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公开(公告)号：US11167839B2
公开(公告)日：2021-11-09
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：US11148797B1
公开(公告)日：2021-10-19
申请号：US16833630
申请日：2020-03-29
Applicant: Textron Innovations Inc.
Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes an engine, a trinary 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 a plurality of ducted fans in a tandem lateral and forward orientation. 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 ducted fans 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 bypass air combines with engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.
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公开(公告)号：US11142310B2
公开(公告)日：2021-10-12
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：US20210300536A1
公开(公告)日：2021-09-30
申请号：US16833628
申请日：2020-03-29
Applicant: Textron Innovations Inc.
Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes first and second engines, a binary lift fan system, first and second forced air bypass systems and first and second exhaust systems. The engines have turboshaft and turbofan modes. The lift fan system includes ducted fans in a tandem longitudinal orientation. In the VTOL orientation of the aircraft, the engines are in the turboshaft mode coupled to the lift fan system such that the engines provide rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engines are in the turbofan mode coupled to the forced air bypass systems such that the bypass air combines with the engine exhaust in the exhaust systems to provide forward thrust generating the wing-borne lift.
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公开(公告)号：US20210300531A1
公开(公告)日：2021-09-30
申请号：US16833638
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 yaw control moments for an aircraft during hover flight. The system includes right and left yaw 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 yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.
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Patent Agency Ranking
公开(公告)号：US11084573B1
公开(公告)日：2021-08-10
申请号：US16833633
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 yaw control moments for an aircraft during forward flight. The system includes right and left yaw 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 yaw effectors that influence the path of airflow above and below the yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.
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公开(公告)号：US11072423B1
公开(公告)日：2021-07-27
申请号：US16833623
申请日：2020-03-29
Applicant: Textron Innovations Inc.
Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes an engine, a unitary 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 a 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 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：US10513334B2
公开(公告)日：2019-12-24
申请号：US15619765
申请日：2017-06-12
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 an X-tiltwing that is rotatable relative to the fuselage between a vertical lift orientation and a forward thrust orientation. The X-tiltwing has oppositely disposed V-wing members each having first and second wing sections. In the vertical lift orientation, the first and second wing sections of each V-wing member are generally in the same horizontal plane. In the forward thrust orientation, the first and second wing sections of each V-wing member are generally in the same vertical plane. A distributed propulsion system is attached to the X-tiltwing such that a plurality of propulsion assemblies is attached to each wing section. A flight control system is operably associated with the distributed propulsion system to independently control each of the propulsion assemblies.
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公开(公告)号：US12195177B2
公开(公告)日：2025-01-14
申请号：US17752542
申请日：2022-05-24
Applicant: Textron Innovations Inc.
Inventor： Kirk Landon Groninga , Daniel Bryan Robertson
IPC: B64C27/80 , B64C5/06 , B64C11/00 , B64C13/24 , B64C27/52 , B64C27/57 , B64C27/58 , B64C29/00 , B64U10/17 , B64U30/26 , B64U30/297 , B64U50/18 , F16H1/28
Abstract: A differential thrust vectoring system includes a first thruster, a second thruster, a main actuator, and a trim actuator. The system is configured such that actuation of the main actuator causes rotation of the thrusters together about an axis, whereas actuation of the trim actuator causes relative rotation of the first and second thrusters about the axis.
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公开(公告)号：US11597510B2
公开(公告)日：2023-03-07
申请号：US16833622
申请日：2020-03-29
Applicant: Textron Innovations Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga , Matthew Edward Louis
IPC: B64C29/00 , B64C11/00 , B64C21/04 , B64D27/16 , B64C11/48 , B64D35/06 , B64D35/02 , B64C27/22 , B64D33/04 , B64D35/04 , B64C3/10 , B64C19/00 , B64C27/26 , B64C27/30 , B64C9/20 , B64C21/08 , B64C27/78 , B64C39/10 , B64C9/18 , B64C15/02 , B64C15/14 , B64C21/00
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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