Patents Issued in January 4, 2018
  • Publication number: 20180002001
    Abstract: Disclosed herein is a water helicopter includes a fuselage, first and second fixed wings extending outwardly from left and right ends of the fuselage, first and second propellers disposed in a spaced apart configuration on a top surface of the fuselage, and a landing and float gear attached to a bottom surface of the fuselage for enabling landing of the water helicopter on water.
    Type: Application
    Filed: June 30, 2016
    Publication date: January 4, 2018
    Inventor: Carter L Daniel, SR.
  • Publication number: 20180002002
    Abstract: A rotor assembly for use with rotor blades and a drive shaft includes a one-piece molded rotor hub having a central hub and a plurality of hollow spindles integrally molded with and extending radially outwardly of the central hub to which rotor blades are attachable. The central hub includes a hollow interior that is receptive to a drive shaft configured to rotate the one-piece molded rotor hub.
    Type: Application
    Filed: December 12, 2016
    Publication date: January 4, 2018
    Inventors: BRYAN KENNETH BASKIN, RON WILLIAM WALDO
  • Publication number: 20180002003
    Abstract: Systems, devices, and methods for an aircraft having a fuselage (110); a wing (120) extending from both sides of the fuselage; a first pair of motors (132b, 133b) disposed at a first end of the wing; and a second pair of motors (142b, 143b) disposed at a second end of the wing; where each motor is angled (381, 382, 391, 392) to provide a component of thrust by a propeller (134, 135, 144, 145) attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.
    Type: Application
    Filed: June 2, 2017
    Publication date: January 4, 2018
    Inventors: Henry Thome Won, Quentin Lindsey
  • Publication number: 20180002004
    Abstract: A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle.
    Type: Application
    Filed: August 11, 2017
    Publication date: January 4, 2018
    Inventors: Guy DEKEL, Lior ZIVAN, Yoav EFRATY, Amit WOLFF, Avner VOLOVICK
  • Publication number: 20180002005
    Abstract: A helicopter with a rotor pivotally connected to a shaft by a universal joint or ball and socket joint. The helicopter includes: a fuselage; a rotor mast that is fixed against relative rotation with respect to the fuselage; at least one blade; a motor for rotating the at least one blade; and a universal joint or ball and socket joint. The universal joint or ball and socket joint: (i) is disposed between the at least one blade and the rotor mast, with the at least one blade being rotatable relative to the universal joint or ball and socket joint; (ii) is disposed between the motor and the rotor mast; and (iii) is fixed against relative rotation with respect to the rotor mast, such that, pivoting of the universal joint or ball and socket joint causes the at least one blade and the motor to tilt.
    Type: Application
    Filed: January 13, 2016
    Publication date: January 4, 2018
    Inventor: Felix Errol Groenewald
  • Publication number: 20180002006
    Abstract: A rotor comprising a hub and a plurality of lift assemblies. Each lift assembly is connected to two adjacent lift assemblies respectively by a first damper and a second damper. The first damper is hinged to a lift assembly about a first axis, and the second damper is hinged to said lift assembly about a second axis. A first plane contains a lead-lag axis of the lift assembly and orthogonally to the pitch axis of the lift assembly. The first axis is situated in a volume lying between the first plane and an axis of rotation of the rotor, the second axis being positioned outside said volume.
    Type: Application
    Filed: June 27, 2017
    Publication date: January 4, 2018
    Applicant: AIRBUS HELICOPTERS
    Inventors: Olivier HONNORAT, Jean-Pierre JALAGUIER
  • Publication number: 20180002007
    Abstract: The present invention relates to A device for supplying hydraulic power, the device comprising two hydraulic circuits jointly feeding multi-cylinder hydraulic power transmission means in which each cylinder is connected to a single one of the hydraulic circuits independently of the others. Each hydraulic circuit includes a hydraulic pressure and flow rate generator and a pressure control module controlling said hydraulic pressure and flow rate generator so as to regulate the pressure of said fluid flowing in said hydraulic circuit as a function of said pressure of said fluid flowing in each hydraulic circuit and possibly as a function of one or more parameters external to said device.
