Patents Issued in March 1, 2018
  • Publication number: 20180057148
    Abstract: A tiltrotor aircraft includes a fuselage supporting first and second wings each having an outboard end. First and second nacelles are respectively coupled to the outboard ends of the first and second wings. The first and second nacelles each have an outboard end. First and second wing extensions are rotatably coupled, respectively, to the outboard ends of the first and second nacelles. First and second actuators are operable to respectively move the first and second wing extensions to dampen a mode of the first and second wings, thereby stabilizing the tiltrotor aircraft.
    Type: Application
    Filed: August 31, 2016
    Publication date: March 1, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventor: Jeffrey Bosworth
  • Publication number: 20180057149
    Abstract: Actuators for high lift devices on aircraft are disclosed herein. An example apparatus includes an actuator for a high lift device of an aircraft including a motor and a transmission, where the transmission includes a first gear stage and a second gear stage, the first gear stage including a first worm gear and the second gear stage including a second worm gear, the first worm gear, the second worm gear and the motor operative to prevent backdrive of the actuator.
    Type: Application
    Filed: August 31, 2016
    Publication date: March 1, 2018
    Inventors: Christopher J. Heiberg, Patrick J. McCormick, Robert J. Atmur
  • Publication number: 20180057150
    Abstract: An aircraft includes a fuselage extending between a forward end and an aft end. The aircraft additionally includes a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor including an outer nacelle and the outer nacelle defining an inlet. Additionally, the aircraft includes a deployable assembly attached to at least one of the fuselage or the outer nacelle, the deployable assembly movable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position to increase an efficiency of the aft fan and/or of the aircraft.
    Type: Application
    Filed: August 23, 2016
    Publication date: March 1, 2018
    Inventors: Lawrence Chih-hui Cheung, Nikolai N. Pastouchenko, Kishore Ramakrishnan
  • Publication number: 20180057151
    Abstract: The invention relates to an aircraft wheel comprising a hub (52) for mounting the wheel on a landing gear axle to enable the wheel to rotate about an axis of rotation, and a rim (55) with edge flanges for receiving a tire, the rim being secured to the hub by a web (56). The hub is adapted to receive releasably a bearing box (60) comprising two bearings (53, 54) each having an inner ring and an outer ring mounted between a bushing (61) for engaging on the axle with an outside wall shaped to receive the inner rings of the bearings, the bushing having one end (63) shaped as an abutment and another end shaped to receive a pre-loading nut (67); and a sleeve (62) extending around the bushing and having an inside wall presenting two shoulders to hold the outer rings of the bearings axially, the sleeve having an outer wall shaped to be received as a sliding fit in a bearing of the hub, with one end (68) shaped as an abutment and another end shaped to receive a stop nut (70).
    Type: Application
    Filed: August 24, 2017
    Publication date: March 1, 2018
    Applicant: SAFRAN LANDING SYSTEMS
    Inventors: Sylvain JABER, Vincent BELLENGER, Nicolas MORETTI, Gilles ELUARD
  • Publication number: 20180057152
    Abstract: An aircraft includes a float which provides buoyancy when the aircraft floats on a surface of water. The aircraft also includes a rotor where the rotor is configured to rotate in a horizontal plane and blow a wake across a side of the float. The rotor and the float are positioned relative to each other such that there is no aerodynamic separation between the wake blown by the rotor and the side of the float.
    Type: Application
    Filed: August 25, 2016
    Publication date: March 1, 2018
    Inventors: Todd Reichert, Cameron Robertson
  • Publication number: 20180057153
    Abstract: An aircraft with an emergency flotation system, the emergency flotation system being activated upon an emergency landing of the aircraft on water, for preventing at least sinking of the aircraft, characterized in that a capsizing avoidance buoyancy system is provided, the capsizing avoidance buoyancy system being activated if predetermined activation criteria are satisfied and only after activation of the emergency flotation system upon an emergency landing of the aircraft on water, for preventing at least capsizing of the aircraft.
    Type: Application
    Filed: July 27, 2017
    Publication date: March 1, 2018
    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Johann RAPPL
  • Publication number: 20180057154
    Abstract: An aircraft landing gear shock absorber assembly having an outer casing having a bore which extends through the outer casing. The bore has a first opening and a second opening. A rod is slidably coupled within the bore such that a first end of the rod projects out of the first opening of the bore, the first end of the rod being arranged to be attached to a wheel assembly. A closure is provided for the second opening of the bore. The bore has a reduced width portion relative to the second opening of the bore, and the rod includes a radially enlarged portion that is wider than the reduced width portion of the bore.
