Patents by Inventor Mark R. Alber

Mark R. Alber 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).

  • Patent number: 10589854
    Abstract: An aircraft is provided and includes a fuselage from which a tilt-wing respectively extends, first prop-rotors, which are formed to define first rotor disks and which are respectively disposed on first portions of each side of the tilt-wing, second prop-rotors, which are formed to define second rotor disks and which are respectively disposed on second portions of each side of the tilt-wing such that the corresponding pairs of first and second rotor disks overlap, and a drive shaft system. The drive shaft system is configured to synchronize respective operations of the first and second prop-rotors.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: March 17, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Mark R. Alber, Jeffrey Parkhurst, Charles Gayagoy
  • Patent number: 10538322
    Abstract: A vertical take-off and landing (VTOL) aircraft is provided. The aircraft includes a wing, nacelles supportively disposed at opposite ends of the wing, proprotors respectively attached to each of the nacelles with each of the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and a delta-wing shaped fuselage disposed along the wing between the nacelles.
    Type: Grant
    Filed: October 16, 2015
    Date of Patent: January 21, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Mark R. Alber, Charles Gayagoy
  • Publication number: 20200017207
    Abstract: A yaw control system of an aircraft includes an aircraft having an airframe extending along a longitudinal axis, a coaxial contra-rotating main rotor system rotatable about a first axis, and a rotor system rotatable about a second axis to move air between a first side of the airframe and a second, opposite side of the airframe. The first side and the second side are disposed on opposing sides of the longitudinal axis. The yaw control provided by operation of the rotor system is supplemental to the yaw control provided by the coaxial contra-rotating main rotor system.
    Type: Application
    Filed: July 12, 2018
    Publication date: January 16, 2020
    Inventor: Mark R. Alber
  • Patent number: 10527123
    Abstract: An aircraft includes an airframe having an extending tail and a longitudinal axis extending from a nose of the airframe defining a length of the airframe. A counter rotating, coaxial main rotor assembly is located at the airframe and includes an upper rotor assembly and a lower rotor assembly. The upper rotor assembly and the lower rotor assembly rotate about an axis of rotation. The axis of rotation intersects the longitudinal axis forward of a midpoint of the longitudinal axis.
    Type: Grant
    Filed: July 14, 2015
    Date of Patent: January 7, 2020
    Assignee: SIKORSKY AIRCRAFT CORP
    Inventors: Mark R. Alber, William J. Eadie
  • Patent number: 10513332
    Abstract: An aircraft includes a fuselage defining an aircraft attitude axis. The fuselage houses an engine fixed relative to the aircraft attitude axis. A rotor assembly is operatively connected to rotate back and forth relative to the aircraft attitude axis from a first position predominately for lift to a second position predominately for thrust. The rotor assembly includes a rotor that is operatively connected to be driven by the engine.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: December 24, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Mark R. Alber, Jeffrey Parkhurst, Charles Gayagoy
  • Patent number: 10508887
    Abstract: A flight control system for an aircraft includes a flight control computer operatively interconnected with a main rotor system and a translational thrust system of the aircraft. A selectively enabled integrated target and flight control system arranged in communication with the flight control computer. The integrated target flight and control system is configured to control pitch attitude and heading of the aircraft. When the integrated target and flight control system is enabled, at least partial operation of the aircraft is controlled in response to a pilot input via the flight control computer.
    Type: Grant
    Filed: May 22, 2017
    Date of Patent: December 17, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Matthew T. Luszcz, David L. Adams, Mark R. Alber
  • Patent number: 10486806
    Abstract: A tiltwing aircraft includes a fuselage, an engine mounted stationary relative to the fuselage, and an opposed pair of wings. The wings are separated from each other with the fuselage therebetween, each wing independently mounted to the fuselage by a respective pivot system for rotation relative to the fuselage. An opposed pair of rotor assemblies is included, each operatively connected to a respective one of the wings for common rotation with the respective wing back and forth between a first position predominantly for lift to a second position predominantly for thrust.
