Patents Issued in October 11, 2018
  • Publication number: 20180290729
    Abstract: performing a single-pilot flight of inter-continental duration T>tp=predetermined single-pilot maximal single pilot flight duration; including using pilot-in-command logic empower a single airborne pilot to pilot via an airborne man-machine interface (MMI), only for a time window W<tp, where W includes at least an initial climbing phase of duration t1 and a final descent phase of duration t3; and using pilot-in-command logic to pilot the aircraft during an intermediate cruising phase occurring between the initial climbing and final descent phases, without recourse to the airborne pilot except during an emergency, thereby to accomplish a single-pilot inter-continental flight of duration T>tp, while utilizing the human airborne pilot only for a time period W<tp.
    Type: Application
    Filed: October 5, 2016
    Publication date: October 11, 2018
    Inventor: David Shavit
  • Publication number: 20180290730
    Abstract: An aircraft flight control system comprises a set of primary computers, each configured to compute a flight order dependent on at least one aircraft flight parameter and intended for an aircraft control surface actuator remote controller. Each computer participates in command mode within a first virtual command/monitor pair and in monitor mode within a second virtual command/monitor pair. Each computer determines a consolidated flight parameter value as a function of a flight parameter value acquired by this computer and of flight parameter values received from the other computers, using a consolidation algorithm commonly used by all primary computers to each determine a consolidated flight parameter value, and compute the intended flight order for the remote controller as a function of the consolidated flight parameter value, according to a unique computation whose result is used by the computer both when acting in command mode and when acting in monitor mode.
    Type: Application
    Filed: April 3, 2018
    Publication date: October 11, 2018
    Inventor: Patrice BROT
  • Publication number: 20180290731
    Abstract: The present invention provides a mobile body which can reliably perform a motion intended by a user, irrespective of being within or outside an area of communication with a control device. A drone (3) includes: a first communication section (33) which wirelessly connects to a smartphone (1) after the drone (3) has performed autonomous flight to the vicinity of a destination which has been set; a control section (35) which obtains a position of the smartphone (1); and a movement control section (32) which controls the autonomous flight so that the drone (3) moves closer to the position.
    Type: Application
    Filed: December 20, 2016
    Publication date: October 11, 2018
    Inventor: IWAO ISHIBASHI
  • Publication number: 20180290732
    Abstract: An actuation system for deploying and retracting a lift assisting device of a leading edge of a wing of an aircraft including a track pivotally coupled to the lift assisting device. The track has first and second outer surfaces and side surfaces. The actuation system includes a shaft rotationally coupled within the wing of the aircraft and operable, in response to flight control signals, to deploy or retract the lift assisting device. The actuation system includes an actuator for actuating the lift assisting device, coupled to the shaft, between a retracted position to a deployed position along an arcuate path. The actuation system includes a plurality of track roller bearings rotatably contacting the first and second outer surfaces of the track to guide the track along the arcuate path. The plurality of track roller bearings includes one or more lined track roller assembly.
    Type: Application
    Filed: June 14, 2018
    Publication date: October 11, 2018
    Applicant: Roller Bearing Company of America, Inc.
    Inventors: Frederick S. Gyuricsko, Jay Phoenix, Arnold E. Fredericksen, John H. Cowles, JR.
  • Publication number: 20180290733
    Abstract: A rotorcraft with a fly-by-wire system includes a computing device having control laws. The control laws are operable to engage a stabilization maneuver in response to a perturbation of an otherwise stable operating condition of the rotorcraft, thereby returning the rotorcraft to the stable operating condition without requiring input from the pilot. One or more control laws are further operable to increase or decrease pitch angle, roll angle, yaw rate, or collective pitch angle. In representative aspects, perturbation of the stable operating condition may occur as a result of transient meteorological conditions (e.g., wind shear, wind gust, turbulence) experienced by a rotorcraft engaged in flight operations at airspeeds between 0 knots (e.g., a hover) and about 60 knots. The control laws are further operable to permit the rotorcraft to operate with Instrument Meteorological Conditions (IMC) approval at substantially all airspeeds within a normal flight envelope of the rotorcraft.
    Type: Application
    Filed: April 5, 2017
    Publication date: October 11, 2018
    Inventors: Robert Earl Worsham II, Thomas Wayne Brooks
  • Publication number: 20180290734
    Abstract: A levered landing gear including a first shock strut having a longitudinal axis, a second shock strut disposed concentrically with the first shock strut along the longitudinal axis such that the first shock strut and the second shock strut extend along a common extension axis, and a truck lever coupled to both the first shock strut and the second shock strut such that the second shock strut pivots the truck lever relative to the first shock strut.
    Type: Application
    Filed: April 11, 2017
    Publication date: October 11, 2018
    Inventor: Mitchell L.R. MELLOR
  • Publication number: 20180290735
    Abstract: A vertical take-off and landing high speed aircraft comprising a fuselage having a first and a second end; a first pair of wings positioned between the first and second end; a secondary pair of wings positioned at the second end, wherein the first and second pairs of wings are joined by a pair of booms, each boom of the pair of booms having an fore end and an aft end; a drive propeller positioned at the first or second end; and a plurality of lift rotors positioned at the fore and aft ends of the pair of booms, the plurality of lift rotors providing a lift force necessary for vertical take-off and landing.
    Type: Application
    Filed: April 6, 2017
    Publication date: October 11, 2018
    Inventor: John Uptigrove
  • Publication number: 20180290736
    Abstract: A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The rotors form a synthetic wing and are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.
    Type: Application
    Filed: November 2, 2017
    Publication date: October 11, 2018
    Inventors: Gregor Veble Mikic, JoeBen Bevirt, Alex Stoll
  • Publication number: 20180290737
    Abstract: An apparatus comprising a drivelink comprising a housing including a socket, wherein the socket comprises a cross-sectional area, and a bearing cartridge disposed within the socket, wherein a cross-sectional area of the cartridge is less than the cross-sectional area of the socket. An apparatus comprising a drivelink comprising a housing having a socket, and a bearing cartridge positioned within the socket and comprising a first portion and a second portion, wherein the first portion is configured to undergo compression when a load is applied to the drivelink, and wherein the second portion is configured to not be in tension when the load is applied to the drivelink.
    Type: Application
    Filed: May 22, 2018
    Publication date: October 11, 2018
    Inventors: Emily Schofield, Chad Lewis Jarrett, Daniel P. Sottiaux, Frank Bradley Stamps
  • Publication number: 20180290738
    Abstract: The present application provides a drive link for a constant-velocity joint of an aircraft rotor, the link connecting a drive hub attached to a driveshaft to a rotor yoke. The link comprises a leading bearing connected to the drive hub, a trailing bearing connected to the yoke, a central portion between the bearings, and a tension loop connecting the bearings. The tension loop is formed from a composite material and is formed as a continuous band. The tension loop transfers drive forces from the leading bearing to the trailing bearing for driving the yoke in rotation with the driveshaft.
    Type: Application
    Filed: June 12, 2018
    Publication date: October 11, 2018
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Richard E. Rauber, Frank B. Stamps
  • Publication number: 20180290739
    Abstract: In one embodiment, a rotorcraft can include a teetering tail rotor assembly. The teetering tail rotor assembly can include one or more multi-bearing yokes. Each yoke can include three or more spherical bearings evenly spaced apart from each other. The teetering tail rotor assembly can include a tail rotor blade affixed to each yoke arm through the three or more spherical bearings. The physical dimensions of the three-bearing yoke can be 10% smaller than a two bearing yoke that can support an equivalent load. For example, the length of each three bearing yoke can be 28 inches, the thickness can be 0.85 inches, and the width can be 3.250 inches.
    Type: Application
    Filed: April 7, 2017
    Publication date: October 11, 2018
    Inventors: Hassan A. Mughal, Jared Addison Hallett, Andrew Paul Haldeman
  • Publication number: 20180290740
    Abstract: An aircraft is provided and includes an airframe, a main rotor assembly operably disposed at an upper portion of the airframe to provide lift, a propulsor assembly operably disposed at a tail portion of the airframe to provide thrust and a control system. The control system includes a mono-cyclic swashplate assembly that is translatable in a translation direction to execute collective control of the propulsor assembly and rotatable about an axis defined transversely with respect to the translation direction to execute cyclic control of the propulsor assembly.
    Type: Application
    Filed: March 18, 2016
    Publication date: October 11, 2018
    Inventors: David A. Darrow, Jr., Ron William Waldo, Stephen V. Poulin, Bryan Kenneth Baskin, Biqiang Xu
  • Publication number: 20180290741
    Abstract: A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing.
    Type: Application
    Filed: May 8, 2018
    Publication date: October 11, 2018
    Inventors: Dana J. Taylor, Phillip T. Tokumaru, Bart Dean Hibbs, William Martin Parks, David Wayne Ganzer, Joseph Frederick King
  • Publication number: 20180290742
    Abstract: A propulsion assembly for an aircraft includes a housing having a gimbal coupled thereto that is operable to tilt about first and second axes. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades. The rotor assembly is rotatable with the output drive of the electric motor in a rotational plane to generate thrust having a thrust vector with a direction. The first axis of the gimbal is orthogonal to the second axis of the gimbal. Actuation of the gimbal tilts the propulsion system relative to the housing to change the rotational plane of the rotor assembly relative to the housing, thereby controlling the direction of the thrust vector within a thrust vector cone.
    Type: Application
    Filed: May 7, 2018
    Publication date: October 11, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Paul K. Oldroyd, John Richard McCullough
  • Publication number: 20180290743
    Abstract: An autonomous flight vehicle capable of both rotary wing flight and fixed wing flight may include a pair of rotary wing flight thrusters used during rotary wing flight and a smaller pair of hybrid flight thrusters used during both rotary wing flight and fixed wing flight. The larger rotary wing flight thrusters are skewed at an angle to reduce an apparent torque and improve the controllability of the autonomous flight vehicle, while using smaller, and so more efficient, thrusters during fixed wing flight.
    Type: Application
    Filed: May 30, 2017
    Publication date: October 11, 2018
    Applicant: SkyX Limited
    Inventor: David Vorsin
  • Publication number: 20180290744
    Abstract: This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back.
    Type: Application
    Filed: June 11, 2018
    Publication date: October 11, 2018
    Inventors: Jerry Daniel Claridge, Charles Fischer Manning
  • Publication number: 20180290745
    Abstract: A flight management system that manages flight conditions of a plurality of flying objects and that causes the flying objects to work together in a coordinated manner to accomplish a purpose. The flight management system includes a flight management apparatus that receives instruction information for giving an instruction to flying objects, that registers a job based on performance information and status information of the flying objects, and that based on the job, gives a motion instruction to one or more flying objects. The flight management system includes also a job generating means that based on the instruction information, generates a job, and a motion instruction means that based on a registered job, gives a motion instruction to the flying object.
    Type: Application
    Filed: October 7, 2016
    Publication date: October 11, 2018
    Inventor: Masayuki KUMADA
  • Publication number: 20180290746
    Abstract: A battery-powered aerial vehicle has a central controller, one or more propelling modules, and one or more battery assemblies for powering at least the one or more propelling modules. The battery assemblies are at a distance away from the central controller for reducing electromagnetic interference to the central controller. In some embodiments, the aerial vehicle is an unmanned aerial vehicle (UAV) having a center unit, a plurality of rotor units circumferentially uniformly distributed about and coupled to the center unit, and one or more battery assemblies. The central controller is in the center unit and the propelling modules are in respective rotor units. Each battery assembly is in a rotor unit in proximity with the propelling module thereof. In some embodiments, the central controller also has a battery-power balancing circuit for balancing the power consumption rates of the one or more battery assemblies.
    Type: Application
    Filed: March 15, 2018
    Publication date: October 11, 2018
    Inventors: Mark Holbrook Hanna, Douglas Morgan Hanna
  • Publication number: 20180290747
    Abstract: This document generally describes a safe-passage guidance strategy developed in a relative velocity framework to enable a generic aerial robot execute a precision three-dimensional maneuver through a narrow orifice in a wall. The relative sizes of the robot and the orifice can be such that the orifice is only slightly larger than the robot. The orifice can be approximated as an elliptical shape, and analytical nonlinear guidance laws incorporating state-based switching can be derived. Guidance laws can be used to maneuver the robot through both fixed and moving orifices as well as in scenarios when the orifice is closing with time.
    Type: Application
    Filed: March 19, 2018
    Publication date: October 11, 2018
    Inventors: Animesh Chakravarthy, Debasish Ghose
  • Publication number: 20180290748
    Abstract: A small unmanned aircraft system is outfitted with a variety of sensors, and communications equipment to enable autonomous, remote exploration and mapping of spaces non line of sight (NLOS), and in the absence of global positioning signals.
