Patents Examined by Jamie S Stehle
  • Patent number: 8485474
    Abstract: Apparatus and methods described herein provide for a boom/receiver-type aerial refueling system having a pressure regulator integrated into the system at the tanker boom nozzle. During refueling operations, pressure of the fuel at the interface between the nozzle at the distal end of the boom assembly and the fuel receptacle of the receiving aircraft is maintained by an integrated pressure regulator integrated into the nozzle or located inline of the fuel flow between the boom assembly and the nozzle. The integrated pressure regulator maintains the pressure of the fuel at the nozzle within a defined range regardless of the elevation azimuth of the boom assembly, the extended length of the telescoping extension, the temperature of the outside air or surfaces of the boom, and other factors that may affect the flow of fuel through the boom.
    Type: Grant
    Filed: August 31, 2010
    Date of Patent: July 16, 2013
    Assignee: The Boeing Company
    Inventors: Lance A. Cutler, Mark A. Shelly
  • Patent number: 8480034
    Abstract: According to certain embodiments, an aerial delivery system configured to be deployed from an aircraft comprises a base, a sleeve generally configured to be positioned on the base, a bag configured to receive at least one liquid and a lid assembly attached to the bag using at least one strap. In some embodiments, the strap is attached to the bag in a manner that causes the bag to be selectively compromised once the aerial delivery system is deployed from an aircraft. In one embodiment, the system comprises a cellulose-based material. In other arrangements, the bag comprises polypropylene.
    Type: Grant
    Filed: May 21, 2010
    Date of Patent: July 9, 2013
    Assignee: Caylym Technologies International, LLC
    Inventors: Richard Goddard, Michael Perlongo
  • Patent number: 8480033
    Abstract: A method and apparatus for thermally decoupling fuel from an airframe structure is provided. In some aspects, an apparatus may include a bladder wall having stratified refractory fabric and refractory metal, and a sealant coating an internal surface of the bladder wall. The bladder wall may be configured to maintain an internal surface temperature of 300° F. or less when exposed to an external surface temperature of at least 500° F.
    Type: Grant
    Filed: June 2, 2011
    Date of Patent: July 9, 2013
    Assignee: Lockheed Martin Corporation
    Inventor: Robert Shannon
  • Patent number: 8480035
    Abstract: According to certain embodiments, an aerial delivery system configured to be deployed from an aircraft comprises a base, a sleeve generally configured to be positioned on the base, a bag configured to receive at least one liquid and a lid assembly attached to the bag using at least one strap. In some embodiments, the strap is attached to the bag in a manner that causes the bag to be selectively compromised once the aerial delivery system is deployed from an aircraft. In one embodiment, the system comprises a cellulose-based material. In other arrangements, the bag comprises polypropylene.
    Type: Grant
    Filed: July 24, 2012
    Date of Patent: July 9, 2013
    Assignee: Caylym Technologies International, LLC
    Inventors: Richard Goddard, Michael Perlongo
  • Patent number: 8474754
    Abstract: Cargo hold floors are provided, and comprise panels or similar two-dimensional floor elements for the attachment of roller elements, ball elements, locking bar elements or similar functional elements. Support elements, in particular floor beams, are provided which support the two-dimensional floor elements whereby the floor elements are permanently joined to the support elements to make pre-fabricated floor modules and the floor modules are installable in the aircraft. To make installation work easier, separate load-bearing elements, for supporting the floor modules on and joining the floor modules to a body or a skin of the aircraft, are provided which, before the floor modules are installed in the aircraft, are joinable to the body or skin of the aircraft, and, when the floor modules are installed in the aircraft, are joinable to the support elements. As a result, it is possible in particular cases to make installation significantly easier.
    Type: Grant
    Filed: March 10, 2010
    Date of Patent: July 2, 2013
    Assignee: Telair International GmbH
    Inventors: Thomas Huber, Richard Holzner
  • Patent number: 8474757
    Abstract: Sleeper seats, wherein each comprises a head rest, a back rest, a seat pan or seat cushion, a leg rest, an ottomans and a dividers between the individual seats with the their column. The four seats are arranged in a staggered chevron formation and two columns. All the seats in each column are parallel with each other and set at a “herringbone” angle ?to the column direction, in other words their central axes A make the angle ?with a longitudinal axis of the array. Each seat extends from its column side of the longitudinal axis across the axis to a small extent. Along the axis, first a seat from one column crosses the axis and then a seat from the other column crosses the axis and so on.
    Type: Grant
    Filed: July 16, 2012
    Date of Patent: July 2, 2013
    Assignee: American Airlines, Inc.