    Type: Application
    Filed: August 22, 2017
    Publication date: March 1, 2018
    Inventor: Robert Kyle Schmidt
  • Publication number: 20180057155
    Abstract: A multicopter aircraft with a wide span rotor configuration is disclosed. In various embodiments, a multicopter as disclosed herein includes a fuselage and a plurality of rotors. The plurality of rotors includes inner rotors and outer rotors, with the inner rotors being substantially surrounded by the outer rotors or the fuselage. The inner rotors and the outer rotors may be tilted based at least in part on their arrangement in relation to the fuselage.
    Type: Application
    Filed: August 26, 2016
    Publication date: March 1, 2018
    Inventors: Todd Reichert, Cameron Robertson
  • Publication number: 20180057156
    Abstract: An aircraft provided with a rotor that is provided with blades and a set of swashplates. The set of swashplates comprises both a rotary swashplate and also a non-rotary swashplate, a lower scissors linkage being hinged to the non-rotary swashplate and being hinged to a member that is stationary in rotation about the axis of rotation, the rotor comprising a plurality of servo-controls each provided with a top hinge hinged to a top attachment fitting of the non-rotary swashplate and with a bottom hinge hinged to a bottom attachment fitting that is stationary in a reference frame of the aircraft. For at least one servo-control referred to as the “inclined servo-control”, the bottom hinge is offset in azimuth about the axis of rotation relative to the top hinge.
    Type: Application
    Filed: August 30, 2017
    Publication date: March 1, 2018
    Applicant: AIRBUS HELICOPTERS
    Inventor: Alain STRUZIK
  • Publication number: 20180057157
    Abstract: In some embodiments, an aircraft includes a fuselage having a forward portion and an aft portion. First and second ducted fans are supported by the forward portion of the fuselage. The first and second ducted fans are tiltable relative to the fuselage between a generally horizontal orientation, in a vertical takeoff and landing mode, and a generally vertical orientation, in a forward flight mode. A tailboom having an aft station extends from the aft portion of the fuselage. A cross-flow fan is disposed in the aft station of the tailboom and is operable to generate a pitch control moment.
    Type: Application
    Filed: August 31, 2016
    Publication date: March 1, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Kirk Landon Groninga, Daniel Bryan Robertson
  • Publication number: 20180057158
    Abstract: A rotorcraft having a fuselage surmounted by a main rotor. The rotorcraft has a first propeller and a second propeller driven in rotation respectively about a first secondary axis of rotation and a second secondary axis of rotation. A mobility system turns the second propeller relative to the fuselage, the mobility system turning the second secondary axis of rotation relative to the fuselage from a first position where the second propeller exerts thrust in a first direction to a second position where the second propeller exerts thrust in a second direction opposite to the first direction.
    Type: Application
    Filed: August 11, 2017
    Publication date: March 1, 2018
    Applicant: AIRBUS HELICOPTERS
    Inventors: Michel VIALLE, Sylvain BERTHALON
  • Publication number: 20180057159
    Abstract: A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a generally vertical orientation in a vertical takeoff and landing mode and a generally horizontal orientation in a forward flight mode. The rotor assembly includes a proprotor operable to produce a generally vertical slipstream in the vertical takeoff and landing mode and a generally horizontal slipstream in the forward flight mode. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.
    Type: Application
    Filed: August 31, 2016
    Publication date: March 1, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Steven Ray Ivans, Nathan Gabriel Wu
  • Publication number: 20180057160
    Abstract: A tri-wing aircraft includes a fuselage having a longitudinally extending fuselage axis. Three wings extend generally radially outwardly from the fuselage axis and are circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals. The wings have airfoil cross-sections including first and second surfaces having chordwise channels therebetween. A distributed propulsion system includes a plurality of propulsion assemblies. Each propulsion assembly includes a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings. At least two variable thrust cross-flow fans are disposed within the chordwise channels of each of the wings. A flight control system is operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.
