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公开(公告)号：US11479354B2
公开(公告)日：2022-10-25
申请号：US16879129
申请日：2020-05-20
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Andrew Thomas Carter , Sung Kyun Kim , Matthew John Hill
Abstract: A propulsion assembly for an aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The propulsion assembly includes a housing coupled to the fuselage of the aircraft. A coaxial rotor system includes a first rotor assembly and a second rotor assembly that are rotatable about a common axis of rotation. The first rotor assembly counter-rotates relative to the second rotor assembly. A motor assembly is operably associated with the coaxial rotor system. The motor assembly provides torque and rotational energy to the first rotor assembly and the second rotor assembly. A gimbal assembly couples the coaxial rotor system to the housing such that the coaxial rotor system is tiltable relative to the fuselage to generate a thrust vector.
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公开(公告)号：US11320841B2
公开(公告)日：2022-05-03
申请号：US16879081
申请日：2020-05-20
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Andrew Thomas Carter , Sung Kyun Kim , Matthew John Hill
Abstract: An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. First and second yaw vanes extend aftwardly from the fuselage. A flight control system is configured to direct the thrust vector of the coaxial rotor system and control movements of the yaw vanes. In a VTOL orientation of the aircraft, differential operation of the yaw vanes and/or differential operations of first and second rotor assemblies of the coaxial rotor system provide yaw authority for the aircraft. In a biplane orientation of the aircraft, collective operation of the yaw vanes provides yaw authority for the aircraft.
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公开(公告)号：US11186357B2
公开(公告)日：2021-11-30
申请号：US16238889
申请日：2019-01-03
Applicant: Textron Innovations Inc.
IPC: G05D1/08 , B64C13/16 , B64C13/04 , B64C27/605 , B64C27/57
Abstract: In an embodiment, a method includes: obtaining a first signal from a first sensor of a rotorcraft, the first signal indicating measured angular velocity around a first axis of the rotorcraft; filtering the first signal with a lag compensator to estimate angular position around the first axis of the rotorcraft; and adjusting flight control devices of the rotorcraft according to the estimated angular position and the measured angular velocity around the first axis of the rotorcraft, thereby changing flight characteristics of the rotorcraft around the first axis of the rotorcraft.
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公开(公告)号：US11067981B2
公开(公告)日：2021-07-20
申请号：US16253037
申请日：2019-01-21
Applicant: Textron Innovations Inc.
Inventor： Sung Kyun Kim
Abstract: In accordance with an embodiment, a method of operating an aircraft includes operating the aircraft in a first mode including determining an attitude based on a pilot stick signal, where a translational speed or an attitude of the aircraft is proportional to an amplitude of the pilot stick signal in the first mode; transitioning from the first mode to a second mode when a velocity of the aircraft exceeds a first velocity threshold; and operating the aircraft in the second mode where the output of the rate controller is proportional to the amplitude of the pilot stick signal.
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公开(公告)号：US11747805B2
公开(公告)日：2023-09-05
申请号：US18060801
申请日：2022-12-01
Applicant: Textron Innovations Inc.
Inventor： Sung Kyun Kim
CPC classification number: G05D1/0061 , B64C13/503 , G05D1/0858
Abstract: In accordance with an embodiment, a method of operating an aircraft includes operating the aircraft in a first mode including determining an attitude based on a pilot stick signal, where a translational speed or an attitude of the aircraft is proportional to an amplitude of the pilot stick signal in the first mode; transitioning from the first mode to a second mode when a velocity of the aircraft exceeds a first velocity threshold; and operating the aircraft in the second mode where the output of the rate controller is proportional to the amplitude of the pilot stick signal.
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Patent Agency Ranking
公开(公告)号：US11479352B2
公开(公告)日：2022-10-25
申请号：US16879070
申请日：2020-05-20
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Andrew Thomas Carter , Sung Kyun Kim , Matthew John Hill , Lynn Francis Eschete
Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft has an airframe including first and second wings with a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. A flight control system is configured to direct the thrust vector. In the VTOL orientation, the first wing is forward of the fuselage, the second wing is aft of the fuselage and the coaxial rotor system is configured to provide thrust in line with a yaw axis of the aircraft. In the biplane orientation, the first wing is below the fuselage, the second wing is above the fuselage and the coaxial rotor system is configured to provide thrust in line with a roll axis of the aircraft.
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公开(公告)号：US20220291697A1
公开(公告)日：2022-09-15
申请号：US17720254
申请日：2022-04-13
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Andrew Thomas Carter , Sung Kyun Kim , Matthew John Hill
Abstract: An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. First and second yaw vanes extend aftwardly from the fuselage. A flight control system is configured to direct the thrust vector of the coaxial rotor system and control movements of the yaw vanes. In a VTOL orientation of the aircraft, differential operation of the yaw vanes and/or differential operations of first and second rotor assemblies of the coaxial rotor system provide yaw authority for the aircraft. In a biplane orientation of the aircraft, collective operation of the yaw vanes provides yaw authority for the aircraft.
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公开(公告)号：US11312480B2
公开(公告)日：2022-04-26
申请号：US16416508
申请日：2019-05-20
Applicant: Textron Innovations Inc.
Inventor： Luke Dafydd Gillett , Sung Kyun Kim , Robert Earl Worsham, II
IPC: B64C13/50 , B64C13/04 , B64C27/605 , B64C27/78 , B64C27/82 , B64C27/08 , B64D35/04 , B64C27/72 , B64C39/02
Abstract: In an embodiment, a rotorcraft includes: a flight control computer configured to: receive a first sensor signal from a first aircraft sensor of the rotorcraft; receive a second sensor signal from a second aircraft sensor of the rotorcraft, the second aircraft sensor being different from the first aircraft sensor; combine the first sensor signal and the second sensor signal with a complementary filter to determine an estimated vertical speed of the rotorcraft; adjust flight control devices of the rotorcraft according to the estimated vertical speed of the rotorcraft, thereby changing flight characteristics of the rotorcraft; and reset the complementary filter in response to detecting the rotorcraft is grounded.
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公开(公告)号：US20210365049A1
公开(公告)日：2021-11-25
申请号：US16879081
申请日：2020-05-20
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Andrew Thomas Carter , Sung Kyun Kim , Matthew John Hill
Abstract: An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. First and second yaw vanes extend aftwardly from the fuselage. A flight control system is configured to direct the thrust vector of the coaxial rotor system and control movements of the yaw vanes. In a VTOL orientation of the aircraft, differential operation of the yaw vanes and/or differential operations of first and second rotor assemblies of the coaxial rotor system provide yaw authority for the aircraft. In a biplane orientation of the aircraft, collective operation of the yaw vanes provides yaw authority for the aircraft.
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公开(公告)号：US20210362857A1
公开(公告)日：2021-11-25
申请号：US16879074
申请日：2020-05-20
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Andrew Thomas Carter , Sung Kyun Kim , Matthew John Hill
Abstract: An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. Tail assemblies are coupled to wingtips of the first and second wings each having an elevon that collectively form a distributed array of elevons. A flight control system is configured to direct the thrust vector of the coaxial rotor system and to control movements of the elevons such that the elevons collectively provide pitch authority and differentially provide roll authority for the aircraft in the biplane orientation. In addition, when the flight control system detects an elevon fault, the flight control system is configured to perform corrective action responsive thereto at a distributed elevon level or at a coordinated distributed elevon and propulsion assembly level.
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