    Type: Application
    Filed: June 22, 2017
    Publication date: January 4, 2018
    Applicant: AIRBUS HELICOPTERS
    Inventors: Pascal LEGUAY, Jean-Yves AGRESTA, Arnaud GROLL
  • Publication number: 20180002008
    Abstract: The present invention discloses a rotor control system where rapid changes in rotor torque are transferred into moment forces acting about the blade pitch axis of a rotor blade in a thrust-generating rotor, to ultimately control the movements of a rotary wing aircraft. The moment forces acting on the rotor blade are transferred through a carefully adjusted damping member in order to allow rapid changes in rotor torque to create cyclic changes in blade pitch angle, while slow or permanent changes are cancelled out and affects the rotational speed and the thrust generated by the rotor, without permanently affecting the blade pitch angle of individual rotor blades.
    Type: Application
    Filed: January 20, 2016
    Publication date: January 4, 2018
    Inventors: Petter Muren, Trygve Frederik Marton, Ivar Johnsrud, Päl Hagh Sandberg
  • Publication number: 20180002009
    Abstract: In some embodiments, a propulsion assembly for an aircraft includes a nacelle, at least one self-contained fuel tank disposed within the nacelle operable to contain a liquid fuel, an engine disposed within the nacelle operable to run on the liquid fuel, a drive system mechanically coupled to the engine and operable to rotate responsive to rotation of the engine, a rotor hub mechanically coupled to the drive system operable to rotate responsive to rotation of the drive system and a proprotor mechanically coupled to the rotor hub and operable to rotate therewith.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Publication number: 20180002010
    Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for an unmanned aerial system inspection system. One of the methods is performed by a UAV and includes obtaining, from a user device, flight operation information describing an inspection of a vertical structure to be performed, the flight operation information including locations of one or more safe locations for vertical inspection. A location of the UAV is determined to correspond to a first safe location for vertical inspection. A first inspection of the structure is performed is performed at the first safe location, the first inspection including activating cameras. A second safe location is traveled to, and a second inspection of the structure is performed. Information associated with the inspection is provided to the user device.
    Type: Application
    Filed: June 29, 2017
    Publication date: January 4, 2018
    Inventors: Mark Patrick Bauer, Bernard J. Michini, Brett Michael Bethke
  • Publication number: 20180002011
    Abstract: In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Publication number: 20180002012
    Abstract: In some embodiments, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, a flight control system operably associated with the distributed propulsion system and a pod assembly selectively attachable to the flying frame. The distributed propulsion system includes a plurality of propulsion assemblies that are independently controlled by the flight control system, thereby enabling the flying frame to have a vertical takeoff and landing mode and a forward flight mode.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Publication number: 20180002013
    Abstract: In some embodiment, an aircraft includes an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system. A pod assembly is selectively attachable to the flying frame. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flying frame has a manned flight mode and an unmanned flight mode.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Publication number: 20180002014
    Abstract: In some embodiments, an aircraft includes a flying frame having an airframe with first and second wing members having a plurality of pylons extending therebetween, a distributed propulsion system including a plurality of propulsion assemblies securably attached to the airframe and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode with the wing members disposed in generally the same horizontal plane and a forward flight mode with the wing members disposed in generally the same vertical plane.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Publication number: 20180002015
    Abstract: In some embodiments, a transportation method includes coupling a flying frame to a passenger pod assembly; lifting the passenger pod assembly into the air in a vertical takeoff and landing mode with the passenger pod assembly in a generally horizontal attitude; transitioning from the vertical takeoff and landing mode to a forward flight mode by rotating the flying frame relative to the passenger pod assembly, which remains in the generally horizontal attitude; transporting the passenger pod assembly toward a second location in the forward flight mode; transitioning the flying frame from the forward flight mode to the vertical takeoff and landing mode by rotating the flying frame relative to the passenger pod assembly, which remains in the generally horizontal attitude; landing the flying frame at the second location in the vertical takeoff and landing mode; and releasing the passenger pod assembly.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Publication number: 20180002016
    Abstract: In some embodiments, a passenger pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a passenger pod assembly having a current location and a destination; upload a flight plan to a flight control system of a flying frame including an airframe and a propulsion system; dispatch the flying frame to the current location of the passenger pod assembly; couple the flying frame to the passenger pod assembly at the current location of the passenger pod assembly; transport the passenger pod assembly by air from the current location of the passenger pod assembly to the destination of the passenger pod assembly; and decouple the passenger pod assembly from the flying frame at the destination of the passenger pod assembly.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Publication number: 20180002017
    Abstract: An unmanned aircraft system includes a testing and calibration system that enables automated testing of movable parts of an unmanned aircraft. The testing and calibration system uses a camera-based technique to determine the position and angle of movable parts, in order to establish whether or not those parts are moving in a manner consistent with correct function.