    Type: Application
    Filed: August 31, 2016
    Publication date: March 1, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Daniel Bryan Robertson, Kirk Landon Groninga
  • Publication number: 20180057161
    Abstract: A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of landing members. A pusher propeller extends from the tailboom assembly. In a vertical takeoff and landing mode, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode, rotation of the pusher propeller provides forward thrust and the first and second rotor assemblies are non-rotatable about the fuselage forming a dual wing configuration to provide lift.
    Type: Application
    Filed: August 30, 2016
    Publication date: March 1, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Kirk Landon Groninga, Daniel Bryan Robertson, Frank Bradley Stamps
  • Publication number: 20180057162
    Abstract: A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of landing members. In a vertical takeoff and landing mode of the aircraft, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode of the aircraft, the first rotor assembly rotates about the fuselage to provide forward thrust and the second rotor assembly is non-rotatable about the fuselage forming wings to provide lift.
    Type: Application
    Filed: August 30, 2016
    Publication date: March 1, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Daniel Bryan Robertson, Kirk Landon Groninga, Frank Bradley Stamps
  • Publication number: 20180057163
    Abstract: A vertical take-off and landing (“VTOL”) unmanned aerial vehicle (“UAV”) system and a method of controlling the same, wherein such method controls the stability and maneuverability of the VTOL UAV by manipulating the speeds of the propellers at each rotor. The VTOL UAV includes a body with three extending arms, wherein each of such arms is aligned and fixed at a certain angle from a central axis passing through the body. Each extending arm is equipped with a rotor with propellers. The rotors are sufficient to control the yaw of the UAV, and there is no need for coaxial rotors or an extra servo-motor in order to control the yaw of the UAV, thus reducing the cost and the weight of the UAV.
    Type: Application
    Filed: August 24, 2016
    Publication date: March 1, 2018
    Inventors: Belal Hussein Sababha, Hamzeh Mahmoud Alzu'bi, Osamah Ahmad Rawashdeh
  • Publication number: 20180057164
    Abstract: An unmanned aerial vehicle (UAV) including a vehicle body and an airflow thruster is provided. The vehicle body has a center hub, an airflow guiding structure and an outer circumferential portion. An interior of the airflow guiding structure is interconnected between the center hub and the outer circumferential portion. The center hub has an airflow inlet. The outer circumferential portion has a plurality of lateral guiding outlets facing downward and corresponding to a gravity direction of the gravity direction of the unmanned aerial vehicle. The airflow thruster is disposed inside the center hub for generating a plurality of jet streams, such that the jet streams flow to the lateral guiding outlets through the airflow guiding structure to generate a propulsion.
    Type: Application
    Filed: February 6, 2017
    Publication date: March 1, 2018
    Inventors: De-Zheng Lan, Shih-Chin Tseng, Shih-Kuang Tsai
  • Publication number: 20180057165
    Abstract: A system including an aerial vehicle having an airframe and a power source onboard the aerial vehicle, wherein the aerial vehicle includes a landing gear structure having a first electrical contact and a second electrical contact, and a charging station having a first electrical contact and a second electrical contact, wherein the aerial vehicle is programmed to dock with the charging station when the power source is in need of recharging, the docking being a mechanical engagement between the first electrical contact and the second electrical contact of the aerial vehicle with the first electrical contact and the second electrical contact of the charging station is provided. A method for continuous surveillance utilizing the aerial vehicles and charging stations is also provided.
    Type: Application
    Filed: October 30, 2017
    Publication date: March 1, 2018
    Inventor: Keith A. Raniere
  • Publication number: 20180057166
    Abstract: A pressure activated release system and method are disclosed for deployment of surface, aerial and subsea payloads. The system and method include a payload release switch that is activated, without human intervention, by a pressure differential. The system and method also includes a payload release mechanism having an unreleased configuration at pressures below a specified pressure. The release mechanism has a released configuration at pressures above the specified pressure. The switch causes the release mechanism to move from the unreleased configuration to the released configuration.
