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公开(公告)号：US11492116B2
公开(公告)日：2022-11-08
申请号：US17545158
申请日：2021-12-08
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell
Abstract: A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes an airframe having at least one wing. First and second oppositely disposed booms extend longitudinally from the at least one wing. Forward rotors are coupled to the forward ends of the booms and aft rotors are coupled to the aft ends of the booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the booms, and a forward thrust orientation, wherein the forward rotors are forward of the booms. The aft rotors are reversibly tiltable between a vertical lift orientation, wherein the aft rotors are below the booms, and a forward thrust orientation, wherein the aft rotors are aft of the booms.
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公开(公告)号：US10946956B2
公开(公告)日：2021-03-16
申请号：US16118372
申请日：2018-08-30
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell
Abstract: An unmanned aerial system includes an elongated fuselage having first and second rotational degrees of freedom. A forward propulsion assembly is disposed at the forward end of the fuselage. The forward propulsion assembly includes a forward rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a first gimballing axis to provide a first moment on the fuselage in the first rotational degree of freedom. An aft propulsion assembly is disposed at the aft end of the fuselage. The aft propulsion assembly includes an aft rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a second gimballing axis to provide a second moment on the fuselage in the second rotational degree of freedom. The first gimballing axis is out of phase with the second gimballing axis to control the orientation of the fuselage.
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公开(公告)号：US20240336366A1
公开(公告)日：2024-10-10
申请号：US18749764
申请日：2024-06-21
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell , Kristen Stuart , Steven G. Hagerott
CPC classification number: B64D31/00 , B64C27/635 , B64C27/68 , B64C39/024 , B64D27/24 , B64U30/20 , B64U50/19 , B64U2201/00
Abstract: A system can include a flight controller for an aircraft that includes an electric motor that drives blades with a variable pitch, where the flight controller receives a command to change a flight characteristic of the aircraft and creates a torque command and a revolutions per minute (RPM) command. The system can also include a propulsion assembly, where the propulsion assembly creates a current command based at least in part on the torque command and the RPM command, creates a blade pitch command based at least in part on the torque command and the RPM command, communicates the current command to the electric motor to change a mechanical output of the electric motor, and communicates the blade pitch command to blade actuators to control the pitch of the blades. The current command and the blade pitch command cause the blades of the aircraft to rotate at a predetermined RPM.
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公开(公告)号：US20220120778A1
公开(公告)日：2022-04-21
申请号：US17562501
申请日：2021-12-27
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell
Abstract: According to one implementation of the present disclosure, a method for determining airspeed for an unpowered vehicle is disclosed. The method includes: determining first and second body-fixed load factor measurements; determining a body Z-force coefficient based on an angle-of-attack parameter; and determining an airspeed value based on the second body-fixed load factor measurement and the body Z-force coefficient.
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公开(公告)号：US11853081B2
公开(公告)日：2023-12-26
申请号：US17373682
申请日：2021-07-12
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell
CPC classification number: G05D1/0607 , B64D45/00 , G08G5/0047
Abstract: According to one implementation of the present disclosure, a method for determining angle-of-attack for an unpowered vehicle is disclosed. The method includes: determining a monotonic portion of a look-up curve of an angle-of-attack operating plot; during flight, determining, by an accelerometer disposed on the unpowered vehicle, first and second accelerometer outputs, where the first and second accelerometer outputs correspond to first and second body-fixed load factor measurements, respectively; determining an operating point on the monotonic portion by applying a quotient of the first and second accelerometer outputs to the angle-of-attack operating plot; and determining an angle-of-attack parameter corresponding to the determined operating point.
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Patent Agency Ranking
公开(公告)号：US11198509B2
公开(公告)日：2021-12-14
申请号：US16750269
申请日：2020-01-23
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell
Abstract: A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes an airframe having a wing with oppositely disposed wing tips. Tip booms respectively extend longitudinally from the wing tips. Forward rotors are coupled to the forward ends of the tip booms and aft rotors are coupled to the aft ends of the tip booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the tip booms, and a forward thrust orientation, wherein the forward rotors are forward of the tip booms. The aft rotors are reversibly tiltable between a vertical lift orientation, wherein the aft rotors are below the tip booms, and a forward thrust orientation, wherein the aft rotors are aft of the tip booms.
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公开(公告)号：US20200070969A1
公开(公告)日：2020-03-05
申请号：US16118372
申请日：2018-08-30
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell
Abstract: An unmanned aerial system includes an elongated fuselage having first and second rotational degrees of freedom. A forward propulsion assembly is disposed at the forward end of the fuselage. The forward propulsion assembly includes a forward rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a first gimballing axis to provide a first moment on the fuselage in the first rotational degree of freedom. An aft propulsion assembly is disposed at the aft end of the fuselage. The aft propulsion assembly includes an aft rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a second gimballing axis to provide a second moment on the fuselage in the second rotational degree of freedom. The first gimballing axis is out of phase with the second gimballing axis to control the orientation of the fuselage.
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公开(公告)号：US10676188B2
公开(公告)日：2020-06-09
申请号：US15724649
申请日：2017-10-04
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell
Abstract: A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The tiltrotor aircraft includes a longitudinally extending fuselage with a wing extending laterally therefrom having oppositely disposed wing tips distal from the fuselage. Tip booms respectively extend longitudinally from the wing tips. Forward rotors are coupled to the forward ends of the tip booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the tip booms, and a forward thrust orientation, wherein the forward rotors are forward of the tip booms. An aft rotor is coupled to the aft end of the fuselage. The aft rotor is reversibly tiltable between a vertical lift orientation, wherein the aft rotor is below the fuselage, and a forward thrust orientation, wherein the aft rotor is aft of the fuselage.
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公开(公告)号：US20200156788A1
公开(公告)日：2020-05-21
申请号：US16750269
申请日：2020-01-23
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell
Abstract: A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes an airframe having a wing with oppositely disposed wing tips. Tip booms respectively extend longitudinally from the wing tips. Forward rotors are coupled to the forward ends of the tip booms and aft rotors are coupled to the aft ends of the tip booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the tip booms, and a forward thrust orientation, wherein the forward rotors are forward of the tip booms. The aft rotors are reversibly tiltable between a vertical lift orientation, wherein the aft rotors are below the tip booms, and a forward thrust orientation, wherein the aft rotors are aft of the tip booms.
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公开(公告)号：US11970284B2
公开(公告)日：2024-04-30
申请号：US16804137
申请日：2020-02-28
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell
Abstract: An exemplary method to determine an airspeed and an angle of attack of a propeller powered vehicle includes determining the power delivered to the propeller, the air density, a propeller power coefficient, an advance ratio for the propeller, and the airspeed using the advance ratio and determining the angle of attack using the airspeed.
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