    Type: Application
    Filed: April 3, 2018
    Publication date: October 11, 2018
    Applicant: Versatol, LLC
    Inventors: Lawrence C. Corban, John Eric Corban, Eric Graham Leal
  • Publication number: 20180290749
    Abstract: The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.
    Type: Application
    Filed: June 8, 2018
    Publication date: October 11, 2018
    Inventors: Dongdong LUO, Feng NI, Hang LV, Wenbing SU
  • Publication number: 20180290750
    Abstract: The present disclosure relates to an apparatus and a method for an unmanned flying aircraft, such as a drone. Sensor data of at least one imaging sensor and of at least one ranging sensor are received with a sensor interface and are supplied to a signal processing unit that is set up to compare the sensor data with reference data in order to detect at least one predefined object and/or to distinguish it from other objects and to determine the parameters of the detected or distinguished object. The parameters of the predefined objects are then output with an output interface.
    Type: Application
    Filed: June 8, 2018
    Publication date: October 11, 2018
    Inventor: Antony PFOERTZSCH
  • Publication number: 20180290751
    Abstract: The present invention includes a movable seat assembly for a vehicle, comprising: first and second predetermined paths located on the floor of the vehicle, each path having an operational location at a first end and an ingress/egress location at a second end, the paths having a substantially straight portion and a curved portion; a seat slidably connected to the paths and capable of translation between the first and the second position; two or more openings on the floor of the vehicle on or about the first and second predetermined paths that provide a locking position for the seat, wherein the two or more opening are connected via a conduit below the surface of the floor; and at least one locking pin/plunger connected to the seat and capable of engaging the two or more openings to lock the seat in place along the first and second predetermined paths.
    Type: Application
    Filed: April 11, 2017
    Publication date: October 11, 2018
    Inventors: Joshua Andrew Emrich, Guillaume Noiseux Boucher
  • Publication number: 20180290752
    Abstract: A seating device comprises a seat bottom unit, in particular an aircraft seat bottom unit, having an accommodating region for receiving a module, in particular a lifejacket module, with at least one upper wall element which forms at least a support surface for a comfort element.
    Type: Application
    Filed: September 29, 2016
    Publication date: October 11, 2018
    Inventors: Zoltan JUSSLI, Jens JAKUBOWSKI, Michael HORLACHER
  • Publication number: 20180290753
    Abstract: Systems and methods are described for controlling seat actuation and other controls using an in-flight entertainment system of an aircraft or other vehicle. The system can include an electronic control unit configured to send commands to actuate a passenger seat based on input received via a passenger controlled device. The electronic control unit or a related peripheral component is configured to receive a flight phase notification. If the flight phase notification indicates a taxi, take-off or landing phase, the electronic control unit sends a command to disable actuation of the passenger seat. Such command could also be sent if the flight phase notification is not received for a predefined time period.
    Type: Application
    Filed: April 6, 2018
    Publication date: October 11, 2018
    Inventor: Matthew Gledich
  • Publication number: 20180290754
    Abstract: An airplane seat device has a seat base module, comprising at least one main body which is at least substantially implemented from a rigid foam, at least one comfort element disposed on an upper side of the main body, at least one accommodating region for attaching to a tubular support, and at least one fastening element for attaching to the tubular support. Wherein the main body has at least two coupling regions, via which the at least one fastening element can be selectively attached to the main body.
    Type: Application
    Filed: August 29, 2016
    Publication date: October 11, 2018
    Inventor: Andreas SCHUMM
  • Publication number: 20180290755
    Abstract: A ram air fan and fan bypass shutoff check valve assembly includes a ram air fan configured to draw an airflow through a fan inlet, and a ram fan bypass duct positioned downstream of the ram air fan. The ram fan bypass duct includes a valve assembly configured to selectably direct the airflow through the ram air fan when the valve assembly is in an open position, and direct the airflow through a bypass duct thereby bypassing the ram air fan when the valve assembly is in a closed position.
