Patents by Inventor Kip Gregory Campbell

Kip Gregory Campbell has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20220204152
    Abstract: One embodiment is an aircraft including a main body, a plurality of propulsion assemblies, and a plurality of hinges, wherein each of the plurality of propulsion assemblies is rotatably coupled to the main body using a hinge from the plurality of hinges. In an example, the aircraft includes four motor support arms and each motor support arm rotatably couples a specific propulsion assembly to a specific corresponding hinge on the main body of the aircraft and increases a span of the aircraft when the aircraft is in the flight configuration and reduces the footprint of the aircraft when the aircraft is in a storage configuration.
    Type: Application
    Filed: December 28, 2020
    Publication date: June 30, 2022
    Inventor: Kip Gregory Campbell
  • Publication number: 20220120778
    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.
    Type: Application
    Filed: December 27, 2021
    Publication date: April 21, 2022
    Inventor: Kip Gregory Campbell
  • Patent number: 11238200
    Abstract: A method of operating a targeting system simulation tool (TSST) includes providing a TSST configured to receive an obstacle/effect parameterization, a simulation parameterization, a sensor parameterization, an aircraft parameterization, and an autonomy parameterization. The method further includes receiving by the TSST, at least one of each of an obstacle/effect parameterization and a simulation parameterization. The method further includes receiving by the TSST, either (1) a sensor parameterization or (2) an aircraft parameterization. The method further includes operating the TSST to apply the provided ones of the obstacle/effect parameterization, simulation parameterization, sensor parameterization, and aircraft parameterization to generate a value, value range, or value limit for the unprovided aircraft parameterization or unprovided sensor parameterization.
    Type: Grant
    Filed: March 5, 2019
    Date of Patent: February 1, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Michael McNair, Brent Chadwick Ross, Christopher Stroncek, Kip Gregory Campbell, Joseph Scott Drennan, Brett Zimmerman, Carey Cannon
  • Publication number: 20220004205
    Abstract: A method of autonomous flight path planning for a group of cooperating aircraft operating in formation includes: receiving information related to obstructions that interfere with an aircraft of the group continuing on a flight path; calculating a velocity obstacle for each obstruction; calculating a plurality of candidate velocities outside of the velocity obstacles; selecting a first velocity from the candidate velocities and operating a leader of the group at the first velocity; calculating, based upon keeping a follower aircraft in formation, a second velocity for the follower; determining whether the second velocity is inside one of the velocity obstacles; operating the follower at the second velocity when the second velocity is outside the velocity obstacles; and calculating a revised velocity that is outside of the velocity obstacles and operating the follower at the revised velocity when the second velocity is inside one of the velocity obstacles.
    Type: Application
    Filed: July 1, 2020
    Publication date: January 6, 2022
    Applicant: Bell Textron Inc.
    Inventors: Michael McNair, Juan Li, Kip Gregory Campbell
  • Patent number: 11209453
    Abstract: According to one implementation of the present disclosure, a method for determining airspeed for an unpowered vehicle is disclosed. The method includes: 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 respective first and second body-fixed load factor measurements; determining an angle-of-attack parameter; determining a body Z-force coefficient based on the angle-of-attack parameter; and determining an airspeed value based on the second body-fixed load factor measurement and the second body-fixed coefficient.
    Type: Grant
    Filed: August 21, 2019
    Date of Patent: December 28, 2021
    Assignee: Textron Innovations Inc.
    Inventor: Kip Gregory Campbell
  • Patent number: 11198509
    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.
    Type: Grant
    Filed: January 23, 2020
    Date of Patent: December 14, 2021
    Assignee: Textron Innovations Inc.
    Inventor: Kip Gregory Campbell
  • Publication number: 20210371085
    Abstract: An unmanned rotorcraft includes an airframe, rotor blades that are coupled to the airframe for rotation therewith, a propulsion unit having a propeller, and an actuator that is coupled to the airframe and adapted to temporarily reorient the propulsion unit such that an axis of the propeller moves out of alignment with an axis of the rotor blades. Rotation of the propeller causes counter-rotation of the airframe and rotor blades. The rotor blades and blades of the propeller are adapted to deploy from collapsed positions when flight of the rotorcraft is initiated. A method of operation by the rotorcraft includes, when it is determined that a current heading does not correspond to a determined flight path, causing the actuator to temporarily reorient the propulsion unit in accordance with an angular orientation of the actuator relative to the current heading.
    Type: Application
    Filed: June 1, 2020
    Publication date: December 2, 2021
    Applicant: Bell Textron Inc.
    Inventor: Kip Gregory Campbell
  • Publication number: 20210341947
    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.
