The invention belongs to the technical field of overall layout design of helicopter structures, and mainly relates to a fuselage structure design of an unmanned helicopter. The assembly comprises a main reducing platform body (1), an engine supporting frame (2), longitudinal beams (3), a middle inclined frame (4) and a front supporting frame (5). The main reducing platform (1) is located at the top of the structure assembly. The engine supporting frame (2) is located on the rear portion of the structural assembly, and the upper end of the engine supporting frame (2) is connected with the mainreducing platform (1). The longitudinal beams (3) comprise a left longitudinal beam (31) and a right longitudinal beam (32) which are arranged in a bilateral symmetry mode, and the upper end of the left longitudinal beam (31) and the upper end of the right longitudinal beam (32) are connected with the left side and the right side of the main reduction platform (1) respectively; the middle inclinedframe (4) is located in the structural assembly, the upper end of the middle inclined frame (4) is connected with the front portion of the main reduction platform (1), and the left side and the rightside of the middle inclined frame (4) are connected with the left longitudinal beam (31) and the right longitudinal beam (32) respectively. The front supporting frame (5) is located on the front portion of the structural assembly, and the left side and the right side of the front supporting frame (5) are connected with the front portion of the left longitudinal beam (31) and the front portion ofthe right longitudinal beam (32) respectively. According to the fuselage structure, a modular design mode is adopted, a large number of integrally-formed components such as frames and beams are used,a brand-new force transmission route is planned, connection of the structure is in smooth transition, continuity is good, force transmission is direct, and sudden change loads do not exist.

    本发明属于直升机结构总体布局设计技术领域,主要涉及一种无人直升机的机身结构设计。包括主减平台(1)、发动机支撑框(2)、纵梁(3)、中部斜框(4)、前部支撑框(5);所述主减平台(1)位于结构组件顶部;所述发动机支撑框(2)位于结构组件后部,其上端与所述主减平台(1)连接;所述纵梁(3)包括左右对称设置的左侧纵梁(31)和右侧纵梁(32),所述左侧纵梁(31)和右侧纵梁(32)上端分别与所述主减平台(1)左右两侧连接;所述中部斜框(4)位于结构组件内部,其上端与所述主减平台(1)前部连接,左右两侧分别与所述左侧纵梁(31)和右侧纵梁(32)连接;所述前部支撑框(5)位于结构组件前部,其左右两侧分别与所述左侧纵梁(31)和右侧纵梁(32)前部连接。该机身结构采用模块化设计方式,大量使用框、梁等一体化成型构件,规划了全新的传力路线,结构的连接平缓过渡,连续性好,传力直接,无突变载荷。


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    Title :

    Unmanned helicopter fuselage force transmission structure assembly


    Additional title:

    一种无人直升机机身传力结构组件


    Contributors:
    SHENG CHAO (author) / LU FUQUAN (author) / LIU SIMIN (author)

    Publication date :

    2021-02-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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