The invention belongs to the field of airplane structural strength, and particularly relates to an airplane control surface structure, a box section structure and a skin. The box section structure comprises a front beam, a middle beam and a rear beam which are sequentially distributed along the course; the ribs are used for connecting the front beam, the middle beam and the rear beam and are distributed in the spanwise direction, and the integral reinforcing ribs are used for connecting the front beam, the middle beam and the rear beam; the integral reinforcing rib is of an integral structure and comprises a web plate, an upper flange and a lower flange which are located on the two side edges of the web plate, a front beam connecting piece, a suspension connector located at the front end of the front beam connecting piece, and control connector double lugs located on the upper flange, wherein the front beam connecting piece extends towards the two sides to form a] shape at the front end of the front beam connecting piece and is used for being connected with a front beam. The middle beam is connected to the middle of the integral reinforcing rib; according to the aircraft control surface structure, the overall strength of the aircraft control surface structure can be enhanced through the overall reinforcing rib, the integrity of the beam can be kept, the structural weight can be greatly reduced, the structural strength is high, and fastener connection is safe and reliable.
本申请属于飞机结构强度领域,特别涉及一种飞机舵面结构,盒段结构以及蒙皮;盒段结构包括:依次沿航向分布的前梁,中梁以及后梁;用于连接前梁,中梁以及后梁的多个展向分布的肋条以及整体加强肋,悬挂接头衬套、操纵接头衬套;其中,整体加强肋为一体结构,包括腹板、位于腹板两侧边的上翼缘与下翼缘,前端向两侧延伸有“]”形,用于连接前梁的前梁连接片,位于所述前梁连接片的前端的悬挂接头,位于所述上翼缘的操纵接头双耳;中梁通过连接在整体加强肋中部;后梁连接在整体加强肋的后端面上,本申请可以通过整体加强肋加强飞机舵面结构的整体强度,并且能够保持梁的整体性,能够大大减少结构重量,而且结构强度高,紧固件连接安全可靠。
Airplane control surface structure
一种飞机舵面结构
2024-04-12
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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