    Type: Application
    Filed: July 12, 2021
    Publication date: November 4, 2021
    Inventor: Kip Gregory Campbell
  • Publication number: 20210269170
    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.
    Type: Application
    Filed: February 28, 2020
    Publication date: September 2, 2021
    Applicant: Bell Textron Inc.
    Inventor: Kip Gregory CAMPBELL
  • Patent number: 11061410
    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.
    Type: Grant
    Filed: April 30, 2019
    Date of Patent: July 13, 2021
    Assignee: TEXTRON INNOVATIONS INC.
    Inventor: Kip Gregory Campbell
  • Publication number: 20210197953
    Abstract: A ducted-rotor aircraft may include a fuselage and first and second ducts that are coupled to the fuselage at respective first and second locations. The first location may be on a first side of a fuselage of the aircraft and spaced from a nominal yaw axis of the aircraft. The second location may be on an opposed second side of the fuselage and spaced from the nominal yaw axis. Each duct may include a rotor that is disposed in an opening that extends through the duct. Each rotor may include a plurality of blades. Each duct may further include a control vane that is mounted aft of the plurality of blades and that is pivotable about a vane axis that is oriented toward the nominal yaw axis.
    Type: Application
    Filed: December 31, 2019
    Publication date: July 1, 2021
    Applicant: Bell Textron Inc.
    Inventors: Karl Schroeder, William Anthony Amante, Kip Gregory Campbell
  • Patent number: 10946956
    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.
    Type: Grant
    Filed: August 30, 2018
    Date of Patent: March 16, 2021
    Assignee: Textron Innovations Inc.
    Inventor: Kip Gregory Campbell
  • Publication number: 20210055324
    Abstract: According to one implementation of the present disclosure, a method for determining airspeed for an unpowered vehicle is disclosed. The method includes: 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 respective first and second body-fixed load factor measurements; determining an angle-of-attack parameter; determining a body Z-force coefficient based on the angle-of-attack parameter; and determining an airspeed value based on the second body-fixed load factor measurement and the second body-fixed coefficient.
    Type: Application
    Filed: August 21, 2019
    Publication date: February 25, 2021
    Inventor: Kip Gregory Campbell
  • Publication number: 20210056857
    Abstract: According to one implementation of the present disclosure, a method for formation flight is disclosed. The method includes: during flight, arranging for a first aircraft to fly into a proximity range of a second aircraft; and determining first aircraft positioning based on power consumption data of the first aircraft, where the first aircraft positioning corresponds to power-reducing formation flight of the first aircraft.
    Type: Application
    Filed: August 20, 2019
    Publication date: February 25, 2021
    Inventors: Kip Gregory Campbell, Juan Li
  • Publication number: 20200348695
    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.
    Type: Application
    Filed: April 30, 2019
    Publication date: November 5, 2020
    Inventor: Kip Gregory Campbell
  • Patent number: 10676188
    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.
    Type: Grant
    Filed: October 4, 2017
    Date of Patent: June 9, 2020
    Assignee: Textron Innovations Inc.
    Inventor: Kip Gregory Campbell
  • Publication number: 20200156788
    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.
    Type: Application
    Filed: January 23, 2020
    Publication date: May 21, 2020
    Applicant: Textron Innovations Inc.
    Inventor: Kip Gregory Campbell
  • Publication number: 20200140079
    Abstract: An aircraft is described and includes an airframe including first and second wings each having first and second oppositely disposed wing tips; first and second booms respectively extending longitudinally between the first and second wings and having forward and aft ends; first and second tail assemblies respectively coupled to aft ends of the first and second booms; first and second forward propulsion assemblies respectively coupled to the forward ends of the first and second booms, wherein the first and second forward propulsion assemblies are tiltable between a vertical takeoff and landing (“VTOL”) flight mode orientation and a forward flight mode orientation; first and second aft propulsion assemblies respectively coupled to upper ends of the tail assemblies, wherein the first and second aft propulsion assemblies are tiltable between a VTOL flight mode orientation and a forward flight mode orientation; and a payload module removably coupled to the airframe.
    Type: Application
    Filed: November 2, 2018
    Publication date: May 7, 2020
    Applicant: Textron Innovations Inc.
    Inventor: Kip Gregory Campbell
  • Patent number: 10618656
    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. One of a plurality of payload modules is interchangeable coupled to the airframe, wherein each payload module has a respective function.
    Type: Grant
    Filed: October 4, 2017
    Date of Patent: April 14, 2020
    Assignee: Textron Innovations Inc.
    Inventor: Kip Gregory Campbell
  • Publication number: 20200070969
    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.
    Type: Application
    Filed: August 30, 2018
    Publication date: March 5, 2020
    Applicant: Textron Innovations Inc.
    Inventor: Kip Gregory Campbell