    Type: Application
    Filed: August 29, 2016
    Publication date: March 1, 2018
    Applicant: United States of America as represented by Secretary of the Navy
    Inventors: Jeffrey M. Lloyd, Brandon J. Wiedemeier
  • Publication number: 20180057167
    Abstract: Directed fragmentation of an unmanned aerial vehicle (UAV) is described. In one embodiment, the UAV includes various components, such one or more motors, batteries, sensors, a housing, casing or shell, and a payload for delivery. Additionally, the UAV includes a controller. The controller determines a flight path and controls a flight operation of the UAV. During the flight operation, the controller develops a release timing and a release location for one or more of the components based on the flight path, the flight conditions, and terrain topology information, among other factors. The controller can also detect a disruption in the flight operation of the UAV and, in response, direct fragmentation of one or more of the components apart from the UAV. In that way, a controlled, directed fragmentation of the UAV can be accomplished upon any disruption to the flight operation of the UAV.
    Type: Application
    Filed: October 25, 2017
    Publication date: March 1, 2018
    Inventors: Pragyana K. Mishra, Dushyant Goyal
  • Publication number: 20180057168
    Abstract: A vehicle cabin curtain rail attachment comprising a guiding rail configured to be mounted fixedly within a cabin and a movable curtain rail section to receive or guide a curtain, wherein the movable curtain rail section is configured to slide along the guiding rail to a desired position.
    Type: Application
    Filed: August 22, 2017
    Publication date: March 1, 2018
    Inventors: Boris HOLTORF, Gunter KYAS
  • Publication number: 20180057169
    Abstract: A stowable reversible seat for a vehicle includes a first member pivotally coupled to a floor for supporting a seat base, a second member releasably secured to the floor for supporting the seat base, and a seat back pivotally coupled to the first member. Components of the seat pivot between a folded configuration for stowing and a deployed configuration for seating. The orientation of the seat may be reversed for switching between a forward-facing direction and an aft-facing direction. A method of configuring a seat into an aircraft includes adapting a cabinet area to receive and conceal the seat, configuring a rail to make the seat slidable out from the cabinet area into an aisle, attaching a pivotable seat base on the seat, and pivotally mounting a supporting leg underneath a portion of the seat to secure the pivotable seat base in a substantially horizontal position.
    Type: Application
    Filed: August 29, 2017
    Publication date: March 1, 2018
    Inventor: Thang Chien Phi
  • Publication number: 20180057170
    Abstract: A method and aircraft for providing bleed air to environmental control systems of an aircraft using a gas turbine engine, including determining a bleed air demand for the environmental control systems, selectively supplying low pressure and high pressure bleed air to the environmental control systems, wherein the selectively supplying is controlled such that the conditioned air stream satisfies the determined bleed air demand.
    Type: Application
    Filed: August 23, 2016
    Publication date: March 1, 2018
    Inventor: Dominique Patrick Sautron
  • Publication number: 20180057171
    Abstract: A method and aircraft for providing bleed air to environmental control systems of an aircraft using a gas turbine engine, including determining a bleed air demand for the environmental control systems, selectively supplying low pressure and high pressure bleed air to the environmental control systems, wherein the selectively supplying is controlled such that the conditioned air stream satisfies the determined bleed air demand.
    Type: Application
    Filed: August 23, 2016
    Publication date: March 1, 2018
    Inventor: Dominique Patrick Sautron
  • Publication number: 20180057172
    Abstract: A method and aircraft for providing bleed air to environmental control systems of an aircraft using a gas turbine engine, including determining a bleed air demand for the environmental control systems, selectively supplying low pressure and high pressure bleed air to the environmental control systems, wherein the selectively supplying is controlled such that the conditioned air stream satisfies the determined bleed air demand.
    Type: Application
    Filed: August 23, 2016
    Publication date: March 1, 2018
    Inventor: Dominique Patrick Sautron
  • Publication number: 20180057173
    Abstract: A method and aircraft for providing bleed air to environmental control systems of an aircraft using a gas turbine engine, including determining a bleed air demand for the environmental control systems, proportionally supplying low pressure and high pressure bleed air to the environmental control systems, wherein the proportional supplying is controlled such that the conditioned air stream satisfies the determined bleed air demand.
