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公开(公告)号：US20240246665A1
公开(公告)日：2024-07-25
申请号：US18624806
申请日：2024-04-02
Applicant: Textron Innovations Inc.
Inventor： Jonathan Andrew Knoll , George Matthew Thompson , Charles Hubert Speller , Grant Michael Beall
CPC classification number: B64C27/28 , B64C29/0033
Abstract: A rotor system for an aircraft includes a rotor assembly comprising a plurality of rotor blades connected to a rotor mast, wherein the rotor assembly is tiltable relative to a wing of the aircraft between a first position corresponding to an airplane mode of the aircraft and a second position corresponding to a helicopter mode of the aircraft; and a drive system for providing rotational energy to the rotor assembly via the rotor mast. The drive system includes at least one electric motor for generating rotational energy to a motor shaft; and a gearbox connected to receive rotational energy from the at least one electric motor via the motor shaft and to provide rotational energy to the rotor mast via a rotor shaft, wherein the at least one electric motor is fixed relative to the wing of the aircraft.
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公开(公告)号：US20240025542A1
公开(公告)日：2024-01-25
申请号：US18480338
申请日：2023-10-03
Applicant: Textron Innovations Inc.
Inventor： Jonathan Andrew Knoll , George Matthew Thompson , Charles Hubert Speller , Grant Michael Beall
CPC classification number: B64C29/0033 , B64D27/24 , B64D29/02 , B64D35/02 , B64D35/04 , H02K7/108 , H02K7/116 , F16D41/00
Abstract: A rotor system for an aircraft includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast via a yoke, wherein the rotor assembly is tiltable between a first position corresponding to an airplane mode and a second position corresponding to a helicopter mode; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast, the drive system comprising at least one electric motor for providing rotational energy to a drive shaft and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the drive shaft and providing rotational energy to the rotor mast via a rotor shaft; wherein the drive system is rotatable relative to the wing about a tilt axis and the rotor shaft is coaxial with the drive shaft.
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公开(公告)号：US20210394895A1
公开(公告)日：2021-12-23
申请号：US16907087
申请日：2020-06-19
Applicant: Textron Innovations Inc.
Abstract: A proprotor system for a ducted aircraft includes a duct and proprotor blades surrounded by the duct. Each proprotor blade is rotatable about a respective pitch change axis. The proprotor blades are configured to change collective pitch about the pitch change axes. The proprotor blades are extendable along the pitch change axes into various positions including a retracted position and an extended position. The proprotor blades change between the retracted position and the extended position based on the collective pitch of the proprotor blades, thereby controlling a tip gap between the proprotor blades and the duct.
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公开(公告)号：US11479350B2
公开(公告)日：2022-10-25
申请号：US16907067
申请日：2020-06-19
Applicant: Textron Innovations Inc.
Abstract: A tip gap monitoring system for a ducted aircraft having a proprotor system including a duct and a plurality of proprotor blades includes sensors coupled to the proprotor system. The sensors are configured to detect one or more parameters of the proprotor system to form a plurality of sensor measurements. The tip gap monitoring system also includes a flight control computer in data communication with the sensors. The flight control computer includes a tip gap measurement module configured to determine a tip gap distance between the duct and the proprotor blades based on the sensor measurements.
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公开(公告)号：US11454280B2
公开(公告)日：2022-09-27
申请号：US16916353
申请日：2020-06-30
Applicant: Textron Innovations Inc.
Inventor： George Matthew Thompson , Joseph Richard Carpenter, Jr. , Paul Sherrill , Jonathan Andrew Knoll
Abstract: A bearing system includes an inboard bearing assembly and an outboard bearing assembly. The inboard bearing assembly includes an inboard fitting and an inboard race. The inboard fitting includes a plate with a convex mating surface and a first aperture formed through the plate for receiving a blade root of a rotor blade. The inboard race comprising a concave mating surface configured to receive the convex mating surface a second aperture formed the inboard race. The outboard bearing assembly includes an outboard bearing assembly comprising an outboard fitting having an aperture formed therethrough for receiving the blade root of the rotor blade.
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Patent Agency Ranking
公开(公告)号：US11407504B2
公开(公告)日：2022-08-09
申请号：US16907079
申请日：2020-06-19
Applicant: Textron Innovations Inc.
Abstract: A tip gap control system for a ducted aircraft includes a flight control computer including an inner duct surface control module configured to generate an inner duct surface actuator command and a proprotor system in data communication with the flight control computer. The proprotor system includes a duct having active inner duct surfaces movable into various positions including a retracted position and an extended position. The proprotor system also includes proprotor blades surrounded by the duct and one or more actuators coupled to the active inner duct surfaces. The one or more actuators move the active inner duct surfaces between the various positions based on the inner duct surface actuator command, thereby controlling a tip gap between the proprotor blades and the duct.
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公开(公告)号：US11203421B1
公开(公告)日：2021-12-21
申请号：US16907087
申请日：2020-06-19
Applicant: Textron Innovations Inc.
Abstract: A proprotor system for a ducted aircraft includes a duct and proprotor blades surrounded by the duct. Each proprotor blade is rotatable about a respective pitch change axis. The proprotor blades are configured to change collective pitch about the pitch change axes. The proprotor blades are extendable along the pitch change axes into various positions including a retracted position and an extended position. The proprotor blades change between the retracted position and the extended position based on the collective pitch of the proprotor blades, thereby controlling a tip gap between the proprotor blades and the duct.
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公开(公告)号：US11634233B2
公开(公告)日：2023-04-25
申请号：US16908471
申请日：2020-06-22
Applicant: Textron Innovations Inc.
Inventor： Nicholas Ralph Carlson , Frank Brad Stamps , George Matthew Thompson , Jonathan Andrew Knoll
Abstract: In an embodiment, a duct for a ducted-rotor aircraft includes a hub, the hub including a rotor and one or more motors configured to drive the rotor. The duct also includes a duct ring that defines an opening surrounding at least a portion of the hub. The duct also includes a plurality of stators that extend outward from the hub. The duct also includes at least one battery electrically coupled to the rotor and configured to power the one or more motors.
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公开(公告)号：US11530035B2
公开(公告)日：2022-12-20
申请号：US17005194
申请日：2020-08-27
Applicant: Textron Innovations Inc.
Inventor： Jonathan Andrew Knoll , George Matthew Thompson , Matthew Edward Louis
Abstract: An aircraft having multiple wing planforms. The aircraft includes an airframe having first and second half-wings with first and second pylons extending therebetween. A distributed thrust array is attached to the airframe. The thrust array includes a plurality of propulsion assemblies coupled to the first half-wing and a plurality of propulsion assemblies coupled to the second half-wing. A flight control system is coupled to the airframe. The fight control system is configured to independently control each of the propulsion assemblies and control conversions between the wing planforms. The aircraft is configured to convert between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. In addition, the aircraft is configured to convert between a biplane configuration and a monoplane configuration in the forward flight orientation.
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公开(公告)号：US20210396247A1
公开(公告)日：2021-12-23
申请号：US16907071
申请日：2020-06-19
Applicant: Textron Innovations Inc.
Abstract: A tip gap control system for a ducted aircraft includes a flight control computer including a blade length control module configured to generate a blade tip actuator command and a proprotor system in data communication with the flight control computer. The proprotor system includes a duct and proprotor blades surrounded by the duct. Each of the proprotor blades includes an active blade tip movable into various positions including a retracted position and an extended position. The tip gap control system also includes one or more actuators coupled to the active blade tips. The one or more actuators move the active blade tips between the various positions based on the blade tip actuator command, thereby controlling a tip gap between the proprotor blades and the duct.
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