公开(公告)号：US20180178899A1

公开(公告)日：2018-06-28

申请号：US15391700

申请日：2016-12-27

Applicant: Korea Advanced Institute of Science and Technology

Inventor： Dongsoo HAR ,  Celso MORAES ,  Dongsuk KUM

IPC: B64C3/38 ,  B64C29/02 ,  B64C9/20 ,  B64C13/50 ,  B64C39/02 ,  B64D27/24

CPC classification number: B64D27/24 ,  B64C3/385 ,  B64C5/02 ,  B64C11/001 ,  B64C13/50 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/62

Abstract: An aircraft includes: a fuselage having opposing leading and trailing extremities along a vertical axis; a fixed wing airframe having opposed at least two main wings connected to the fuselage and extending on a horizontal axis; at least two electric coplanar main wing motors respectively attached to the main wings; a duct frame attach to the trailing extremity of the fuselage; at least two horizontal stabilizers connected to the duct frame and extending on the horizontal axis; an electric tail motor fitted an inner side of the duct frame; multiple battery packs installed inside the fuselage and suitable for supply power to the main wing motors and the tail motor; and support beams suitable for connecting the duct frame to the fuselage.

公开(公告)号：US20180178910A1

公开(公告)日：2018-06-28

申请号：US15852444

申请日：2017-12-22

Applicant: Korea Advanced Institute of Science and Technology

Inventor： Dongsoo HAR ,  Sang Min LEE

IPC: B64C29/00 ,  B64D27/24 ,  B64D41/00

CPC classification number: B64D27/24 ,  B64C3/385 ,  B64C5/02 ,  B64C11/001 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  B64D41/007 ,  F15B15/06 ,  F16H19/001 ,  F16H19/04 ,  F16H21/44 ,  Y02T50/62

Abstract: An aerial vehicle includes: a main body; two main wings arranged to the main body; two main wing tilting control units coupled to the main wings to control the main wings to tilt independently; two main propulsion units arranged to the main wings; tail wings arranged to a rear side of the main body; a rudder arranged to the tail wing; a rudder tilting control unit to control the rudder to tilt; a tail propulsion unit arranged to the rear side of the main body; a tail tilting control unit to control the tail propulsion unit to tilt; a power unit to provide power to the main and tail propulsion units; and a position control unit to control the main wing tilting control units, the main propulsion units, the rudder tilting control unit, the tail propulsion unit, the tail tilting control unit to adjust position of the aerial vehicle.