    Type: Application
    Filed: August 23, 2016
    Publication date: March 1, 2018
    Inventor: Dominique Patrick Sautron
  • Publication number: 20180057174
    Abstract: An aircraft air conditioning system comprises an ambient air line configured to have ambient air flow therethrough and being connected to a mixer of the air conditioning system to feed ambient air to the mixer, and a recirculation air line configured to have recirculation air flow therethrough and being connected to the mixer to feed to the mixer recirculation air discharged from an aircraft area to be air conditioned. A refrigerating machine of the air conditioning system comprises a refrigerant circuit configured to have a refrigerant flow therethrough and being thermally coupled to the ambient air line and to the recirculation air line to transmit heat from the ambient air flowing through the ambient air line and from the recirculation air flowing through the recirculation air line to the refrigerant circulating in the refrigerant circuit, before the ambient air and the recirculation air are fed into the mixer.
    Type: Application
    Filed: October 23, 2017
    Publication date: March 1, 2018
    Inventors: Frank KLIMPEL, Hans BRUNSWIG, Steffen GOLLE, Ullrich HESSE, Enrico KLAUSNER, Mario RADDATZ
  • Publication number: 20180057175
    Abstract: An aircraft air conditioning system comprises an ambient air line which is configured have ambient air flow therethrough and is connected to a mixer of the aircraft air conditioning system to supply ambient air to the mixer, and a refrigerating machine which comprises a refrigerant circuit configured to have a refrigerant flow therethrough, the refrigerant circuit being thermally coupled to the ambient air line to transfer heat, from the ambient air flowing through the ambient air line, to the refrigerant circulating in the refrigerant circuit, before the ambient air is supplied into the mixer. A control device is configured to control the ambient air flow through the ambient air line such that the ambient air is selectively conducted through different sections of the ambient air line or different bypass lines running parallel to the sections of the ambient air line.
    Type: Application
    Filed: October 23, 2017
    Publication date: March 1, 2018
    Inventors: Frank KLIMPEL, Hans BRUNSWIG, Steffen GOLLE, Ullrich HESSE, Enrico KLAUSNER, Mario RADDATZ
  • Publication number: 20180057176
    Abstract: Composite airfoils of the present disclosure comprise a root section including a first surface. The airfoils comprise an intermediate section having a first surface and coupled with the root section at a first end. The airfoils comprise a tip section having a first surface and coupled at a first end with a second end of the intermediate section. The airfoils comprise a conductive material layer adjacent at least one of the first surface of the root section, the first surface of the intermediate section, and the first surface of the tip section. The conductive material comprises a first polymer, a second polymer, and a sulfonic acid.
    Type: Application
    Filed: August 30, 2016
    Publication date: March 1, 2018
    Inventors: Patrick J. KINLEN, Kenneth W. YOUNG
  • Publication number: 20180057177
    Abstract: Apparatuses for and methods of deicing aircraft surfaces, engine inlets, windmill blades and other structures. Deicing apparatuses can comprise at least one standoff coupled with an actuator and a first region of an inner surface of a skin. A standoff can act as a moment arm and can create efficient, tailorable skin bending and acceleration, breaking an ice to skin bond. Integral as well as modular leading edges can can comprise deicing apparatuses.
    Type: Application
    Filed: October 20, 2017
    Publication date: March 1, 2018
    Inventor: Peter Lenkey
  • Publication number: 20180057178
    Abstract: In some implementations, in an emergency in the vehicle, an emergency evacuation path is illuminated using the light emitted from the emergency evacuation rope where at least a portion of the emergency evacuation path extends to a location outside the vehicle. Egress of occupants along the emergency evacuation path is enabled using an emergency evacuation rope.
    Type: Application
    Filed: August 26, 2016
    Publication date: March 1, 2018
    Inventors: Daniel Frank Devitt, Michael Reaugh Smith
  • Publication number: 20180057179
    Abstract: An aircraft comprises at least first and second gas turbine engines arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine comprising at least one compressor or turbine rotor disc defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors of at least one of the engines is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine is nonintersecting with another engine.
    Type: Application
    Filed: October 25, 2017
    Publication date: March 1, 2018
    Applicant: ROLLS-ROYCE plc
    Inventor: Matthew MOXON
  • Publication number: 20180057180
    Abstract: One object is to provide a drone capable of achieving desired performance by preventing entry of foreign matter such as water droplets or dust particularly into a power portion thereof. A drone of the present invention is provided with a fixed section having a motor housing for housing a motor therein and a rotary section having a propeller shaft supported via a bearing so as to be rotatable with respect to the motor housing and configured to rotate integrally with the propeller. In an opposed portion where fixed-side components constituting the fixed section and rotary-side components constituting the rotary section are opposed to each other, there is provided a foreign matter entry prevention unit configured to prevent foreign matter from entering an inside of the motor housing.
    Type: Application
    Filed: August 29, 2017
    Publication date: March 1, 2018
    Inventors: Yutaro ABE, Hiromu YASUDA
  • Publication number: 20180057181
    Abstract: An aircraft is provided including a fuselage extending between a forward end and an aft end. An aft engine is mounted to the aft end of the fuselage and defines a centerline. The aft engine further includes a nacelle having a forward transition duct at the forward end of the nacelle. The forward transition duct also defines a centerline and the centerline of the forward transition duct is angled downward relative to the centerline of the aft engine.
    Type: Application
    Filed: August 24, 2016
    Publication date: March 1, 2018
    Inventors: Jixian Yao, Nikolai N. Pastouchenko, Ivan Malcevic
  • Publication number: 20180057182
    Abstract: An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft.
    Type: Application
    Filed: October 26, 2017
    Publication date: March 1, 2018
    Inventors: Patrick Michael Marrinan, Thomas Lee Becker, Kurt David Murrow, Jixian Yao
  • Publication number: 20180057183
    Abstract: A rotorcraft comprising a cowling for closing an opening in the fuselage, the cowling being linked to the fuselage by means of a fastening system having a supporting means pivotally attached to the interior of the fuselage and a translation means coupled to the supporting means to respectively enable movements of rotation and translation of the cowling.
    Type: Application
    Filed: August 23, 2016
    Publication date: March 1, 2018
    Inventors: Yann LE CADET, Christophe LETEURTRE
  • Publication number: 20180057184
    Abstract: Methods and apparatus to control thrust ramping of an aircraft engine are disclosed. An example thrust control system includes a sensor to measure a crosswind speed and a thrust manager to compare the measured crosswind speed to a crosswind threshold range. The thrust manager activates a partial thrust ramping schedule during takeoff when the measured crosswind speed is within the crosswind threshold range. The partial thrust ramping schedule is selected from a plurality of thrust ramping schedules.
    Type: Application
    Filed: August 31, 2016
    Publication date: March 1, 2018
    Inventors: Jason J. Jackowski, Kent E. Karnofski
  • Publication number: 20180057185
    Abstract: An unmanned aerial vehicle has an internal combustion engine, and a fuel and lubrication system comprising a fuelling system for fuelling the engine and a lubrication system for delivering lubricating oil to the engine. The fuelling system comprises a fuel reservoir from which fuel can be delivered to the engine. The fuel reservoir comprises a main tank and a header tank. The lubrication system comprises an oil tank. The oil tank is accommodated internally within the main tank to provide an integrated assembly. The arrangement provides for warming of lubrication oil for the UAV engine using several available heat sources. Further, the arrangement facilitates a configuration and layout intended to minimise or negate any undesirable moments of inertia for the UAV during flight as fuel and oil is consumed.
    Type: Application
    Filed: February 19, 2016
    Publication date: March 1, 2018
    Applicant: ORBITAL AUSTRALIA PTY LTD
    Inventors: Geoffrey Paul CATHCART, Stephen John KARAY, Nicholas COPLIN, John Howard TUBB, Callan Murray BLEECHMORE, Donald Andrew RAILTON, Mario Charles MUSCAT
  • Publication number: 20180057186
    Abstract: A toggle assembly includes a first joint member having a first lug and a second lug, a second joint member, and a third joint member. The second joint member has a first arm that receives a first rolling element, a second arm that receives a second rolling element, a third arm, and a fourth arm. The second joint member is pivotally connected to the first joint member via a first pin that extends through the first lug, the first rolling element, the second rolling element, and the second lug. The third joint member has a third lug and a fourth lug disposed opposite the third lug. The third joint member is pivotally connected to the second joint member via a cross rod pin that extends through the third lug, the third arm and the fourth arm.
    Type: Application
    Filed: October 19, 2017
    Publication date: March 1, 2018
    Inventors: Stephen Michael Bortoli, Gary Sasscer
  • Publication number: 20180057187
    Abstract: A yaw feedback system for use by an aircraft is provided. The yaw feedback system includes a processor, a runway centerline indicator, and a yaw feedback indicator. The processor is configured to determine a yaw difference between a current track of the aircraft and a runway centerline. The runway centerline indicator is configured to virtually extend a runway visual range (RVR) for a pilot of the aircraft. The yaw feedback indicator is coupled to the processor and configured to prompt the pilot for a yaw input to compensate for the yaw difference.