    Type: Grant
    Filed: September 23, 2016
    Date of Patent: November 26, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Mark R. Alber
  • Patent number: 10389078
    Abstract: A cooling system for a rotorcraft laser system is provided. The cooling system includes at least one laser carrying component operatively coupling a laser turret and a laser generating assembly. The cooling system also includes at least one fuel line fluidly coupled to a fuel tank containing a fuel. The cooling system further includes a heat exchanger containing a portion of the laser carrying component and the fuel line to transfer heat therebetween to cool the laser carrying component.
    Type: Grant
    Filed: December 10, 2015
    Date of Patent: August 20, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Alfred Russell Smiley, Panagiotis Koliais, Timothy Fred Lauder, Mark R. Alber
  • Patent number: 10336449
    Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, wings extending outwardly from opposite sides of the fuselage, nacelles supportively disposed on the wings and reversely oriented, axial flow engines disposed in each of the nacelles to generate mechanical energy for driving lift and thrust generating prop-rotor rotations.
    Type: Grant
    Filed: April 19, 2016
    Date of Patent: July 2, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Mark R. Alber
  • Patent number: 10309857
    Abstract: A method for determining a center-of-gravity of an aircraft in three dimensions includes determining a first center-of-gravity location for an aircraft in a first plane defined by a first axis and a second axis. The method includes positioning the aircraft in a tilted position by rotating the aircraft and determining a second center-of-gravity location for the aircraft in the first plane in the tilted position. The method includes comparing the first center-of-gravity location to the second center-of-gravity location to determine a component of the first center-of-gravity location along a third axis defined out-of-plane from the first plane to determine a three-dimensional center-of-gravity of the aircraft.
    Type: Grant
    Filed: November 30, 2016
    Date of Patent: June 4, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Jeffrey Parkhurst, Jason Satira, Mark R. Alber
  • Publication number: 20190161175
    Abstract: A retractable landing gear system for a vertical takeoff and landing (VTOL) aircraft includes a rotational strut rotatably coupled to a fuselage of the VTOL aircraft. The rotational strut includes a first end, a second end, and an intermediate portion extending therebetween. A drag strut includes a first end portion pivotally connected to the rotational strut and a second end portion. A locking link includes a first end section pivotally connected relative to the fuselage, a second end section pivotally connected to the drag strut and an intermediate section having a hinge element. A retraction system is operatively connected to the rotational strut and the locking link. The retraction system is operable to pivot the drag strut about a first axis and rotate the rotational strut about a second axis that is distinct from the first axis.
    Type: Application
    Filed: November 29, 2017
    Publication date: May 30, 2019
    Inventors: Jason A. Satira, Charles Gayagoy, Mark R. Alber
  • Publication number: 20180312241
    Abstract: A fairing for a landing gear wheel assembly on a tail sitter aircraft is disclosed, which includes a fairing housing defining a longitudinal axis, and at least one pair of laterally opposed aerodynamic tail surfaces extending radially outward from the fairing housing for added flight stability.
    Type: Application
    Filed: April 25, 2016
    Publication date: November 1, 2018
    Applicant: Sikorsky Aircraft Corporation
    Inventor: Mark R. Alber
  • Patent number: 10106274
    Abstract: An aircraft is provided and includes a fuselage, first and second wings extending outwardly from opposite sides of the fuselage, proprotors operably disposed on each of the first and second wings to drive vertical take-off and landing aircraft operations and horizontal flight aircraft operations and a refueling system including at least one fuel tank disposed in at least one or more of the fuselage, the first wing or the second wing and a refueling apparatus. The refueling apparatus is coupled to the at least one fuel tank such that fuel is movable with respect to the at least one fuel tank during aircraft ground and aerial operations.
    Type: Grant
    Filed: March 15, 2016
    Date of Patent: October 23, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Mark R. Alber, Charles Gayagoy, Jeffrey Parkhurst, Glenn D. Tiongson
  • Publication number: 20180261966
    Abstract: A cooling system for a rotorcraft laser system is provided. The cooling system includes at least one laser carrying component operatively coupling a laser turret and a laser generating assembly. The cooling system also includes at least one fuel line fluidly coupled to a fuel tank containing a fuel. The cooling system further includes a heat exchanger containing a portion of the laser carrying component and the fuel line to transfer heat therebetween to cool the laser carrying component.
