With Auxiliary Propulsion, Counter-troque Or Steering Device Patents (Class 244/17.19)
  • Patent number: 7178757
    Abstract: An autogyro, or aircraft with a rotating wing, has an airframe providing a motorcycle-like configuration for the rider. The motorcycle-like straddle-type seat locates the rider in front of the rotating wing, behind a teardrop shaped simulated fuel tank, and above the motorcycle engine used for turning the front-mounted propeller. A motorcycle-like handlebar controls the aircraft, including the adjustment for the rotating wing axis of rotation with respect to the aircraft and the engine throttle. Additional controls for operating the aircraft on the ground, such as wheel brakes and the steering, are also controlled from the handlebar.
    Type: Grant
    Filed: February 8, 2005
    Date of Patent: February 20, 2007
    Inventors: Charlene Breese, Vance Breese
  • Patent number: 7104499
    Abstract: A system for providing aircraft thrust includes a compressor, operable to take in a quantity of air, reduce the volume of the air to generate compressed air, and to deliver the compressed air to a tank. The tank is coupled to the compressor and is operable to receive the compressed air, store the compressed air, and deliver the compressed air to a nozzle mounted externally to the aircraft. The nozzle is operable to receive the compressed air and discharge the compressed air to provide thrust for the aircraft.
    Type: Grant
    Filed: September 25, 2002
    Date of Patent: September 12, 2006
    Assignee: Northrop Grumman Corporation
    Inventor: Allen A. Arata
  • Patent number: 7077358
    Abstract: A helicopter having a torque-correcting thruster device. The helicopter has an aerodynamic body which has opposite side portions, a top portion and a bottom portion. The aerodynamic body has a cockpit and a pilot seat in the cockpit. The helicopter includes landing gear attached to the bottom portion of the aerodynamic body. The helicopter includes a rotor that is supported by the aerodynamic body and a rotor blade attached to the rotor, and a thruster device operative on one of the side portions of the aerodynamic body to produce an aft-directed thrust that counteracts the torque produced by rotation of the rotor blade so as to control the yaw of the helicopter. The aft-directed thrust simultaneously supplements the forward thrust of the helicopter.
    Type: Grant
    Filed: January 27, 2005
    Date of Patent: July 18, 2006
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventor: James R. Quartarone
  • Patent number: 7063289
    Abstract: A vertical stabilizer (38) is supported by and projects upwardly and rearwardly from the tail portion (14) of a helicopter fuselage (12). A tail rotor (TSR) is mounted on the vertical stabilizer (38) for rotation about a horizontal axis (C). The tail rotor (TSR) is positioned laterally outwardly from one side of the vertical stabilizer (38). The vertical stabilizer (38) has an upper end, a lower end and a rear edge recess (44) located between the upper end and the lower end. The recess (44) has a laterally convex rear edge (50). The tail portion (14) of fuselage (12) has a rear end extension (40) that extends rearwardly from the vertical stabilizer (38) and narrows in width as it extends rearwardly. The rear end extension (40) of the fuselage (12) provides vertical area to replace vertical area that was removed by placement of the recess (44) in the vertical stabilizer (38).
    Type: Grant
    Filed: September 28, 2004
    Date of Patent: June 20, 2006
    Inventor: Robert J. Desroche
  • Patent number: 7032860
    Abstract: An anti-torque thruster system implemented onboard an aircraft comprising a propulsion means coupled to the aircraft, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the aircraft, a fuel storage container coupled to the propulsion means via a fuel delivery conduit, wherein the fuel storage container is capable of storing an appropriate fuel for the propulsion means, a valve means disposed between the fuel storage container and the propulsion means, wherein the valve means may be useable to regulate the flow of fuel from the fuel storage container to the propulsion means, and a controller for controlling the valve means to regulate the flow of fuel from the fuel storage container to the propulsion means, wherein the controller is capable of receiving input from at least one input device.