    Type: Application
    Filed: August 31, 2016
    Publication date: March 1, 2018
    Inventors: Samantha Schwartz, Katie M. Reid
  • Publication number: 20180057188
    Abstract: A tool assembly includes a support frame including support beams and support mounts supporting the support beams. The support frame is rigid and used to transport the tool assembly. A support tool is supported by the support frame and includes a faceplate and a supporting grid structure formed with the faceplate as a monolithic structure defined by a series of AM layers. The faceplate has a supporting surface at a top of the support tool for supporting a working component. The supporting grid structure engages the support beams such that loads are transferred between the support tool and the support frame through the support beams. The support frame maintains dimensional stability of the support tool during transport and when resting within an allowable tolerance of the support tool.
    Type: Application
    Filed: October 21, 2016
    Publication date: March 1, 2018
    Applicant: THE BOEING COMPANY
    Inventors: Eric Eldon Deck, Michael Palmore Matlack
  • Publication number: 20180057189
    Abstract: Described herein is a thrust system for a vehicle that includes at least three electrical power controllers, at least four electrical switches each configured to receive electrical power from at least one of the at least three electrical power controllers, and at least three thrusters each configured to receive electrical power from at least one of the at least three electrical switches. The at least four electrical switches are operable to switch a supply of electrical power from any of the at least three electrical power controllers to any one of the at least three thrusters.
    Type: Application
    Filed: November 3, 2017
    Publication date: March 1, 2018
    Inventors: John F. Stickelmaier, Julie M. Perkins, Kurt B. Kreiner, Philip D. Nguyen
  • Publication number: 20180057190
    Abstract: An insulation panel includes a face sheet hermetically coupled to a plurality of structural walls to define a plurality of cell bodies, with each cell body positioned contiguously with an adjacent cell body. An insulation structure is disposed within each cell body and further includes a first radiant barrier layer, a second radiant barrier layer, and a spacer disposed between the first radiant barrier layer and the second radiant barrier layer. Sealed cells formed by completing the cell bodies may contain a gas that condenses or freezes in response to cryogenic cooling of a structure to which the insulation panel is coupled. Load-responsive spacers may also be disposed between the insulation structure and the face sheet to support the face sheet while in atmospheric conditions and to disengage from the face sheet in low pressure environments, such as space.
    Type: Application
    Filed: August 30, 2017
    Publication date: March 1, 2018
    Applicant: Quest Thermal Group LLC
    Inventors: Scott A. Dye, Phillip N. Tyler, Alan B. Kopelove
  • Publication number: 20180057191
    Abstract: Disclosed are the thermal protection and drag reduction method and system for an ultra high-speed aircraft. A cold source is and a cold source driving device are arranged inside a cavity of the ultra high-speed aircraft. A plurality of micropores are arranged on a wall surface of the cavity. The cold source driving device comprises an air pump, a cold source reservoir and a buffer. The air pump supplies compressed air to a cold source reservoir during operation. The cold source enters the buffer and is vaporized under the action of air pressure. High-pressure gas is ejected from the micropores to form a gas film on the outer surface of the cavity. The gas film not only can perform thermal protection on the ultra high-speed aircraft, but also can effectively reduce viscous drag between the aircraft and the external gas, by virtue of which the thermal barrier phenomenon is alleviated or eliminated. Therefore, security of the ultra high-speed aircraft is improved and service life is prolonged.
    Type: Application
    Filed: February 6, 2016
    Publication date: March 1, 2018
    Inventors: Wenwu ZHANG, Shuhong XIANG, Chunhai GUO, Jingyu TONG, Tianrun ZHANG, Yang YANG, Tao SONG
  • Publication number: 20180057192
    Abstract: A stand-off panel thermal protection system is disclosed. The system comprises a sandwich panel comprising: a first ceramic matrix composite facesheet and a second ceramic matrix composite facesheet. A ceramic matrix composite core is positioned between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet. The ceramic matrix composite core has a perimeter. The first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet extend past the perimeter to form a gap between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet surrounding the ceramic matrix composite core. A plurality of orifices are formed through the sandwich panel.