    Type: Application
    Filed: December 10, 2015
    Publication date: September 13, 2018
    Applicant: Sikorsky Aircraft Corporation
    Inventors: Alfred Russell Smiley, Panagiotis Koliais, Timothy Fred Lauder, Mark R. Alber
  • Publication number: 20180244396
    Abstract: A drive system for a rotorcraft includes at least one engine, the engine including a compressor section, and a turbine section positioned rearward from the compressor section. A main rotor input shaft extends from a rotor power turbine of the turbine section and is connectable to a main rotor assembly of the rotorcraft to transfer rotational energy from the rotor power turbine to the main rotor assembly. An auxiliary input shaft extends from an auxiliary power turbine of the turbine section and is connectible to an auxiliary rotor assembly of the rotorcraft to transfer rotational energy from the auxiliary power turbine to the auxiliary rotor assembly.
    Type: Application
    Filed: August 25, 2016
    Publication date: August 30, 2018
    Inventor: Mark R. Alber
  • Patent number: 9988148
    Abstract: A vehicle is provided and includes a wing having opposite surfaces and opposite sides and first and second engines disposed to drive wing movement and being respectively supported asymmetrically on the opposite surfaces and at the opposite sides of the wing.
    Type: Grant
    Filed: July 9, 2015
    Date of Patent: June 5, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Mark R. Alber
  • Publication number: 20180149545
    Abstract: A method for determining a center-of-gravity of an aircraft in three dimensions includes determining a first center-of-gravity location for an aircraft in a first plane defined by a first axis and a second axis. The method includes positioning the aircraft in a tilted position by rotating the aircraft and determining a second center-of-gravity location for the aircraft in the first plane in the tilted position. The method includes comparing the first center-of-gravity location to the second center-of-gravity location to determine a component of the first center-of-gravity location along a third axis defined out-of-plane from the first plane to determine a three-dimensional center-of-gravity of the aircraft.
    Type: Application
    Filed: November 30, 2016
    Publication date: May 31, 2018
    Inventors: Jeffery Parkhurst, Jason Satira, Mark R. Alber
  • Publication number: 20180148161
    Abstract: An adjustable cable attachment system for a VTOL aircraft includes a VTOL airframe. A winch is operatively connected to an underside of the airframe with the aircraft in a horizontal flight mode. An adjustable cable is operatively connected to the winch to adjustably relocate a slung load with respect to the center of gravity of the aircraft to balance the aircraft. A fixed cable is operatively connected to the underside of the airframe with the aircraft in the horizontal flight mode.
    Type: Application
    Filed: November 29, 2016
    Publication date: May 31, 2018
    Inventors: Jeffery Parkhurst, Mark R. Alber
  • Publication number: 20180086446
    Abstract: A tiltwing aircraft includes a fuselage, an engine mounted stationary relative to the fuselage, and an opposed pair of wings. The wings are separated from each other with the fuselage therebetween, each wing independently mounted to the fuselage by a respective pivot system for rotation relative to the fuselage. An opposed pair of rotor assemblies is included, each operatively connected to a respective one of the wings for common rotation with the respective wing back and forth between a first position predominantly for lift to a second position predominantly for thrust.
    Type: Application
    Filed: September 23, 2016
    Publication date: March 29, 2018
    Inventor: Mark R. Alber
  • Patent number: 9908615
    Abstract: A rotor blown wing (RBW) aircraft including an airframe, at least one rotor blown wing (RBW) having at least control selectively controllable surface, at least one rotor configured to generate and direct an airflow over the at least one RBW, and a control system operatively connected to the at least two selectively controllable control surfaces. The control system selectively controls the at least one selectively controllable control surface to change the airflow over the at least one RBW to facilitate a vertical landing.
    Type: Grant
    Filed: August 11, 2016
    Date of Patent: March 6, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Mark R. Alber, Jeffery Parkhurst, Cody Fegely, Stephen Kubik