    Type: Application
    Filed: August 4, 2016
    Publication date: January 4, 2018
    Inventors: Peter Abeles, Keenan Wyrobek
  • Publication number: 20180002018
    Abstract: A method for navigating an airborne device relative to a target comprises detecting, at an optical detector on the airborne device, an optical signal generated by one or more LEDs on the target. The method also comprises comparing, by a processor on the airborne device, the detected optical signal with a previously-detected optical signal. The method further comprises determining, by the processor based on the comparison, a change in location of at least one of the airborne device or the target. The method also comprises adjusting a position of the airborne device based on the determined change in location. The method also comprises predicting, by the processor, a movement of the target based on information indicative of at least one of a position, a rotation, an orientation, an acceleration, a velocity, or an altitude of the target, wherein the position of the airborne device is adjusted based on the predicted movement of the target.
    Type: Application
    Filed: August 24, 2017
    Publication date: January 4, 2018
    Inventor: Damien Bruno Jourdan
  • Publication number: 20180002019
    Abstract: A water scooping apparatus for an aircraft comprising an extendible tubular member having a first end and an opposite end, wherein the first end is pivotally attached to the aircraft, a duct for fluidly connecting the extendible tubular member at the first end to a water tank, a floater connected to the opposite end of the extendible tubular member, wherein the floater is provided with an intake opening for taking in water; wherein the intake opening is fluidly connected to the extendible tubular member; wherein the water scooping apparatus is operable between a resting position in which the extendible tubular member is substantially retracted, and an operating position in which the extendible tubular member extends downwards from the aircraft at an angle.
    Type: Application
    Filed: January 12, 2016
    Publication date: January 4, 2018
    Inventor: Jack BENEDIK
  • Publication number: 20180002020
    Abstract: A frame member, a monument for a vehicle, and a vehicle are provided. The frame member includes an extrusion that has a spar with first and second opposing surfaces and first and second opposing ends. The spar includes a first retention lip extending from the first planar surface along the first end at an acute angle relative to the first planar surface. The spar includes a rub strip protrusion extending from the first planar surface between the first and second ends. The rub strip protrusion includes a third end and a second retention lip extending from a third surface facing the first retention lip. The second retention lip and the third surface form an acute angle. The extrusion also includes at least two panel protrusions extending from the second planar surface of the spar. A rub strip can include retention tabs with outward-facing notches that engage the first and second retention lips.
    Type: Application
    Filed: June 30, 2016
    Publication date: January 4, 2018
    Inventors: Sougand TALEBPOUR, Roland MAIR, Russell W. KECK, Tomas ARMENTA, Paul T. BRIDGEMAN, Franco M. CAGNINA
  • Publication number: 20180002021
    Abstract: A head support apparatus is provided for supporting a person's head while sitting in an airplane seat. The apparatus comprises a strap member for encircling around the back of a seat while retaining the user's head. The strap can be made adjustable and stretchable to accommodate the size of the person's head and to provide an appropriate level of snugness. The head support apparatus may provide a sleep mask element.