    Type: Grant
    Filed: November 5, 2004
    Date of Patent: April 25, 2006
    Assignee: EATTS, LLC
    Inventors: Charles T. Kirk, Virginia L. Hodder, legal representative, Grover L. Moore, deceased
  • Patent number: 6929215
    Abstract: A tail rotor system for a helicopter includes a gear box housing retainer (66) coupled to the tail boom (16) of the helicopter. The tail rotor system also includes a power-limiting device (50) configured to disconnect the tail rotor from a power plant for driving the tail rotor about a rotor axis of rotation.
    Type: Grant
    Filed: September 4, 2002
    Date of Patent: August 16, 2005
    Inventor: Paul E. Arlton
  • Patent number: 6869045
    Abstract: A vertical stabilizer (38) is supported by and projects upwardly and rearwardly from the tail portion (14) of a helicopter fuselage (12). A tail rotor (TSR) is mounted on the vertical stabilizer (38) for rotation about a horizontal axis (C). The tail rotor (TSR) is positioned laterally outwardly from one side of the vertical stabilizer (38). The vertical stabilizer (38) has an upper end, a lower end and a rear edge recess (44) located between the upper end and the lower end. The recess (44) has a laterally convex rear edge (50). The tail portion (14) of fuselage (12) has a rear end extension (40) that extends rearwardly from the vertical stabilizer (38) and narrows in width as it extends rearwardly. The rear end extension (40) of the fuselage (12) provides vertical area to replace vertical area that was removed by placement of the recess (44) in the vertical stabilizer (38).
    Type: Grant
    Filed: March 11, 2004
    Date of Patent: March 22, 2005
    Assignee: Boudary Layer Research, Inc.
    Inventor: Robert J. Desroche
  • Patent number: 6863240
    Abstract: To achieve the required optional conformability and navigability of the hovering motion of the hovering body in a free liquid environment, the hovering body is equipped with a suitable created mechanism for optional control of direction and/or the position of the hovering motion in the form of the basic jacket suitably equipped with at least one slot jet where the basic jacket is suitably connected to the elongated jacket mechanism for the optional stabilization of the direction and/or the position of the hovering motion suitably equipped with at least one uplift component.
    Type: Grant
    Filed: October 11, 2000
    Date of Patent: March 8, 2005
    Inventor: Jan Námis{hacek over (n)}ák
  • Patent number: 6758436
    Abstract: A propeller related vehicle in accordance with one embodiment of the present invention is described as a helicopter having an airframe housing a pneumatic motor mechanism for powering a main propeller attached to a main drive shaft. The helicopter further includes a horizontal stabilizing means attached between the main propeller and the main drive shaft, which permits the main propeller to freely pivot about the main drive shaft independently from the airframe. As such when the main propeller is rotating and the main propeller begins to pitch, the rotating main propeller has a centrifugal force created by the rotation thereof and will tend to pivot about the horizontal stabilizing means in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position.
    Type: Grant
    Filed: October 23, 2002
    Date of Patent: July 6, 2004
    Assignee: Rehco, LLC
    Inventors: Jeffrey Rehkemper, Keith Johnson
  • Patent number: 6755374
    Abstract: A preferred embodiment of a rotary-wing aircraft comprises a main rotor, a tail boom extending through an area of downwash from the main rotor, and a linear nozzle fixedly coupled to the tail boom and having an opening extending along the tail boom for discharging a sheet of fluid in a direction substantially tangential to an outer surface of the tail boom. A preferred embodiment also comprises a yaw-control device movably coupled to the tail boom and having an opening formed therein for discharging fluid in a direction away from the yaw-control device and into the area of downwash from the main rotor.
    Type: Grant
    Filed: January 27, 2003
    Date of Patent: June 29, 2004
    Inventor: Franklin D. Carson
  • Patent number: 6732973
    Abstract: A stabilizer attached between a propeller and a shaft; and the propeller is pivotally mounted to the shaft in a substantially perpendicular plane to the shaft. The stabilizer has a tendency to exert a reactionary force on the propeller, when the propeller pivots in relation to the shaft, such that the reactionary force tends to return the propeller in the substantially perpendicular plane.
