公开(公告)号：US20210300529A1

公开(公告)日：2021-09-30

申请号：US16833624

申请日：2020-03-29

Applicant: Textron Innovations Inc.

Inventor： Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Matthew Edward Louis

IPC: B64C21/00 ,  B64C15/14

Abstract: An active flow control system for generating pitch control moments for an aircraft during flight. The system includes a nozzle disposed proximate the aft end of the aircraft. The nozzle is configured to discharge a gas stream in the aftward direction. A pressurized air system includes a pressurized air source and one or more injectors configured to selectively inject pressurized air into the nozzle to influence the path of the gas stream. Based upon which injectors are injecting pressurized air into the nozzle, the gas stream exits the nozzle generating no pitch control moment, generating a pitch down control moment or generating a pitch up control moment.

公开(公告)号：US11077951B1

公开(公告)日：2021-08-03

申请号：US16833621

申请日：2020-03-29

Applicant: Textron Innovations Inc.

Inventor： Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Steven Ray Ivans ,  Matthew Edward Louis

IPC: B64C29/00 ,  B64C27/22 ,  B64D27/16 ,  B64C11/00 ,  B64C11/48 ,  B64D35/04 ,  B64D33/04 ,  B64D35/02

Abstract: A propulsion system for an aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The propulsion system includes an turboshaft engine, a lift fan system, a forced air bypass system and an exhaust system. The engine has a turboshaft mode and a turbofan mode. The lift fan system includes at least one ducted fan. In the VTOL orientation of the aircraft, the engine is in the turboshaft mode coupled to the lift fan system such that the engine provides rotational energy to the at least one ducted fan generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engine is in the turbofan mode coupled to the forced air bypass system such that the bypass air combines with the engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

公开(公告)号：US20200307781A1

公开(公告)日：2020-10-01

申请号：US16789888

申请日：2020-02-13

Applicant: Textron Innovations Inc.

Inventor： Kirk Landon Groninga ,  Daniel Bryan Robertson

IPC: B64C29/00 ,  B64C39/00 ,  B64C39/08 ,  B64D27/24

Abstract: An aircraft having a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes a fuselage and a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage. The dual tiltwing assembly includes a forward wing and an aft wing coupled together and to the fuselage by a quadrilateral linkage. A distributed propulsion system is coupled to the dual tiltwing assembly and includes a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing. A flight control system is operably associated with the distributed propulsion system and the dual tiltwing assembly. The flight control system is operable to independently control each of the propulsion assemblies and is operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation.

公开(公告)号：US10752373B2

公开(公告)日：2020-08-25

申请号：US15815513

申请日：2017-11-16

Applicant: Textron Innovations Inc.

Inventor： Kirk Landon Groninga ,  Daniel Bryan Robertson

IPC: B64D33/08 ,  B64D27/24 ,  B64D35/08 ,  H02K9/16 ,  H02K5/20 ,  B64C29/00

Abstract: A stacked motor assembly for an aircraft includes a forward motor having an exhaust port and an aft motor disposed aft of the forward motor, the aft motor having an intake port. The stacked motor assembly includes an exhaust conduit originating from the exhaust port of the forward motor and disposed at least partially around the aft motor such that exhaust from the forward motor bypasses the aft motor. The stacked motor assembly also includes an intake conduit terminating at the intake port of the aft motor and disposed at least partially around the forward motor such that intake air for the aft motor bypasses the forward motor.

公开(公告)号：US10597152B2

公开(公告)日：2020-03-24

申请号：US15662257

申请日：2017-07-27

Applicant: Textron Innovations Inc.

Inventor： Kirk Landon Groninga ,  Daniel Bryan Robertson

IPC: B64C29/00 ,  B64C39/08 ,  B64C39/00 ,  B64D27/24 ,  B64D27/02

Abstract: An aircraft having a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes a fuselage and a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage. The dual tiltwing assembly includes a forward wing and an aft wing coupled together and to the fuselage by a quadrilateral linkage. A distributed propulsion system is coupled to the dual tiltwing assembly and includes a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing. A flight control system is operably associated with the distributed propulsion system and the dual tiltwing assembly. The flight control system is operable to independently control each of the propulsion assemblies and is operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation.