Patents Issued in June 21, 2018
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Publication number: 20180170541Abstract: An unmanned aerial vehicle (UAV) comprises a central body, a plurality of arms that extend out from the central body, and a plurality of rotors. Each arm has one or more joints that segment the arm into a stem portion proximal to the central body and one or more branch portions distal to the central body. The one or more joints permit the one or more branch portions to move horizontally relative to the stem portion between an extended state and a compacted state. The one or more branch portions are arranged substantially parallel to a perimeter edge of the central body in the compacted state. Each rotor in the plurality is attached to the one or more branch portions.Type: ApplicationFiled: February 6, 2018Publication date: June 21, 2018Inventors: Xumin WU, Xiaolong WU, Sungki LEE, Jiyuan AO, Zhuang FENG
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Publication number: 20180170542Abstract: A system comprising: a low observable aircraft (2) having its external surfaces oriented at a limited number of directions; a device (12) mounted to the aircraft (2) outside the external surfaces of the aircraft (2); and a fairing (10) located outside the external surfaces of the aircraft (2), the fairing (10) being releasably coupled to the one or more external surfaces of the aircraft (2), at least part of the fairing(10) being spaced apart from one or more of the external surfaces of the aircraft (2) so as to define a chamber between the fairing (10) and that one or more external surfaces of the aircraft (2). The device (12) is wholly located within the chamber. One or more external surfaces of the fairing (10) are oriented in the same direction as at least one external surface of the aircraft (2).Type: ApplicationFiled: June 21, 2016Publication date: June 21, 2018Inventor: Andrew Charles White
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Publication number: 20180170543Abstract: Methods and systems for attaching and detaching an item satchel from an autonomous delivery unit. An attachment system includes an attachment system frame, and a satchel comprising a plurality of external pins. The attachment system also includes a plurality of hooks, mechanically attached to the frame, each hook including a first engagement surface and a second engagement surface, one or more electric actuators, mechanically attached to the frame, and mechanically connected to the plurality of hooks. Each of the first engagement surfaces engage a corresponding pin of the plurality of external pins at a first position between the horizontal and vertical positions, and each of the second engagement surfaces engage the corresponding pin of the plurality of external pins at the vertical position to secure an item satchel to an autonomous delivery unit.Type: ApplicationFiled: December 21, 2017Publication date: June 21, 2018Inventors: Ryan M Luckay, Robert E. Dixon, JR., Gregory Cooil
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Publication number: 20180170545Abstract: A power drive unit (PDU) includes a light source configured to generate light as pulses with pulse intervals between the pulses. The PDU also includes a light driver configured to control the light source to generate the light at a desired intensity. The PDU also includes a light receiver configured to receive a reflection of the light. The PDU also includes a processor coupled to the light receiver and configured to determine whether the cargo is positioned on the PDU based on the reflection of the light. The PDU also includes a light controller coupled to the processor and the light driver and configured to determine an adjustment to the desired intensity of the light generated by the light source based on an intensity of the reflection of the light and whether the light source is generating a pulse or a pulse interval.Type: ApplicationFiled: December 16, 2016Publication date: June 21, 2018Inventors: Scott Harms, Justin D. Williams
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Publication number: 20180170546Abstract: A cargo handling system for restraining a unit load device includes a structural channel having a hollow interior and at least one roller rotatably mounted within said hollow interior. At least one locking mechanism associated with said structural channel is movable to engage the unit load device. At least one side roller assembly is operably coupled to an exterior surface of said structural channel. The at least one side roller assembly includes a side roller positioned such that said an upper surface of said at least one roller and an upper surface of said side roller are disposed within a plane for supporting said unit load device.Type: ApplicationFiled: February 23, 2017Publication date: June 21, 2018Inventors: Vinodkumar Shivalinga, Narain Jayaprakash, Vikramkumar Bogar, Wallace Harold Larson, Mark L. Olson
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Publication number: 20180170547Abstract: A toilet module attachment assembly that includes a retainer member that is adapted to be secured to a wall. The retainer member includes a wall attachment flange and a press fit portion extending generally inwardly from the wall attachment flange. When the retainer member is secured to a wall a channel is defined between the wall and the press fit portion. The attachment assembly also includes a seal member that includes a bulge portion that is received in the channel of the retainer member.Type: ApplicationFiled: February 9, 2018Publication date: June 21, 2018Inventors: Scott Savian, Ian Geoffrey Scoley, Eric Long
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Publication number: 20180170548Abstract: An aircraft module covering device includes at least one aircraft module and with at least one panel which is configured for covering the aircraft module and is for this purpose fixedly connected to the aircraft module to at least partly cover the aircraft module in a mounted state, wherein the panel is configured to be connected to the aircraft module via at least one form-fit connection and comprises for this purpose at least one connection element, which is fixedly arranged on an underside of the panel.Type: ApplicationFiled: April 8, 2016Publication date: June 21, 2018Inventors: Eugen WOHLMANN, Dennis GIESWEIN, Adam WOJSIAT, Marius HAGEMANN, Philip GRAESER
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Publication number: 20180170549Abstract: An aircraft seat device has a table module and a PED holder configured for supporting a PED in an operable position on the table module, wherein the PED holder comprises at least one holding element which is pivotally connected to the table module, wherein the PED holder comprises a pivot bearing unit, which is configured for pivoting the holding element by more than 180 degrees.Type: ApplicationFiled: April 8, 2016Publication date: June 21, 2018Inventors: Zoltan JUSSLI, Andreas ERB
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Publication number: 20180170550Abstract: An aircraft device includes at least one control and/or regulation unit which is configured for controlling an aircraft passenger seat unit, and of a PED in which at least one operating program is stored, wherein the control and/or regulation unit is configured to receive control signals from the PED for controlling the aircraft passenger seat unit.Type: ApplicationFiled: April 7, 2016Publication date: June 21, 2018Inventors: Michael STRECKERT, Juergen MEHMEL, Michael GERNGROSS, Joerg LAUBENBERGER, Michael HOPPE
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Publication number: 20180170551Abstract: A foot rest installation comprising a base structure that includes a footwell and may be provided under a seat, in a bulkhead or in a console, and a foot rest assembly. The foot rest assembly has a deployable foot rest support structure and a first foot rest component comprising a flexible structure, for example a net, having a first end fixed with respect to the base structure at a first location, and a second end coupled to the foot rest support structure at a second location that is spaced apart from the pivot axis along a front-to-rear axis. When deployed, the foot rest support structure extends downward and rearward from the pivot axis to deploy the net in the footwell. When stowed, the foot rest support structure extends upward and rearward from the pivot axis.Type: ApplicationFiled: December 18, 2017Publication date: June 21, 2018Inventor: Keith Newell
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Publication number: 20180170552Abstract: A collapsible backrest may include a cover and a back panel retained within a first compartment of the cover. A base panel flexibly coupled to the back panel and retained within a second compartment of the cover with the central panel and the base panel defining a notch. A central panel may be flexibly coupled to the base panel and retained within a third compartment of the cover. An end panel may also be flexibly coupled to the central panel and retained within a fourth compartment of the cover. The central panel and the end panel define a cavity. The base panel, the central panel, and the end panel form a triangular support structure in a deployed position. The base panel, the central panel, and the end panel may also be arranged end-to-end and substantially parallel to the back panel in a stowed position.Type: ApplicationFiled: December 16, 2016Publication date: June 21, 2018Applicant: AMI Industries, Inc.Inventors: Jacob W. Kirkley, Chad R. Pacheco
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Publication number: 20180170553Abstract: An innovative passive cooling solution with sealed UAV enclosure system allows heat from a semiconductor chip to be dissipated to the ambient environment through evaporation/condensation phase-change cooling and air cooling a heat sink such as a fin without any additional power consumption to operate cooling solution. One example of such a solution may include a pipe with a fin and a fluid. The pipe may include a wick structure along an inner surface of the pipe configured to allow the fluid to travel within the wick structure and to allow a vapor form of the fluid to exit the wick structure towards a center of the pipe.Type: ApplicationFiled: December 20, 2016Publication date: June 21, 2018Inventors: Peng WANG, Don LE, Jon ANDERSON, Chinchuan Andrew CHIU
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Publication number: 20180170554Abstract: An environmental control system includes a primary heat exchanger operable to transfer heat from an air source to a refrigerant in a generator flow and output an air flow. An ejector is operable to produce an intermediate refrigerant flow based on receiving the generator flow as a motive fluid and drawing a vapor refrigerant flow as a suction fluid. A refrigerant condenser is operable to convert the intermediate refrigerant flow to a liquid refrigerant flow. A pump is operable to provide the refrigerant to the primary heat exchanger from a portion of the liquid refrigerant flow. An expansion device is operable to expand the liquid refrigerant flow prior to entering an evaporator. The evaporator is operable to convert the liquid refrigerant flow to the vapor refrigerant flow and produce a cooled evaporator air flow output based on the air flow.Type: ApplicationFiled: December 21, 2016Publication date: June 21, 2018Inventors: Abdelrahman I. Elsherbini, Brian St. Rock
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Publication number: 20180170555Abstract: A system for de-icing an aircraft structure or surface comprises an inert gas generating system comprising a catalyst for receiving fuel and oxygen and converting the fuel and oxygen to CO2 and H2O in gaseous form, and a condenser for condensing the H2O to liquid form, the condenser providing heat to the aircraft structure or surface.Type: ApplicationFiled: December 18, 2017Publication date: June 21, 2018Inventor: Paul PHILLIPS
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Publication number: 20180170556Abstract: An anti-ice system includes a duct that extends from a hot air bleed source to an anti-ice manifold and a direct-acting valve coupled to the duct. The duct may be configured to route hot air from the hot air bleed source to the anti-ice manifold at a regulated pressure and the direct-acting valve may include an inlet portion, a reference chamber, a force-type torque motor, an outlet portion, and a modulating sleeve. The inlet portion may be configured to be in hot air receiving communication with hot air from the hot air bleed source, the reference chamber may be configured to be in hot air receiving communication with the inlet portion, the force-type torque motor may be configured to control a reference pressure of hot air in the reference chamber, and the outlet portion may be configured in hot air receiving communication with the inlet portion via the modulating sleeve.Type: ApplicationFiled: December 16, 2016Publication date: June 21, 2018Applicant: ROHR, INC.Inventors: ROBERT GOODMAN, ZHIJUN ZHENG, MICHAEL D. GREENBERG
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Publication number: 20180170557Abstract: An ice-protection system for an aerodynamic structure for an aircraft comprising: an outer skin defined by a leading edge point and a trailing edge point that are interconnected by an upper skin and a lower skin, an internal chamber defined within the outer skin configured to be in fluid communication with the atmosphere external to the outer skin via an inlet and an outlet, and at least one air heater provided within the chamber in proximity to the inlet, wherein during use, a pressure differential exists between the inlet and the outlet that causes external air to flow through the chamber from the inlet to the outlet, and wherein the heater is configured to heat the air passing through the inlet such that the temperature of the air in the chamber is sufficiently increased so as to prevent ice accretion on the outer skin.Type: ApplicationFiled: December 18, 2017Publication date: June 21, 2018Inventor: Florian LORENZ
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Publication number: 20180170558Abstract: The present disclosure relates to an aircraft comprising a passenger module, and also a method of protecting a passenger on an aircraft. The passenger module is configured to be ejected through a skin of the aircraft in response to an ejection command. The ejection command may be given in response to a fatal condition to the aircraft being detected or manually indicated.Type: ApplicationFiled: December 11, 2017Publication date: June 21, 2018Inventors: Dariusz SAPIJA, Sebastian Szymanski
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Publication number: 20180170559Abstract: An inflatable flotation device includes an inflatable body configured to be stored in a deflated state and to be inflated in response to an event. The inflatable flotation device also includes a switch attached to the inflatable body and configured to switch from an off state to an on state in response to the inflatable body being inflated at least one of to or beyond a predetermined inflation level. The inflatable flotation device also includes a speaker attached to the inflatable body, electrically coupled to the switch, and configured to generate an audio signal indicating that the inflatable body is ready for use in response to the switch being switched from the off state to the on state.Type: ApplicationFiled: December 20, 2016Publication date: June 21, 2018Inventors: Timothy C. Haynes, Daniel Bahena
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Publication number: 20180170560Abstract: Systems and methods for integrating Boundary Layer Ingestion (BLI) apparatus into an aircraft (1) are disclosed. The longerons (34) in the aft fuselage (18) may be extended to support an aft propulsor (20). The aft propulsor may be a turbofan or turboelectric propulsion system (46). An upper longeron (34a) may support a tail section (14) of an aircraft. The aft fuselage skin (22) is contoured to permit boundary layer airflow to enter an intake fan (24) of the aft propulsor.Type: ApplicationFiled: December 19, 2016Publication date: June 21, 2018Inventors: ANGELINA M. CONTI, PATRICK G. HARVEY, KRUNAL B. MISTRY, KIMBERLY A. RINK, TED K. ROTHAUPT
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Publication number: 20180170561Abstract: An aircraft is provided. The aircraft includes an engine compartment and an engine provided in the engine compartment. The aircraft further includes a ductwork housing positioned above the engine. The ductwork housing includes at least one duct. The at least one duct has an outlet port that faces downwardly. Operation of the engine causes air to flow through the duct and exit the outlet port. The outlet port is configured to direct the air flow downwardly to provide lift for the aircraft.Type: ApplicationFiled: February 6, 2018Publication date: June 21, 2018Inventor: Thomas Francis Daily, JR.
