公开(公告)号：US11787539B2

公开(公告)日：2023-10-17

申请号：US17220137

申请日：2021-04-01

申请人： Xingkang Li ,  Heng Ren ,  Qiang Li ,  Xingjian Li

发明人： Xingkang Li ,  Heng Ren ,  Qiang Li ,  Xingjian Li

IPC分类号： B64C37/00 ,  B64D27/10 ,  B64C1/06 ,  B64C27/68 ,  B64C9/00 ,  B64C5/00 ,  B64D31/00

CPC分类号： B64C37/00 ,  B64C1/065 ,  B64C5/00 ,  B64C9/00 ,  B64C27/68 ,  B64D27/10 ,  B64D31/00 ,  B64C2009/005

摘要： A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention.

公开(公告)号：US20220315215A1

公开(公告)日：2022-10-06

申请号：US17220137

申请日：2021-04-01

申请人： Xingkang Li ,  Heng Ren ,  Qiang Li ,  Xingjian Li

发明人： Xingkang Li ,  Heng Ren ,  Qiang Li ,  Xingjian Li

IPC分类号： B64C37/00 ,  B64C1/06 ,  B64C27/68 ,  B64D31/00 ,  B64C9/00 ,  B64D27/10 ,  B64C5/00

摘要： A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention.