳,前翼、中翼和后翼通过前支座和后支座与第一安装槽和第二安装槽之间连接,防热腻子设置在前翼、中翼和后翼之间的对接处中;本申请可以通过后支座的活动安装,使其与机体壳体之间的连接结构可以热变形匹配,避免了完全固定的安装方式,在机翼产生热变形的时候,无法同步伸展,导致机翼容易受损。
Wing of large-size heat-proof bearing integrated aircraft
一种大尺寸防热承载一体飞行器机翼
2023-06-23
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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