公开(公告)号：US20200017212A1

公开(公告)日：2020-01-16

申请号：US16031771

申请日：2018-07-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Dakota Charles Easley ,  Levi Charles Hefner

IPC: B64C39/02 ,  G05D1/08 ,  B64D31/06 ,  B64D27/26

Abstract: An unmanned aircraft system having a flying wing orientation includes an airframe having leading and trailing edges, a two-dimensional thrust array coupled to the leading edge, a power system and a flight control system operable to independently control the speed of each propulsion assembly of the two-dimensional thrust array. In the flying wing orientation, the two-dimensional distributed thrust array provides airspeed control responsive to collectively changing the speed of each propulsion assembly, pitch authority responsive to differentially changing the speed of the propulsion assemblies above the airframe relative to the propulsion assemblies below the airframe, roll authority responsive to differentially changing the speed of the propulsion assemblies rotating clockwise relative to the propulsion assemblies rotating counterclockwise and yaw authority responsive to differentially changing the speed of the propulsion assemblies on a port side of the airframe relative to the propulsion assemblies on a starboard side of the airframe.

公开(公告)号：US20200017213A1

公开(公告)日：2020-01-16

申请号：US16031786

申请日：2018-07-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi Charles Hefner ,  Dakota Charles Easley

IPC: B64C39/02 ,  B64D27/26

Abstract: An unmanned aircraft system includes a flying wing airframe having leading and trailing edges with respective sweep angles. A thrust array is coupled to the airframe and includes first and second motor mounts each selectively rotatably coupled to the leading edge by a locking joint. Each motor mount has first and second propulsion assemblies coupled to respective first and second distal ends thereof. A power system is operably associated with the thrust array and is operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and is operable to independently control the speed of each propulsion assembly. In a flight configuration, each motor mount is locked substantially perpendicular with the leading edge by the respective locking joint. In a compact storage configuration, each motor mount is locked substantially parallel with the leading edge the respective locking joint.

公开(公告)号：US20200017211A1

公开(公告)日：2020-01-16

申请号：US16031741

申请日：2018-07-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi Charles Hefner ,  Dakota Charles Easley

IPC: B64C39/02 ,  B64D27/26 ,  B64D31/06

Abstract: An unmanned aircraft system includes a flying wing airframe having leading and trailing edges with respective sweep angles. A thrust array is coupled to the airframe and includes first and second motor mounts each rotatably coupled to the leading edge. Each motor mount has first and second propulsion assemblies coupled to respective first and second distal ends thereof. A power system is operably associated with the thrust array and is operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and is operable to independently control the speed of each propulsion assembly. In a flight configuration of the system, each motor mount is substantially perpendicular with the leading edge such that the thrust array forms a two-dimensional thrust array. In a compact storage configuration of the system, each motor mount is substantially parallel with the leading edge.

公开(公告)号：US20190031316A1

公开(公告)日：2019-01-31

申请号：US16148005

申请日：2018-10-01

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi Charles Hefner ,  Dakota Charles Easley ,  Danielle Lynn Moore

IPC: B64C3/56 ,  B64C11/48 ,  B64C29/02 ,  B64C39/02 ,  B64C39/00

Abstract: A foldable wing system for an unmanned aerial system having a fuselage includes a left wing frame having an inboard gear rotatably coupled to the fuselage, a right wing frame having an inboard gear rotatably coupled to the fuselage and a wing actuator coupled to a linkage point on at least one of the wing frames. The wing frames are movable between a plurality of positions including a deployed position and a stowed position. The inboard gear of the left wing frame is engaged with the inboard gear of the right wing frame such that the wing frames move symmetrically between the plurality of positions in response to movement of the linkage point by the wing actuator.