    Type: Application
    Filed: June 28, 2017
    Publication date: January 4, 2018
    Inventor: Osborne E. Smith
  • Publication number: 20180002022
    Abstract: Various embodiments provide a method for installing a seat suspension on a seat frame having a first side frame member and a second side frame member opposed to and spaced apart from each other. The method may include moving a retainer on a first side of the seat suspension in a direction substantially perpendicular to a plane defined by the first and second side frame members for fastening onto a support member on the first side frame member; and moving a retainer on a second side of the seat suspension in the direction substantially perpendicular to the plane defined by the first and second side frame members for fastening onto a support member on the second side frame member. The second side of the seat suspension is opposed to and spaced apart from the first side of the seat suspension.
    Type: Application
    Filed: December 31, 2014
    Publication date: January 4, 2018
    Inventors: Siang Ann CHENG, Guo Ying ZHENG
  • Publication number: 20180002023
    Abstract: The present invention disclosed a cooling system for unmanned aerial vehicle, which includes a main body, four arms disposed on the main body, two clockwise rotating propellers and two counterclockwise rotating propellers disposed on the arms respectively; wherein at least one air guide hole on each of the arms, which guide air to a middle of the main body; the two clockwise rotating propellers are disposed diagonally and the two counterclockwise rotating propellers are disposed diagonally; a clockwise rotating propeller is on a left-front arm; each of the clockwise and the counterclockwise rotating propellers rotates to generate an airstream which is configured to sweep towards the arm, the airstreams are configured to flow to an internal part of the main body by the air guide hole. The cooling system is able to cool down the whole unmanned aerial vehicle.
    Type: Application
    Filed: September 14, 2017
    Publication date: January 4, 2018
    Inventors: Yu Tian, Wenyan Jiang
  • Publication number: 20180002024
    Abstract: A structural element of a means of transport comprising a resistive heater for defrosting operations, wherein the resistor has conduction terminals coupled to respective terminals of a voltage generator adapted to cause a current flux through the resistor. The resistor includes one or more conductive paths of partially reduced graphene oxide or partially oxidized graphene configured to generate, when travelled by the current flux, heat by Joule effect.
    Type: Application
    Filed: July 3, 2017
    Publication date: January 4, 2018
    Applicant: Leonardo S.p.A.
    Inventors: Antonio Brelati, Rosario Del Giudice, Ida Ricco, Francesco Nonis
  • Publication number: 20180002025
    Abstract: A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, and a turbine section with a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. An electric motor is connected to the first shaft such that rotational energy generated by the electric motor is translated to the first shaft. An electric energy storage component is electrically connected to the electric motor, and electrically connected to at least one aircraft taxiing system. The gas turbine engine is configured such that the gas turbine engine requires supplemental power from the electric motor during at least one mode of operations.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Inventors: Charles E. Lents, Larry W. Hardin, Jonathan Rheaume
  • Publication number: 20180002026
    Abstract: An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.
    Type: Application
    Filed: May 26, 2017
    Publication date: January 4, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Paul K. Oldroyd, John Richard McCullough
  • Publication number: 20180002027
    Abstract: In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Publication number: 20180002028
    Abstract: A control system may be used to control actuators that actuate movement of flight control surfaces of an aircraft. Each actuator is couplable to a flight control surface and includes a motion control assembly having a hydraulic motor and a drive path from the hydraulic motor to the flight control surface. Each hydraulic motor includes an extend port and a retract port. The system includes a hydraulic control module fluidly connected to the extend port and the retract port of each hydraulic motor and a controller operable to output hydraulic power from the hydraulic control module to the motion control assembly to actuate movement of the flight control surfaces. The controller is configured to identify an actuator that positionally leads the other actuators and reduce hydraulic power to the motion control assembly assigned to such actuator.
    Type: Application
    Filed: June 5, 2017
    Publication date: January 4, 2018
    Inventor: Eric Alexander Polcuch
  • Publication number: 20180002029
    Abstract: This disclosure relates to a support device for an actuator. The support device includes a support unit adapted to be mounted to a stationary structure, an attachment unit adapted to be attached to an actuator casing and a single pivot shaft, and the attachment unit is pivotably connected to the support unit via the single pivot shaft. The support device according to the present disclosure has a simple structure and is stable in operation. The present disclosure further relates to an air intake system for an auxiliary power unit, which includes the above support device for the actuator. In addition, the present disclosure further relates to an aircraft including the air intake system for the auxiliary power unit.
    Type: Application
    Filed: June 22, 2017
    Publication date: January 4, 2018
    Inventors: Feng ZHANG, Na SHI, Ying AN
  • Publication number: 20180002030
    Abstract: Embodiments of the present disclosure relate generally to the use of the fuel cell systems on board aircraft and other passenger transportation vehicles and to methods of using heat, air, and water generated by such fuel cell systems. The heat may be used to address condensation within the aircraft. The heat may be used to help evaporate excess water that would otherwise condense in the aircraft skin. The excess water collected may be used to create humidification for cabin air. In other examples, the heat, warmed air, or warmed water may be delivered to other locations or heating systems for beneficial use.
    Type: Application
    Filed: January 22, 2016
    Publication date: January 4, 2018
    Applicant: Zodiac Aerotechnics
    Inventors: Samuel Klassen, Franck Masset, Andreas Hoogeveen, Hanane Zraaia, Loic Bouillo, Christian Thiry, Guillaume Gager, Charles Foncin, Jakub Landa, Remko Schiphorst
  • Publication number: 20180002031
    Abstract: A ram air turbine actuator having: a housing; at least one solenoid; a latch mechanism operably connected to the at least one solenoid and located within the housing, the latch mechanism in operation moves from a first position to second position when the at least one solenoid is activated; and a hydraulic pressure system operably connected to the latch mechanism, the hydraulic pressure system in operation moves the latch mechanism from the second position to the first position using hydraulic pressure from a hydraulic fluid, when the at least one solenoid is deactivated. The hydraulic pressure system is located within the housing. The hydraulic pressure is relieved when the latch mechanism is in the first position.
    Type: Application
    Filed: June 30, 2016
    Publication date: January 4, 2018
    Inventor: Timothy Scott Konicek
  • Publication number: 20180002032
    Abstract: The present invention relates to A power margin indicator device constituting a first limitation indicator for a rotorcraft, for providing a pilot of said rotorcraft with information about a power margin available on at least one engine and a main power transmission gearbox of said rotorcraft as a function of flying conditions, said device comprising: input means for collecting input data corresponding various operating parameters of said at least one engine and of said MGB; calculation means connected to said input means, said calculation means serving to determine a collective pitch margin for the blades of a rotor of said rotorcraft; and display means presenting said collective pitch margin.
    Type: Application
    Filed: June 28, 2017
    Publication date: January 4, 2018
    Applicant: AIRBUS HELICOPTERS
    Inventors: Gregory ABBAS, Damien GAVIOS
  • Publication number: 20180002033
    Abstract: A method for making an electroluminescent marking on an exterior wall of an aircraft, including a step of superpositioning of layers designed or configured to produce the electroluminescent marking on a first face of a flexible backing distinct from the aircraft to obtain a marking tape and a step of affixing the marking tape to the exterior wall of the aircraft. The disclosure herein also concerns a marking tape for the implementing of the method, a marking device obtained from the method, and an aircraft comprising the marking device.
    Type: Application
    Filed: June 29, 2017
    Publication date: January 4, 2018
    Inventors: Vincent LOUBIERE, Alix COURTADON, Matthew TRINGHAM
  • Publication number: 20180002034
    Abstract: The present invention is an aircraft lighting system. In particular, the present invention is directed to an aircraft lighting system with light that is directed toward an aircraft's engines to deter bird strikes. The lighting system for a jet-powered aircraft has at least one light mounted on an aircraft fuselage aimed at an engine inlet of an engine nacelle of the aircraft. The illumination from the light comprises ultraviolet light between 300 and 400 nm in wavelength and the light flashes at a pre-determined frequency preferably between 1 and 3 Hz. Additional lights can be mounted on the engine nacelles to illuminate outer engine nacelles. Preferably, the engine of the aircraft also has blades coated in fluorescent or iridescent paint to increase the reflectivity of the blades to further illuminate the blades of the engine. The lighting system preferably automatically illuminates the engine inlets during take-off and descent.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Inventor: Maurice A. Khawam
  • Publication number: 20180002035
    Abstract: A self-stabilizing spherical unmanned aerial vehicle (UAV) camera assembly, including: a stabilizer assembly; a plurality of motors coupled to the stabilizer assembly; a spherical camera mounting cage assembly disposed about and coupled to the stabilizer assembly; and a plurality of cameras coupled to the spherical camera mounting cage assembly. Preferably, the plurality of cameras include a plurality of stereoscopic cameras coupled to an exterior of the spherical camera mounting cage assembly. The self-stabilizing spherical UAV camera assembly is capable of taking/recording 360 degree×180 degree stereoscopic photo/video content. The self-stabilizing spherical UAV camera assembly can also be used with various real-time visualization and control technologies.
    Type: Application
    Filed: October 10, 2016
    Publication date: January 4, 2018
    Inventor: Carl Michael NEELY
  • Publication number: 20180002036
    Abstract: An obstacle avoidance device for detecting surroundings of an unmanned mobile device is disclosed, which includes a stabilization platform connected with the unmanned mobile device, wherein the stabilization platform includes a stabilizer for ensuring stably bearing at least one platform camera; and an obstacle avoidance module fixed with the stabilization platform, so as to reduce interferences to detecting the surroundings by the obstacle avoidance module when the unmanned mobile device acts. The obstacle avoidance device of the present invention is able to keep a stable attitude while the unmanned mobile device is unstable and changes an attitude thereof, so as to effectively avoid obstacles.
    Type: Application
    Filed: September 14, 2017
    Publication date: January 4, 2018
    Inventors: Yu Tian, Wenyan Jiang
  • Publication number: 20180002037
    Abstract: An integrated mobile ground support system 10 includes a wheeled cart 12 on which is mounted a power plant 14 to power an air compressor 16 to provide bleed air to an aircraft. The power plant 14 also powers an electrical generator 22, the output of which is controlled and converted to AC and/or DC power to meet the power requirements of the aircraft. An air conditioning unit 20 is also mounted on the cart 12 for providing conditioned air to the aircraft.
    Type: Application
    Filed: June 29, 2016
    Publication date: January 4, 2018
    Applicant: John Bean Technologies Corporation
    Inventors: Steven U. Nestel, Scott B. Gwilliam, Pete James Menke, Brent Andrew Carlson, Randall A. Melancon, Krzysztof Kubica
  • Publication number: 20180002038
    Abstract: A method of making a rotor blade assembly includes receiving a sheath assembly and a blade body at a blade assembly tool. The sheath assembly is spread by applying force to an interior surface of the sheath assembly. The blade body is inserted within the interior of the sheath assembly, registered with the sheath assembly, and the force removed from the interior surface of the sheath assembly such that the sheath assembly collapses on the blade body.
    Type: Application
    Filed: June 30, 2016
    Publication date: January 4, 2018
    Inventors: David Littlejohn, Sven Roy Lofstrom, Eric C. Boyle
  • Publication number: 20180002039
    Abstract: A system and method of detecting damage to a component may include a first sensor and a processor. The method may include the steps of receiving, by the processor, a first data for the component from a first sensor, aligning, by the processor, the first data with a reference model, determining, by the processor, a feature dissimilarity between the first data and the reference model, classifying, by the processor, the feature dissimilarity, and determining, by the processor, a probability that the feature dissimilarity indicates damage to the component.
    Type: Application
    Filed: July 1, 2016
    Publication date: January 4, 2018
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Alan Matthew Finn, Srinivas Ravela, Joseph A. Sylvestro
  • Publication number: 20180002040
    Abstract: Systems and methods for recording and communicating engine data are provided. One example embodiment is directed to a method for testing communications. The method includes receiving a message via a data load protocol. The method includes initiating a connectivity test, in response to the received message. When the connectivity test fails, the method includes transmitting a failure signal associated with the data load protocol. When the connectivity test passes, the method includes transmitting a success signal associated with the data load protocol.
    Type: Application
    Filed: June 26, 2017
    Publication date: January 4, 2018
    Inventors: Richard John Reiffer, JR., Michael Clay Scholten
  • Publication number: 20180002041
    Abstract: Functional components of spacecraft structures can be subject to detrimental impacts by energetic particles produced from an electric propulsion system. A graphene coating applied to a functional component can maintain electrical conductivity upon a surface of the functional component, thereby allowing charge dissipation to take place, while also resisting sputtering erosion resulting from impacts of the energetic particles. Accordingly, spacecraft structures can include an electric propulsion system, a functional component that is at least partially impacted by an outflow of the electric propulsion system, and a graphene coating upon the functional component. Methods for operating such spacecraft structures can include generating an outflow of energetic particles from an electric propulsion system of a spacecraft structure, and at least partially impacting the outflow of energetic particles upon a functional component of the spacecraft structure, where the functional component has a graphene coating thereon.
    Type: Application
    Filed: June 29, 2016
    Publication date: January 4, 2018
    Inventors: Vadim KHAYMS, Steven W. SINTON, Peter V. BEDWORTH
  • Publication number: 20180002042
    Abstract: A filling device with a filling failure is identified less costly, and the filling amount by the filling device is adjusted quickly. The filling/sealing device includes a filler including a filling turret having a plurality of holding parts and a filling device provided for each of the holding parts to fill a container with a liquid content, forwarding turrets that hold and turret-convey a container transported from the filling turret, a sealing device that seals the container transported from the forwarding turrets with a lid, an inspection device provided in the path, in which the container is held and turret-conveyed, to inspect a filling amount in the container, and a controller that identifies a filling device with a filling failure on the basis of an inspection result from the inspection device and controls the filling amount by the filling device.
    Type: Application
    Filed: December 16, 2015
    Publication date: January 4, 2018
    Applicants: TOYO SEIKAN CO., LTD., MITSUBISHI HEAVY INDUSTRIES MECHATRONICS SYSTEMS, LTD.
    Inventors: Kazuyuki KUROSAWA, Hidehiko YUSE, Shinichi HIZUME, Shinji ISHIKURA
  • Publication number: 20180002043
    Abstract: A method of packaging a product within a bag includes the step of providing for at least one product security element to be present on or within the bag, in a region of where the bag will be sealed. The method also includes the steps of filling the bag with the product, and subsequently sealing the bag, using heat sealing apparatus, whereby the seal thus formed passes through at least a portion of the at least one product security element, thereby permanently heat sealing the product security element to the bag.
    Type: Application
    Filed: September 15, 2017
    Publication date: January 4, 2018
    Inventors: Shane Robert RECKIN, Denys Anthony HENDRA, Scott Edward LEANING
  • Publication number: 20180002044
    Abstract: A break-open single-dose package includes at least one support panel movable to fold the break-open single-dose package, a sealable pocket for storing a spreadable consumable, an applicator, and one or more grips adjacent the at least one support panel. The sealable pocket is positioned adjacent the at least one support panel and includes a frangible region adapted to form an opening through which the spreadable consumable can exit the pocket in response to folding of the break-open single-dose package. The applicator is positioned adjacent the frangible region of the pocket for permitting a user to spread any spreadable consumable that exits the pocket on a surface using the applicator without requiring the user's hand(s) to contact the spreadable consumable. The one or more grips are positioned and adapted to facilitate user control of the break-open single-dose package. Other example single-dose packages are also disclosed.
    Type: Application
    Filed: June 29, 2017
    Publication date: January 4, 2018
    Inventors: Bryce G. RUTTER, Craig SAWICKI
  • Publication number: 20180002045
    Abstract: A packaging apparatus includes a first holding unit configured to hold a peripheral edge portion of a film on a front side; a second holding unit configured to hold the peripheral edge portion on a rear side; a lifting unit configured to press an article to be packaged to the film; a folding unit configured to fold the peripheral edge portion on the rear side into an underside of the article to be packaged; and an extruding unit configured to extrude the article to be packaged to the front side. The first holding unit moves to decrease tension of the held film after the peripheral edge portion on the rear side starts to be folded into the underside of the article to be packaged before the extruding unit starts to extrude the article to be packaged from the rear side to the front side.