    Type: Application
    Filed: April 7, 2017
    Publication date: October 11, 2018
    Inventors: Donald E. Army, Frederick Peacos, III
  • Publication number: 20180290756
    Abstract: An in-line heater system on board an aircraft includes a heater element positioned within a tubing, at least one sensor positioned within the tubing configured to monitor the temperature within the tubing, and an inline heater controller configured to receive information regarding the heater element via the at least one sensor. The inline heater controller is positioned at a location spaced away from the heater element and the tubing. The inline heater controller includes a printed circuit board configured to receive the information regarding the heater element via the at least one sensor, and an aerospace connector configured to transmit the information regarding the heater element via the at least one sensor to the aircraft.
    Type: Application
    Filed: May 15, 2017
    Publication date: October 11, 2018
    Inventors: Alan L. White, Greg King
  • Publication number: 20180290757
    Abstract: An onboard rebreathing loop system resident on an aircraft for providing oxygen to aircraft personnel includes a ceramic oxygen generating system (COGS) module configured to receive an inlet air and output a high purity oxygen (O2) gas into a breathing loop and a carbon dioxide (CO2) scrubber module configured to receive exhaled air from the aircraft personnel and output a CO2-scrubbed air into the breathing loop. The high purity O2 gas and CO2-scrubbed air are mixed to form a mixed gas having a partial pressure of O2 suitable for breathing by the aircraft personnel. The onboard rebreathing loop system may further include an odor removal module, an air temperature and/or humidity control module to condition the mixed gas before breathing by the aircraft personnel, and a gas sensor module to confirm the partial pressure of O2 within the mixed gas before breathing by the aircraft personnel.
    Type: Application
    Filed: April 10, 2018
    Publication date: October 11, 2018
    Applicant: Carleton Life Support Systems, Inc.
    Inventors: Steven C. Peake, Gary Byrd, Courtney J. Monzyk, Timothy Raleigh, Chris Fellner, Gary Wu
  • Publication number: 20180290758
    Abstract: A deicing system for an aircraft may supply heat to an aircraft component in pulses. A first series of pulses may melt ice built up on the aircraft component. A second series of pulses may prevent ice from forming on the aircraft component. The length of each of the pulses in the first series of pulses may be longer than the length of each of the pulses in the second series of pulses. The pulses may be supplied by a pneumatic deicing system or an electrical deicing system.
    Type: Application
    Filed: June 8, 2018
    Publication date: October 11, 2018
    Applicant: Rohr, Inc.
    Inventors: Galdemir Cezar Botura, Dimitrios Papaioannou
  • Publication number: 20180290759
    Abstract: A computer-implemented method, system, and/or computer program product optimizes an operation of an aerial drone. A drone on-board computer on an aerial drone receives sensor readings from sensors on the aerial drone, where the sensor readings detect a change in flight conditions while the aerial drone is flying between a first location and a second location. In response to the sensors on the aerial drone detecting a change in the flight conditions while the aerial drone is flying between the first location and the second location, the drone on-board computer disengages an electric motor from propellers on the aerial drone and engages an internal combustion engine to the propellers.
    Type: Application
    Filed: June 8, 2018
    Publication date: October 11, 2018
    Inventors: AHAMED JALALDEEN, CHIVUKULA V. L. NARAYANA
  • Publication number: 20180290760
    Abstract: An aircraft jet propulsion system is disclosed. The aircraft jet propulsion system may comprise a thermoelectric generator array (“TEG” array) coupled to a portion of the aircraft jet propulsion system, wherein the TEG array converts heat energy to electrical energy, and supplies power to the aircraft jet propulsion system, wherein the electrical energy is supplied to a power supply. The aircraft jet propulsion system may comprise an alternator that generates less energy than is required to power the aircraft jet propulsion system. The TEG array may supplement the energy generated by the alternator. The energy generated by the TEG array and the energy generated by the alternator may be sufficient to power the aircraft jet propulsion system and/or the electrical energy generated by the TEG array may be sufficient to power to aircraft jet propulsion system.
    Type: Application
    Filed: June 12, 2018
    Publication date: October 11, 2018
    Applicant: United Technologies Corporation
    Inventor: John Akin
  • Publication number: 20180290761
    Abstract: An inerting system for aircraft including a gas circuit with successively at least one air inlet, a compressor and an air separation module. The air separation module includes an outlet for oxygen-enriched gas and an outlet for inerting gas. The air separation module includes gas permeation membranes resistant to a temperature greater than or equal to 100° C. and preferably 140° C., and the inerting gas outlet is connected to a turbine for releasing pressure and cooling the inerting gas.
