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公开(公告)号：US11077939B1
公开(公告)日：2021-08-03
申请号：US16833619
申请日：2020-03-29
Applicant: Textron Innovations Inc.
IPC: B64C29/00 , B64C27/22 , B64D33/04 , B64C19/00 , B64C3/10 , B64C27/30 , B64C27/26 , B64C15/14 , B64C21/00
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 binary 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 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 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：US10967968B2
公开(公告)日：2021-04-06
申请号：US16188553
申请日：2018-11-13
Applicant: Textron Innovations Inc.
Abstract: A method for an aircraft may include determining a transition from an airplane mode to a helicopter mode for a propulsion system of the aircraft, wherein the propulsion system comprises a plurality of rotor blades; determining whether a descent rate condition is satisfied, wherein the descent rate condition is associated with a maximum allowable descent rate for the aircraft; and controlling a collective pitch angle for the plurality of rotor blades based on the descent rate condition.
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公开(公告)号：US20200148346A1
公开(公告)日：2020-05-14
申请号：US16188553
申请日：2018-11-13
Applicant: Textron Innovations Inc.
Abstract: A method for an aircraft is provided in one example embodiment and may include determining a transition from an airplane mode to a helicopter mode for a propulsion system of the aircraft, wherein the propulsion system comprises a plurality of rotor blades; determining whether a descent rate condition is satisfied, wherein the descent rate condition is associated with a maximum allowable descent rate for the aircraft; and controlling a collective pitch angle for the plurality of rotor blades based on the descent rate condition.
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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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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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Patent Agency Ranking
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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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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