    Type: Application
    Filed: January 13, 2016
    Publication date: January 4, 2018
    Applicant: Ishida Co., Ltd.
    Inventor: Yuuki TAI
  • Publication number: 20180002046
    Abstract: The steel strapping machine without using joint currently available from the market has three shortcomings. Firstly, packages cannot be strapped tightly. Secondly, a steel strap may get caught on a lower mold when the lower mold is taken out from underside of the steel strap. Thirdly, the strapping machine is not available for small packages. To overcome the shortcomings of the prior arts, the present disclosure proposes a separatable lower mold of the steel strapping machine without using a joint, which is formed as two parts being able to be closed together or separated from each other. The separatable lower mold has advantages that packages can be strapped tightly, the steel strap will not get caught on the lower mold when the lower mold is taken out from the underside of the steel strap and it is possible for the strapping machine to strap small packages.
    Type: Application
    Filed: February 25, 2016
    Publication date: January 4, 2018
    Inventor: Guowu GAO
  • Publication number: 20180002047
    Abstract: A labeling machine for producing respective multipacks, the multipacks comprising a group of products secured together by a label. The labeling machine includes a conveyor that comprises a conveyor module for forming a group of products from a plurality of individual products and for providing the group of products to a labeling process to produce a multipack of products. The labeling machine includes at least one labeler. The conveyor module comprises at least two conveying units which each conveying unit comprising at least one carrier. The movement of the conveying units may be individually controllable allowing two carriers on different conveying units to cooperate as a fixing unit. A method of producing respective multipacks, which each comprise a group of products, using the labeling machine is also provided.
    Type: Application
    Filed: June 30, 2017
    Publication date: January 4, 2018
    Inventors: Georg Austermeier, Hauke Friedhoff
  • Publication number: 20180002048
    Abstract: A pack provided with: a group of tobacco articles; and a sealed wrap, which encloses the group of articles, has a pull-out opening for the articles, is pressurized so as to have an inner pressure that is higher than the atmospheric pressure, and consists of a heat-sealable sheet of wrapping material, which is folded around the group of articles and is stabilized by means of heat-sealing; in the sealed wrap there is a volatile aromatic substance that is independent of the group of tobacco articles.
    Type: Application
    Filed: January 29, 2016
    Publication date: January 4, 2018
    Inventors: Roberto Polloni, Angelo Li Vigni, Luca Federici
  • Publication number: 20180002049
    Abstract: A wrapping group for wrapping products, in containment bands, including a support structure which defines an advancing plane and with which are associated a first conveyor for conveying a plurality of products one after the other and spaced apart from each other, along the advancing plane and along an advancing direction. Each editorial product includes a book and/or a packet of sheets or of sheeted products stacked on each other. A feeding device feeds a plurality of containment bands laid in length one after the other and spaced apart from each other along a plane substantially transversal or orthogonal to the advancing direction and along a feeding direction substantially transversal or orthogonal to the advancing plane of the products.
    Type: Application
    Filed: February 23, 2016
    Publication date: January 4, 2018
    Applicant: SITMA MACHINERY S.p.A.
    Inventors: Marco AVANZI, Gianni MANZINI
  • Publication number: 20180002050
    Abstract: A hand-held handle dispenser comprising: a main frame having a handle, an adhesive tape roll provided at a rear side of the main frame for delivering an adhesive tape, an application element provided at the front side of the main frame for applying the adhesive tape on a parcel and a cutting blade for cutting the adhesive tape, a cartridge for storing an insert strip roll and transport and affixing elements for conveying the insert strip from the cartridge to the application element and affixing it against the adhesive tape to form a handle.
    Type: Application
    Filed: January 21, 2016
    Publication date: January 4, 2018
    Inventor: Yann LE RIGOLEUR