    Type: Application
    Filed: April 5, 2018
    Publication date: October 11, 2018
    Inventors: Pierrick MAILHET, Frederic TONG-YETTE
  • Publication number: 20180290762
    Abstract: An avionics display for rotorcraft provides a depiction of 360 degrees of terrain and obstacles about the rotorcraft using a top plan view at above a predetermined altitude that transitions to an angle perspective view as the altitude drops. The display provides improved situational awareness for highly mobile aircraft at critical times of takeoff and landing.
    Type: Application
    Filed: April 11, 2016
    Publication date: October 11, 2018
    Inventors: David J. Moore, Terrance J. McCraw
  • Publication number: 20180290763
    Abstract: A sky tree for unmanned aerial vehicles includes a trunk, a flight platform, an elevator, a parking room, a command center, and a supply station. The sky tree is arranged in a geographic region to provide the unmanned aerial vehicles in the region for certain application field with logistics support integrating command dispatching, application monitoring, communication relay, and replenishment. A sky forest for unmanned aerial vehicles includes a plurality of sky trees for unmanned aerial vehicles arranged in a geographic region, and a control center. The sky forest becomes part of the public property in the geographic region, provides logistics support for all unmanned aerial vehicles in the region, and controls flights of the unmanned aerial vehicles in an orderly manner.
    Type: Application
    Filed: June 8, 2018
    Publication date: October 11, 2018
    Inventor: Shihwa Huang
  • Publication number: 20180290764
    Abstract: Some embodiments described herein relate to a drone landing platform. One or more sensors coupled to the drone landing platform can detect local conditions in the vicinity of the drone landing platform. A communications system can be operable to transmit information related local conditions to a drone.
    Type: Application
    Filed: April 5, 2018
    Publication date: October 11, 2018
    Applicant: DroneTerminus LLC
    Inventors: Joseph Barry MCMILLIAN, Mark MESSINA, Paul CAPRIOLI
  • Publication number: 20180290765
    Abstract: A processing station for registering a piece of passenger's luggage for a trip, wherein the processing station comprises: an injector for receiving the piece of luggage associated with the passenger: at least one sensor associated with the injector, the at least one sensor, in combination with at least the floor of the injector, creating a zone around the piece of luggage; and a controller associated with the sensor being adapted to: monitor, via the at least one sensor, intrusions through the zone to determine one or more of whether a predetermined limit on dimensions of the piece of luggage has been exceeded or whether a foreign object has intruded the zone from outside, and allow further processing of the piece of luggage only if no intrusion of the zone is detected; and wherein the controller adjusts the area of the zone to accommodate different sizes of luggage.
    Type: Application
    Filed: February 23, 2018
    Publication date: October 11, 2018
    Inventors: Richard DINKELMANN, Rainer Rudolf DINKELMANN
  • Publication number: 20180290766
    Abstract: A system for verifying an aircraft instrumentation value comprising: an Air Data Test Module (ADTM) configured to pneumatically simulate at least one instrumentation value based upon a pressure set-point. The pneumatically simulated instrumentation value corresponds to the pressure set point and is reported by an aircraft transponder. A receiver module receives the pneumatically simulated instrumentation value transmitted by the aircraft transponder. A signal processor, is operative to (i) control the ADTM, (ii) command a prescribed instrumentation value to be simulated by the ADTM, (iii) compare the prescribed instrumentation value to the pneumatically simulated instrumentation value, and (iv) issue a pass signal when the values match, and a fail signal when the values differ by a threshold value.
    Type: Application
    Filed: April 11, 2017
    Publication date: October 11, 2018
    Inventors: Thomas J. Piggin, Neil Stewart Sands, Peter John McCarthy
  • Publication number: 20180290767
    Abstract: The satellite launcher comprises a plurality of stages detachable from each other, at least one stage including at least one engine, and at least one of said stages carrying a payload, and said stages are placed one beside or around the other, so that the width of the vehicle is at least one third of its length. The method comprises the following phases: a) ascent of the vehicle with a balloon from a ship; and b) ignition of engines of the vehicle to put a satellite placed in the vehicle into orbit.