    Type: Grant
    Filed: October 23, 2002
    Date of Patent: May 11, 2004
    Assignee: Rehco, LLC
    Inventor: Jeffrey Rehkemper
  • Patent number: 6729576
    Abstract: The present invention broadly relates to a tail cone assembly for a helicopter. The tail cone assembly includes a monocoque shell formed from a composite material. The composite material preferably comprises a non-metallic matrix, such as an epoxy resin matrix, having fibers, such as graphite fibers, embedded therein. The fibers may be oriented along a single axis or along multiple axes. Other components of the tail cone assembly may also be formed from composite materials, which composite materials may be the same as or different from the composite material forming the shell.
    Type: Grant
    Filed: August 13, 2002
    Date of Patent: May 4, 2004
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Bruce Frederic Kay, Alan Roy Goodworth
  • Patent number: 6715711
    Abstract: A hub-protecting cap for use with a helicopter. The helicopter has a fuselage, a tail rotor assembly operatively coupled to the fuselage for rotation relative to the fuselage about a tail rotor axis, at least one tail rotor blade detachably connected to the tail rotor assembly, a retention pin, and a pitch control link mechanism. The hub-protecting cap comprises a cap body portion, a pin-receiving aperture, and a link-attaching portion. The cap body portion is adapted to be attached to a hub portion of the tail rotor assembly in a manner to cover the hub portion when the tail rotor blade is detached from the tail rotor assembly. The cap body portion has a hub socket adapted such that pitch change bearing surfaces of the hub portion are within the hub socket of the cap body portion when the cap body portion is attached to the hub portion. The pin-receiving aperture is through the cap body portion.
    Type: Grant
    Filed: April 1, 2003
    Date of Patent: April 6, 2004
    Assignee: The Boeing Company
    Inventors: Neal W. Muylaert, Christopher T. Duffield
  • Patent number: 6666404
    Abstract: Conventional rotorcraft are required to provide a significant amount of anti-torque movement to offset the torque created by the rotor and the right-angle gearbox coupling the rotor to the engine. By vertically integrating the engine in the unmanned rotorcraft of the present invention, the torque component rising from the right-angle gearbox is eliminated. This type of adaptation, however, is generally unacceptable in conventional helicopter integration, since a vertically mounted engine directly under the rotor would deprive the user of critical payload volume at the center of gravity. The radial distribution of payload in the design of the present invention avoids this penalty. Conventional anti-torque systems, including tail rotors, ducted gas, and dual counter rotating rotors produce drag, weight, and efficiency penalties.
    Type: Grant
    Filed: October 8, 2002
    Date of Patent: December 23, 2003
    Assignee: The Boeing Company
    Inventors: David A. Wingert, James Hanna, Donald E. Jones
  • Patent number: 6659395
    Abstract: A propeller related vehicle in accordance with one embodiment of the present invention is described as a helicopter having an airframe housing a motor mechanism for powering a main propeller attached to a main drive shaft that extends vertically through the airframe and for powering a tail rotor. The helicopter further includes a horizontal stabilizing mechanism attached between the main propeller and the main drive shaft, which permits the main propeller to freely pivot about the main drive shaft independently from the airframe. As such when the main propeller is rotating and the main propeller begins to pitch, the rotating main propeller has a centrifugal force created by the rotation thereof and will tend to pivot about the horizontal stabilizing mechanism in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position. In addition various main propeller configurations may be employed that provide additional self-stabilization.
    Type: Grant
    Filed: July 8, 2002
    Date of Patent: December 9, 2003
    Assignee: Rehco, LLC
    Inventors: Jeffrey Rehkemper, Keith Johnson, Nicholas Grisolia
  • Patent number: 6612195
    Abstract: A face gear transmission system divides the input torque into multiple kinematic paths. The first kinematic scheme consists of a drive shaft and driven shaft having a plurality of pinions which contact a primary face gear. The second kinematic scheme consists of two independent symmetrical gear paths. One is a first pinion, a first idler and a first idler face gear and the primary face gear. The other independent gear path is a pinion on the second shaft, the idler, and second idler face gear and the primary face gear. The face gear transmission is especially applicable to rotorcraft having one or more input drive shafts to provide a proprotor transmission system which is relatively small in size and light in weight.
