公开(公告)号：US11708147B2

公开(公告)日：2023-07-25

申请号：US17557981

申请日：2021-12-21

Applicant: Textron Innovations Inc.

Inventor： Pascal Flynn-Robitaille

IPC: B64C9/08 ,  B64C13/38 ,  B64C29/02

CPC classification number: B64C9/08 ,  B64C13/38 ,  B64C29/02

Abstract: An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

公开(公告)号：US20210339849A1

公开(公告)日：2021-11-04

申请号：US16863235

申请日：2020-04-30

Applicant: Textron Innovations Inc.

Inventor： Kevin Morris ,  Nicholas Brodeur ,  Pascal Flynn-Robitaille

IPC: B64C25/62 ,  B64C29/02 ,  B64C39/06

Abstract: A damping landing gear assembly for a vertical takeoff and landing aircraft includes a spring housing forming a spring chamber, a spring disposed in the spring chamber and a plunger slidably coupled to the spring housing and movable between a compressed position and an extended position. The spring biases the plunger into the extended position during flight. The vertical takeoff and landing aircraft experiences a landing force during landing. The landing force compresses the plunger into the compressed position against the bias of the spring, thereby absorbing at least a portion of the landing force.

公开(公告)号：US11312491B2

公开(公告)日：2022-04-26

申请号：US17005704

申请日：2020-08-28

Applicant: Textron Innovations Inc.

Inventor： Kevin Morris ,  Nicholas Brodeur ,  Pascal Flynn-Robitaille ,  Mathieu Beland

IPC: B64C29/02 ,  B64D1/10 ,  B64C39/08 ,  B64C1/00 ,  B64C1/22 ,  B64C1/14 ,  B64D27/24 ,  B64C39/02 ,  B64D41/00 ,  G05D1/10 ,  E05F15/00

Abstract: An autonomous cargo delivery aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes a fuselage having an aerodynamic shape with a leading edge, a trailing edge and first and second sides. First and second wings are coupled to the fuselage proximate the first and second sides, respectively. A distributed thrust array includes a first pair of propulsion assemblies coupled to the first wing and a second pair of propulsion assemblies coupled to the second wing. A flight control system is operably associated with the distributed thrust array and configured to independently control each of the propulsion assemblies. The first side of the fuselage includes a door configured to provide access to a cargo bay disposed within the fuselage from an exterior of the aircraft with a predetermined clearance relative to the first pair of propulsion assemblies.

公开(公告)号：US20220111949A1

公开(公告)日：2022-04-14

申请号：US17557981

申请日：2021-12-21

Applicant: Textron Innovations Inc.

Inventor： Pascal Flynn-Robitaille

IPC: B64C9/08 ,  B64C13/38 ,  B64C29/02

Abstract: An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

公开(公告)号：US11254423B2

公开(公告)日：2022-02-22

申请号：US16863235

申请日：2020-04-30

Applicant: Textron Innovations Inc.

Inventor： Kevin Morris ,  Nicholas Brodeur ,  Pascal Flynn-Robitaille

IPC: B64C25/62 ,  B64C39/06 ,  B64C29/02

Abstract: A damping landing gear assembly for a vertical takeoff and landing aircraft includes a spring housing forming a spring chamber, a spring disposed in the spring chamber and a plunger slidably coupled to the spring housing and movable between a compressed position and an extended position. The spring biases the plunger into the extended position during flight. The vertical takeoff and landing aircraft experiences a landing force during landing. The landing force compresses the plunger into the compressed position against the bias of the spring, thereby absorbing at least a portion of the landing force.