    Type: Application
    Filed: November 3, 2017
    Publication date: March 1, 2018
    Inventors: Michael J. BEST, Thomas R. PINNEY, Jonathan D. EMBLER
  • Publication number: 20180057193
    Abstract: A simulated gravity device method and apparatus is presented. The simulated gravity device (SGD) is disposed in mechanical communication with a spacecraft. The SGD is rotatable about a central axis, and is capable of supporting a person therein. The SGD is rotatable at a speed resulting in various forces, said various forces dependent on a rotation speed of said SGD and on a position within said SGD. The SGD is able to simulate the force of gravity on an astronaut.
    Type: Application
    Filed: August 17, 2017
    Publication date: March 1, 2018
    Inventor: David Byron Douglas
  • Publication number: 20180057194
    Abstract: An apparatus for dispensing lids has at least one magazine lane including an entrance end, an exit end, and a longitudinal length defined therebetween. The at least one magazine lane further includes a plurality of side guides along the longitudinal length for guiding the lids therebetween and a pair of rollers for carrying the lids thereon. The apparatus further has a throat plate at or near the exit end, the throat plate including an opening. At least one of the throat plate, the side guides, or the rollers is adaptable so as to accommodate different sizes and/or shapes of lids.
    Type: Application
    Filed: August 9, 2017
    Publication date: March 1, 2018
    Inventors: Wade Joseph Burken, Donald Brooks MacKinnon, Daniel Leonard Matthies, Jeffrey David Wintring
  • Publication number: 20180057195
    Abstract: The packet for providing nutrients to a person is disclosed. The packet may be inserted into a bottle of water at which time, a film of the packet begins to dissolve and allow the water to seep into the packet. When the water seeps into the packet, the water dissolves the film from the inside out so that the film dissolves from the outside in and inside out to reduce the time required to completely dissolve the film. Moreover, the bottle of water can be closed so that the user can shake the bottle of water and allow the powdered nutrient in the packet to rub against the film and further reduce the time required to completely dissolve the film and also dispersed the powdered nutrient in the water. The powdered nutrient may have a rate of dissolution that is slower than the film so that the powdered nutrient can run and cause friction against the film throughout the entire period of time water bottle was shaken.
    Type: Application
    Filed: May 30, 2017
    Publication date: March 1, 2018
    Inventor: Nicholas J. Singer
  • Publication number: 20180057196
    Abstract: A tray (100) for accommodating a coiled medical device, such as a catheter assembly (700), includes a first compartment (101), a second compartment (102), and a third compartment (103). The catheter assembly (700) and devices associated with a catheterization procedure, such as syringes (701,702) containing sterile water and lubricating jelly and a specimen container (703) can be disposed within the tray. Printed instructions (1001) can be included with the tray (100). One or more layers of wrap material (2200) can be folded about the tray (100) to enclose the tray (100) and other items, such as an additional layer of wrap material (2701), packaged liquid hand sanitizer (2401), and packaged gloves (2402). When a health care services provider (3101) unfolds the wrap material, the same can be used to create a sterile field beneath a patient (3201).
    Type: Application
    Filed: November 3, 2017
    Publication date: March 1, 2018
    Inventors: Jennifer E. Tomes, Sarah Dickinson, Deborah Adler, Jack Maze, Alberto Savage, Kenneth Chua, Earl Wilson, John Kutsch
  • Publication number: 20180057197
    Abstract: A packaging device (2) and a packaging method are for highly compressed bales (3) on a baling press (1). The packaging device (2) has a supply device (9) for a web-shaped packaging material (8) and a wrapping device (10) for attaching an annularly surrounding wrapping web (7) on the free side surfaces (32) of the compressed bale (3) which is held between compression rams (31). The wrapping device (10) is arranged with a transport device (20) movably relative to the compressed bale (3). The supply device (9) is arranged in a spatially and kinematically separate manner from the wrapping device (10), in particular in a stationary manner.
    Type: Application
    Filed: March 26, 2014
    Publication date: March 1, 2018
    Applicant: AUTEFA SOLUTIONS GERMANY GMBH
    Inventors: Norbert SAUERWEIN, Jan SCHNEIDER