    Type: Application
    Filed: September 23, 2015
    Publication date: October 11, 2018
    Applicant: ZERO 2 INFINITY SL
    Inventor: Jose Mariano LOPEZ-URDIALES
  • Publication number: 20180290768
    Abstract: Disclosed is a satellite which includes: at least one optical photography instrument including a main lens having an optical axis and the optical instrument having a field of view; at least one launcher interface system, intended for being removably secured to a satellite interface system of a launcher of the satellite; a linking device between the launcher interface and the optical instrument extending substantially parallel to the optical axis of the main lens between an upper end and a lower end; the launcher interface system is connected to the linking device by the lower end and the optical axis of the optical instrument is directed from the upper end towards the lower end of the linking device, the launcher interface system being outside the field of view of the instrument.
    Type: Application
    Filed: September 29, 2016
    Publication date: October 11, 2018
    Inventors: Frédéric FAYE, Eric BEAUFUME, Jacques COTTIER
  • Publication number: 20180290769
    Abstract: A torque generation system includes: a plurality of solar array panels and/or solar array panel divisions; and a torque controller configured to control an electricity generation ratio of each of the plurality of solar array panels and/or solar array panel divisions to generate torque.
    Type: Application
    Filed: May 30, 2018
    Publication date: October 11, 2018
    Applicant: Japan Aerospace Exploration Agency
    Inventors: Osamu MORI, Junichiro KAWAGUCHI, Yoji SHIRASAWA, Toshihiro CHUJO, Kosuke AKATSUKA
  • Publication number: 20180290770
    Abstract: A rotary propulsion engine system designed to propel a craft. Such a rotary propulsion engine system comprises at least two reaction masses or armatures, at least two reaction mass driver assemblies, at least two travel pathways for said reaction masses or armatures, two counterrotating discs housing an equal number of the at least two said reaction mass driver assemblies, and a counterbalancing means used to maintain a balanced distribution of masses about the axis of rotation of each counterrotating disc in order to maintain a zero horizontal torque sum as each reaction mass or armature moves along its ballistic trajectory. Reaction masses are fired into a rotational environment wherein the kinetic energy of said reaction masses is recycled, thereby reducing or eliminating the need for chemical propellant-based propulsion systems, and transporting heavy, finite, and expensive fuels for combustion.
    Type: Application
    Filed: April 6, 2018
    Publication date: October 11, 2018
    Inventor: Aaron Allen Opalek
  • Publication number: 20180290771
    Abstract: A spacecraft includes payload equipment and bus equipment, each of the payload equipment and the bus equipment being coupled with a secondary structure arrangement. The spacecraft is configured to structurally interface with a launch vehicle upper stage only by way of an exoskeletal launch support structure (ELSS) that provides a first load path between a launch vehicle upper stage and the secondary structure arrangement. The spacecraft is configured to deploy from the launch vehicle upper stage by separating from the ELSS. In some implementations, the first load path is the only load path between the spacecraft and the launch vehicle upper stage, and substantially all of the ELSS remains with the launch vehicle upper stage. Because the secondary structure may be substantially less massy then the ELSS, subsequent orbit raising maneuvers may then be executed with a spacecraft having a reduced dry mass.
    Type: Application
    Filed: April 5, 2017
    Publication date: October 11, 2018
    Inventor: Jason Chiang
  • Publication number: 20180290772
    Abstract: An automatic filling system is for filling a filling material into a filling container. The automatic filling system includes abase, a transport unit having multiple transport seats disposed along a looped transport route, an input unit for transferring the filling container to one of the transport seats, an inverting unit for inverting the filling container, a fill unit for filling the filling material into the filling container, a stopper placement unit for placement of a stopper, a cap placement unit for placement of a cap, a locking unit for locking the cap, a detecting unit for weight measurement, a defect removing unit, and an output unit for transferring the filling container out of the transport unit.
    Type: Application
    Filed: April 3, 2018
    Publication date: October 11, 2018
    Inventor: Yung-Hsing Lin
  • Publication number: 20180290773
    Abstract: The present invention is a method by which a reusable, refillable pressurized container used in consumer refillable packaging can be certified in a manner akin to single use containers. The certification calls for each receptacle to pass certain quality assurance measures, including automated testing and examination (100% receptacle testing and examination). In an exemplary case, the materials (fluids) in these receptacles will be for personal care or household use and will be non-regulated non-hazardous non-flammable non-corrosive materials (fluids), although the invention will not necessarily be so limited. The gases in these receptacles are preferably non-flammable compressed gases (compressed air or nitrogen) commercially free from corroding components.