    Inventor: Anthony Harcup
  • Patent number: 8453967
    Abstract: An apparatus for the recovery of an aircraft includes a capture device and first and second pole pairs. The first pole pair includes first top and bottom poles respectively placed near first top and bottom portions of the capture device. The first pole pair is configured to move from a first position, in which the pole pair holds the capture device in an open position to capture the aircraft, to a second position, in which the pole pair holds the capture device in a closed position to contain the captured aircraft after impact of the aircraft on the capture device. The second pole pair includes second top and bottom poles respectively placed near second top and bottom portions of the capture device. The second pole pair is also configured to move from the first position to the second position. Further, energy elements are coupled on one end to a respective top or bottom portion of the capture device and on another end to a respective top or bottom pole.
    Type: Grant
    Filed: June 9, 2010
    Date of Patent: June 4, 2013
    Assignee: AAI Corporation
    Inventors: Stephen W. Miller, Steven J. Fox, Graham W. Schill, Brian A. Aske
  • Patent number: 8448896
    Abstract: A nacelle includes a downstream structure having an outer structure, a concentric inner structure surrounding a downstream portion and an upstream section having a relatively small diameter and a downstream section having a relatively large diameter, the inner and outer structures define an annular flow channel. The nacelle includes a guiding system for connecting the inner structure and downstream portion or a portion of a suspension mast, the system combines a translation and rotation movement of at least a portion of the inner structure between a working position, where the inner structure is used as a cowling for the turbojet downstream portion, and a maintenance position where the inner structure exposes the turbojet downstream portion and enable movement of the portion of the inner structure along the profile of the upstream section having a relatively small diameter, and the downstream section having a relatively large diameter.
    Type: Grant
    Filed: January 21, 2009
    Date of Patent: May 28, 2013
    Assignee: Aircelle
    Inventors: Pierre Caruel, Jean-Philippe Joret, Peter Segat
  • Patent number: 8434710
    Abstract: An unmanned aerial vehicle (UAV) in the form of a “tail sitter” flying wing adapted for vertical take off and landing and transitions between flight as a helicopter and wing-borne flight. The vehicle is electrically powered from onboard batteries and equipped with rotors on miniature helicopter rotor heads at the tips of the wing for both lift, during take off and landing, and forward thrust. In planform the wing comprises, to each side of its longitudinal axis, an inner section with swept back leading and trailing edges, and an outer section with a leading edge more perpendicular to the longitudinal axis, being only mildly swept back or substantially unswept, and a swept forward trailing edge.
    Type: Grant
    Filed: November 20, 2008
    Date of Patent: May 7, 2013
    Assignee: Qinetiq Limited
    Inventors: Inderpal Singh Hothi, Jon Robert Stoackley, Steven John Stoackley
  • Patent number: 8418960
    Abstract: A rib bay platform for use in an aircraft rib bay, is adjustable in length (for example it comprises two telescopically mounted sections. The platform comprises a first end configured for mounting on a stringer of the rib bay (for example by an interference fit), and a second end configured for mounting on another stringer of the rib bay (for example on feet mounted on ball-and-socket joints). A method of operating in an aircraft rib bay comprises the steps of providing a rib bay platform of adjustable length; adjusting the length of the platform; mounting the platform between the two stringers; whereby a person may then operate inside the aircraft rib bay while being supported on the platform.
    Type: Grant
    Filed: August 3, 2007
    Date of Patent: April 16, 2013
    Assignee: Airbus Operations Limited
    Inventors: John Moore, Thomas Williams
  • Patent number: 8418965
    Abstract: A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided.
    Type: Grant
    Filed: June 1, 2009
    Date of Patent: April 16, 2013
    Assignee: Israel Aerospace Industries Ltd.
    Inventor: Israel Schnitzer
  • Patent number: 8418959
    Abstract: An unmanned aerial vehicle equipped with a spherical locking portion for landing on an unmanned ground vehicle is disclosed. The spherical locking portion can be the body of the unmanned aerial vehicle. Further, an unmanned ground vehicle for landing of an unmanned aerial vehicle, comprising a landing portion configured to have some of a spherical locking portion of the unmanned aerial vehicle inserted therein is disclosed.
    Type: Grant
    Filed: September 1, 2010
    Date of Patent: April 16, 2013
    Assignee: Pusan National University Industry—University Cooperation Foundation
    Inventors: Beom-Soo Kang, Woo-Jin Song, Tae-Wan Ku, Young-Seop Byun
  • Patent number: 8403271
    Abstract: A tapered micro-plow, or a series of tapered micro-plows, are submerged in a boundary layer just upstream of a reflection point of an oblique shock. Each micro-plow develops a beneficial pair of vortices which redistribute high energy flow within the boundary layer such that flow separation is prevented or delayed. The beneficial vortex pairs rotate about an axis that is parallel to the flow of fluid, and together rotate such that they induce a velocity on one another which tends to hold them near the surface and delay vortex lift-off.
