The invention relates to the technical field of spaceflight component structure design, in particular to a spaceflight interface component and a manufacturing method. The first boss is arranged on the skin; the plurality of second bosses are arranged on the skin; the reinforcing ribs are arranged on the skin, and the first boss and the second bosses are connected through the reinforcing ribs; the reinforcing ribs are connected in a crossed mode. First round corners are arranged at the joints of the reinforcing ribs and the skin, the joints of the first bosses and the skin and the joints of the second bosses and the skin; the skin, the first boss, the plurality of second bosses and the plurality of reinforcing ribs are all made of carbon fiber composite materials; the spaceflight interface component is manufactured through the cooperation of the first fillet structure design and the carbon fiber composite material, and the continuity of fibers of the spaceflight interface component is guaranteed; the machining time is shortened by 85%, and the material utilization rate reaches 90%; the specific stiffness and the specific strength are higher than those of a metal piece.
本发明涉及航天部件结构设计技术领域,具体涉及一种航天接口部件及制造方法,航天接口部件包括:蒙皮;第一凸台设置于所述蒙皮上;多个第二凸台设置于蒙皮上;多个加强筋设置于蒙皮上,第一凸台和多个第二凸台通过加强筋连接;多个加强筋相互交叉连接;在加强筋与蒙皮的连接处、第一凸台与蒙皮的连接处、以及第二凸台与蒙皮的连接处均设有第一圆角;蒙皮、第一凸台、多个第二凸台和多个加强筋均采用碳纤维复合材料制作;本申请通过第一圆角结构设计配合碳纤维复合材料制作航天接口部件,保证航天接口部件纤维的连续性;机加工时间缩短85%,材料利用率达到90%;比钢度和比强度均高于金属件。
Aerospace interface component and manufacturing method
一种航天接口部件及制造方法
2023-08-11
Patent
Electronic Resource
Chinese
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