    Type: Grant
    Filed: November 26, 2001
    Date of Patent: September 2, 2003
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Yuriy Z. Gmirya, Jules G. Kish
  • Patent number: 6416015
    Abstract: A rotary-wing aircraft comprises a main rotor, a tail boom extending through an area of downwash from the main rotor, and first and second linear nozzles fixedly coupled to the tail boom. The first nozzle is adapted to discharge a sheet of fluid in a direction substantially tangential to an outer surface of the tail boom to divert the rotor downwash and thereby produce a force that counteracts the biasing torque of the main rotor. The rotary-wing aircraft further comprises a yaw-control member movably coupled to the tail boom. The second nozzle is adapted to discharge a sheet of fluid in a direction substantially tangential to an outer surface of the yaw-control member to further divert the rotor downwash and thereby increase the force that counters the main-rotor torque.
    Type: Grant
    Filed: May 1, 2001
    Date of Patent: July 9, 2002
    Inventor: Franklin D. Carson
  • Patent number: 6371408
    Abstract: Apparatus and methods for automatically altering tail rotor authority on a helicopter based on ambient air pressure and temperature changes utilizing a sealed bellows which extends or retracts based on temperature and or pressure changes thereby moving a target attached thereto. Target position movement is sensed by proximity sensors which in turn activate relays operating a drive motor which changes the pivot position of a walking beam, bell crank or other tail rotor pitch control mechanism positioned between a manual input linkage and an output linkage extending to the tail rotor pitch control thereby altering the maximum tail rotor control, tail rotor authority available by a given movement of the manual input linkage while concurrently controlling the alignment of the proximity sensors so that the target is maintained between the proximity sensors.
    Type: Grant
    Filed: August 3, 2000
    Date of Patent: April 16, 2002
    Inventor: Dennis Halwes
  • Patent number: 6352220
    Abstract: In at least one embodiment, the apparatus of the invention is a flight vehicle tail assembly having an exterior surface, at least one first vent in the exterior surface, at least one second vent in the exterior surface, and an air passage connecting the at least one first vent to the at least one second vent allowing air to flow therebetween. Where the at least one first vent is located near a high air pressure area acting on the exterior surface during a range of predefined flight conditions. Further, the at least one second vent is located near a low air pressure area acting on the exterior surface during the predefined flight conditions. So that at the predefined flight conditions adverse loads on the tail assembly are reduced by venting air from the high pressure area, through the tail assembly, to the low pressure area.
    Type: Grant
    Filed: June 2, 2000
    Date of Patent: March 5, 2002
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Daniel W. Banks, Henry L. Kelley
  • Patent number: 6290171
    Abstract: The present invention relates to a device (1A) for controlling a hybrid countertorque system of a helicopter (He), which comprises a countertorque rotor (R2), and at least one aerodynamic steering surface (D). According to the invention, said device comprises means (1A) for controlling, as a matter of priority, the aerodynamic surface (D) so that it generates lift which represents at least part of a first control command, which can be executed by said surface (D), and to control the countertorque rotor (R2) in such a way that the combined action of the surface (D) and of the rotor (R2) represents a command for controlling the helicopter (He) in terms of yaw.
    Type: Grant
    Filed: October 6, 1998
    Date of Patent: September 18, 2001
    Assignee: Eurocopter
    Inventors: André-Michel Dequin, Valery Lionel Delisle
  • Patent number: 6193189
    Abstract: In a rotary engine having rotating cylinders which burns a fuel which is not mixed with oil there is a real problem of centrifugal force form the rotating engine causing oil to flow into the combustion chambers. The disclosed rotary engine has oil reservoirs which are positioned radially outwardly from the pistons so that centrifugal force resulting from engine rotation tends to keep oil out of the combustion chambers.
    Type: Grant
    Filed: August 10, 1999
    Date of Patent: February 27, 2001
    Inventor: James R. Keever