    Type: Application
    Filed: April 9, 2018
    Publication date: October 11, 2018
    Inventors: Lawrence M. Levenstein, Eric A. Williams
  • Publication number: 20180290774
    Abstract: A rotatable thermoforming machine for producing soluble pockets made from a soluble web. The machine has a plurality of pocket forming cavities 38a, b, c in each of which a respective pocket is formed in the soluble web. The pockets travel in a machine direction defined as the X direction and filling means 44 is arranged to at least partially fill the or each pocket formed in the soluble web. The filling means 44 comprising one or more nozzles 44, each nozzle 44 being arranged to be moveable in at least the X-direction as the or each respective pocket is filled from the filling nozzle 44.
    Type: Application
    Filed: September 26, 2016
    Publication date: October 11, 2018
    Inventors: James FOWLER, Boris MAKUTONIN
  • Publication number: 20180290775
    Abstract: The present disclosure provides a device for packaging drug portions, including a plurality of reservoir and dispensing stations, at least one conveyance and collecting apparatus, a packaging material feed, a packaging device, a folding and conveyance device included with the packaging device, a guide device including a receiving segment and a conveying segment, the conveying segment extending along the passage of the folding and conveyance device and guides drug portions into the tubular packaging material web, a first joining device arranged downstream of the folding and conveyance device, and a second joining device arranged downstream of the first joining device, which joins the tubular packaging material web at pre-specified intervals with respect to the direction of movement of the tubular packaging material, such that a continuous blister tube is created.
    Type: Application
    Filed: April 7, 2017
    Publication date: October 11, 2018
    Inventor: Dietmar Gross
  • Publication number: 20180290776
    Abstract: A wrapping machine for wrapping groups of products (100) with an extensible plastic film (50) in order to form bundles (200), comprises first conveyor means (2) for supporting and moving a group of products (100) along an advancing direction (A) inside the wrapping machine (1), supporting means (3; 103) for receiving from the first conveyor means (2) and supporting the group of products (100), a wrapping unit (10) for wrapping a portion (51) of film (50) having a preset length around the group of products (100), supported by the supporting means (3; 103), in order to form a bundle (200), a supplying unit (30) of the film (50) to supply the wrapping unit (10) with the film portion (51) having a preset length, separated from the film (50) unwound from a respective reel (55); the supporting means (3; 103) include first gripping means (4; 104) arranged to hold an initial flap (51a) of the film portion (51) during the wrapping of the group of products (100); containment means (6; 60) are provided to abut at least
    Type: Application
    Filed: May 27, 2016
    Publication date: October 11, 2018
    Inventor: Mauro CERÉ
  • Publication number: 20180290777
    Abstract: A food product gathering and dispensing system is disclosed. The food product is generally a flat disc shaped article dispensed onto a consumable strip of food product conveyer material. The food product is fed to single, or series related, spools that wind up the consumable conveyer material and food product into a removable roll. The roll is placed into a dispenser pack, optionally subject to further environmental treatment, and refrigeration. The pack is then installed within a refrigerated dispenser system where the food product and consumable material are collectively unwound and separated, as the food product is fed into a processing system, i.e., a cooking device. The consumable conveyer material is collected and separately discarded.
    Type: Application
    Filed: April 5, 2018
    Publication date: October 11, 2018
    Inventor: Gregg A. MARTIN
  • Publication number: 20180290778
    Abstract: Methods and machines are provided for forming a five-sided carton of packages of smoking articles. A piece of film material is applied to a plurality of packages of smoking articles such that five sides of the plurality of packages are at least partially covered by the film material, but the sixth side remains uncovered. The film material is applied such that the group of packages is sufficiently tightly bound so that none of the packages may slip free from the carton. The sixth side of the plurality of packages in the carton remains exposed so that tax stamps may be easily applied. The film of material may be applied so that a gap is formed relative to the sixth side.
    Type: Application
    Filed: February 28, 2018
    Publication date: October 11, 2018
    Inventors: Jerry Wayne Pipes, Mark Shane Hatcher, Wesley Steven Jones