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公开(公告)号：US11180241B2
公开(公告)日：2021-11-23
申请号：US16833636
申请日：2020-03-29
Applicant: Textron Innovations Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga , Matthew Edward Louis
Abstract: An active flow control system for generating roll control moments for an aircraft during hover flight. The system includes right and left roll effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left roll effectors. Based upon which of the injectors is injecting pressurized air, the right and left roll effectors generate no roll control moment, generate a roll right control moment or generate a roll left control moment.
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公开(公告)号：US11174020B2
公开(公告)日：2021-11-16
申请号：US16833635
申请日：2020-03-29
Applicant: Textron Innovations Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga , Matthew Edward Louis
IPC: B64C21/08 , B64C19/00 , B64C29/00 , B64D27/16 , B64C11/48 , B64D35/06 , B64C11/00 , B64D35/02 , B64C27/22 , B64D33/04 , B64D35/04 , B64C3/10 , B64C27/26 , B64C27/30 , B64C9/20 , B64C27/78 , B64C21/04 , B64C39/10 , B64C9/18 , B64C15/02 , B64C15/14 , B64C21/00
Abstract: An active flow control system for generating roll control moments for an aircraft during forward flight. The system includes right and left roll effectors disposed on a trailing edge of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left roll effectors that influence the path of airflow across the wing. Based upon which of the injectors is injecting pressurized air, the right and left roll effectors generate no roll control moment, generate a roll right control moment or generate a roll left control moment.
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公开(公告)号：US20210300540A1
公开(公告)日：2021-09-30
申请号：US16833622
申请日：2020-03-29
Applicant: Textron Innovations Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga , Matthew Edward Louis
Abstract: A ducted fan assembly includes a duct having an inlet, an inner surface, an expanding diffuser and an outlet. A fan disposed within the duct between the inlet and the expanding diffuser is configured to rotate about a fan axis to generate airflow. An active flow control system includes a plurality of injection zones circumferentially distributed about the inner surface. The expanding diffuser has a diffuser angle configured to create flow separation when the airflow is uninfluenced by the active flow control system such that the airflow has a thrust vector with a first direction that is substantially parallel to the fan axis. Injection of pressurized air from one of the injection zones asymmetrically reduces the flow separation between the airflow and the expanding diffuser downstream of that injection zone such that the thrust vector of the airflow has a second direction that is not parallel to the first direction.
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公开(公告)号：US20210300539A1
公开(公告)日：2021-09-30
申请号：US16833618
申请日：2020-03-29
Applicant: Textron Innovations Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga , Matthew Edward Louis
Abstract: A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.
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Patent Agency Ranking
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
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.
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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.
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.
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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
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.
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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
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.
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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
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.
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