    Type: Grant
    Filed: August 24, 2010
    Date of Patent: March 26, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: Neal D. Domel, Dan J. Baruzzini, Daniel N. Miller
  • Patent number: 8403260
    Abstract: Airship handling devices and associated systems and methods are disclosed herein. An airship handling device in accordance with one embodiment of the disclosure, for example, can include a first support member mountable to a ground vehicle. The device can also include a second support member operably coupled to the first support member and configured to rotatably move relative to the first support member about a support member axis. The second support member is out of contact with the ground vehicle. The device can further include a line attachment portion carried by the second support member and positioned to releasably couple a flexible handling line from an airship to the second support member. The handling line is not coupled to a winch.
    Type: Grant
    Filed: September 14, 2012
    Date of Patent: March 26, 2013
    Assignee: American Blimp Co., LLC
    Inventors: James R. Thiele, Carl F. Daley
  • Patent number: 8398910
    Abstract: A method for manufacturing a fiber-composite component with a cladding field and a primary component for reinforcing the fiber-composite component includes the steps of: applying a prepreg semifinished product to a mold to form the cladding field, where in the prepreg semifinished product fibers extend in some sections in a curved manner according to an assumed flow force path in the cladding field of the component to be manufactured; curing the prepreg semifinished product; applying layers of a semifinished textile product to the cured prepreg semifinished product to form the primary component; impregnating the semifinished textile product with matrix material; and curing the assembly comprising pre-cured prepreg semifinished product and semifinished textile product; a fiber-composite component with at least one structural component and a skin section connected to said structural component with a recess as well as a fiber-composite fuselage component of an aircraft with a shell component with at least one re
    Type: Grant
    Filed: February 9, 2009
    Date of Patent: March 19, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Wolfgang Kastner, Thomas Grauerholz
  • Patent number: 8393570
    Abstract: The invention relates to a device for moving a trailing edge flap of an aircraft wing, in which device the trailing edge flap comprises one or several flap segments, wherein a first flap segment is movably mounted on the wing and is connected to a first toothed movement element that is moved by means of a first pinion.
    Type: Grant
    Filed: November 21, 2008
    Date of Patent: March 12, 2013
    Assignee: Airbus Operations GmbH
    Inventor: Rainer Gartelmann
  • Patent number: 8393564
    Abstract: A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.
    Type: Grant
    Filed: September 10, 2011
    Date of Patent: March 12, 2013
    Assignee: Zee.Aero Inc.
    Inventor: Ilan Kroo
  • Patent number: 8387923
    Abstract: A jet of air is impelled on to the upper surface of a flap in order to increase its lift. Part of the air in this air jet is drawn, through air intakes, from the air stream flowing over an upper surface of the fixed part of the wing, located upstream of the flap. The air jet drawn in by suction by the air intakes is reinforced by a jet of compressed air blown through a passage which opens immediately downstream of the air intakes. This creates a combined jet of the air sucked in and the blown jet, which is ejected on to the upper surface of the flap through outlet apertures located on the rear edge of the fixed part of the wing.
    Type: Grant
    Filed: March 10, 2008
    Date of Patent: March 5, 2013
    Assignee: Alenia Aeronautica S.p.A.
    Inventor: Nicola Italo Catino
  • Patent number: 8382031
    Abstract: An engine unit for an aircraft including an engine, a device for hooking the engine, and a nacelle surrounding the engine and provided with fan cowls, the device for hooking including a rigid structure and a front aerodynamic structure whereon the fan cowls are articulated, the front aerodynamic structure including a cradle with a rear mechanism of hooking mounted on the rigid structure. The cradle also includes a front mechanism of hooking mounted on an air inlet of the nacelle.
    Type: Grant
    Filed: August 22, 2008
    Date of Patent: February 26, 2013
    Assignee: Airbus Operations
    Inventors: Loic Dussol, Frederic Ridray
  • Patent number: 8376262
    Abstract: An aircraft includes a cabin in which at least part of the space is demarcated by trim panels and the cabin is provided with a system for the active control of ambient noise. Each trim panel is either an active panel including actuators powered by the active noise control system or a passive panel without such actuators. In addition, the trim panels of the cabin of the one type, either active or passive, are mechanically interchangeable with a panel of the other type, either passive or active, respectively. Power supply wiring for active panels is installed in the aircraft, this wiring being capable of powering all active panels which could be installed, whether said active panels are actually installed or whether interchangeable passive panels are installed. Finally, a power supply system for the active panels is installed in the aircraft and connected to the power supply wiring of the active panels.
    Type: Grant
    Filed: July 9, 2008
    Date of Patent: February 19, 2013
    Assignee: European Aeronautic Defence and Space Company EADS France
    Inventor: Benoit Petitjean