An aircraft structure (10) comprising: a fuselage (24); first and second front wings (20, 22) mounted to and/or extending from opposite sides of the fuselage (24); a continuous rear span (34) defining first and second rear wings (30, 32) and a central stationary connecting portion (36); a first wing connection member (42) extending between the first front wing (20) and the first rear wing (30); a second wing connection member (42) extending between the second front wing (22) and the second rear wing (32); wherein the aft span (34) is supported by a centrally positioned V-tail joint, the V-tail joint being defined by a first and a second angled angled arm (100, 110); a first electric motor and a second electric motor, each having a rotor, are mounted to each wing (20, 22, 30, 32), each rotor pivoting between a first configuration for vertical flight and a second configuration for forward flight.
一种飞行器结构(10),包括:机身(24);第一前机翼和第二前机翼(20、22),安装到所述机身(24)的相对侧和/或从所述机身的相对侧延伸;连续的后翼展(34),限定第一后机翼和第二后机翼(30、32)以及中心静止连接部分(36);第一机翼连接构件(42),在第一前机翼(20)与第一后机翼(30)之间延伸;第二机翼连接构件(42),在第二前机翼(22)与第二后机翼(32)之间延伸;其中,后翼展(34)由居中定位的V型尾部接合部支撑,所述V型尾部接合部由第一成角度倾斜的臂和第二成角度倾斜的臂(100、110)限定;各自具有旋翼的第一电动马达和第二电动马达被安装到每个机翼(20、22、30、32),每个旋翼在用于竖直飞行的第一配置与用于向前飞行的第二配置之间枢转。
Aircraft structure
飞行器结构
2023-05-30
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
AIRCRAFT FRONT EDGE STRUCTURE, AIRCRAFT BLADE AND AIRCRAFT
Europäisches Patentamt | 2017
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