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Publication number: 20180170562Abstract: In one example, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and including front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.Type: ApplicationFiled: February 8, 2018Publication date: June 21, 2018Inventors: Omid B. Nakhjavani, Robert H. Willie, Paul S. Park, Mohammad Ali Heidari, Leonard J. Hebert, Milan Stefanovic, Parminder Singh, Naimishkumar B. Harpal, Andrew Y. Na
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Publication number: 20180170563Abstract: In order to reduce the congestion of the attachment means for aircraft engines in a secondary vein, a first fuselage frame has two side portions for supporting the engine, each associated with one of the two partly buried side engines, these portions being curved inwards so as to surround and follow the profile of the outer shroud of an intermediate case. The side portion is attached on this shroud through first and second attachment arrangements spaced apart from each other circumferentially, these arrangements being configured in order to allow absorption of the forces related to the torque along a longitudinal direction of the engine.Type: ApplicationFiled: December 18, 2017Publication date: June 21, 2018Inventors: Eric BOUCHET, Esteban MARTINO-GONZALEZ, Jerome COLMAGRO, Fernando INIESTA LOZANO, Julien MOULIS, Antoine ABELE
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Publication number: 20180170564Abstract: A unit (1?, 10?, 100?) for generating non-propulsive electrical power for use on board an aircraft, the unit (1?, 10?, 100?) comprising an electricity production device (3, 30) comprising a gas turbine (31) and an electricity generator (32) mechanically connected to an outlet shaft (33) of the gas turbine (31), said electricity generator (32) including output electrical connections (320) for being electrically connected to an electrical power supply network (2, 20, 200) on board an aircraft. The unit (1?, 10?, 100?) includes energy storage means (5) and regulator means (6) configured to control the speed of rotation of the gas turbine (31) as a function of the electrical power required by the on-board electrical power supply network (2, 20, 200).Type: ApplicationFiled: December 15, 2017Publication date: June 21, 2018Applicants: SAFRAN POWER UNITS, INSTITUT NATIONAL POLYTECHNIQUE DE TOULOUSE, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUEInventors: Stephane Richard Dominique Vaillant, Mickael Faucher, Christophe Turpin
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Publication number: 20180170565Abstract: An aircraft drive device (10) for creating propulsion and/or lift of an aircraft, the drive device comprising a rotating shaft (12), a rotating shaft bearing (14, 16), a rotating shaft drive machine (18) for rotationally driving the rotating shaft (12), and a housing (20), wherein the rotating shaft bearing (14,16) and the rotating shaft drive device (18) are arranged in an interior of the housing (44) and the rotating shaft (12) protrudes to the outside of the housing (20) through a housing opening (42) of the housing (20), wherein in the region of the housing opening (42) an overvoltage arrester device (52) is arranged which is designed for diverting an overvoltage present at the rotating shaft (12).Type: ApplicationFiled: December 21, 2017Publication date: June 21, 2018Inventors: Jürgen STEINWANDEL, Michael HOFMANN, Michael JUDAS
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Publication number: 20180170566Abstract: A system is provided for an aircraft propulsion system. This system includes a nacelle structure, a nacelle cowl and an alignment assembly. The nacelle cowl is configured to move between a closed position and an open position. The alignment assembly includes a pair of mating components respectively arranged with the nacelle structure and the nacelle cowl. A first of the pair of mating components is configured as or otherwise includes a receptacle. A second of the pair of mating components is configured as or otherwise includes a locator. The locator is configured to mate with the receptacle and thereby locate the nacelle cowl relative to the nacelle structure when the nacelle cowl is in the closed position. The locator includes a base and a guide attached to the base. The guide is formed as a discrete body from the base.Type: ApplicationFiled: December 16, 2016Publication date: June 21, 2018Inventors: Thomas Paolini, Marc Schommer
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Publication number: 20180170567Abstract: An autothrottle system for an aircraft includes a motor, actuator assembly, and position sensor operatively connected between the motor and a moving portion of the actuator assembly. An electronic controller is configured to control the motor to move the actuator assembly to actuator positions based at least on position information from the position sensor to move the throttle lever to lever positions. When a surge condition is detected the autothrottle increases the throttle lever in a regulated manner for optimal performance over the different regions of an engine power output.Type: ApplicationFiled: February 20, 2018Publication date: June 21, 2018Inventor: Geoffrey S. M. HEDRICK
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Publication number: 20180170568Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment. Thus, the air input lip has a lighter structure.Type: ApplicationFiled: December 7, 2017Publication date: June 21, 2018Applicants: Airbus Operations S.A.S., AIRBUS SASInventors: Alain Porte, Patrick Oberle, Gregory Albet
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Publication number: 20180170569Abstract: An engine cooling system for a rotorcraft includes an engine having an engine cooling circuit, a hydraulic pump powered by the engine to pump hydraulic fluid, and a hydraulic circuit in fluid communication with the hydraulic pump and the engine cooling circuit, the hydraulic circuit including at least one hydraulic-powered component. The hydraulic pump is adapted to pump the hydraulic fluid through both the hydraulic circuit and the engine cooling circuit, thereby cooling the engine.Type: ApplicationFiled: December 20, 2016Publication date: June 21, 2018Applicant: Bell Helicopter Textron Inc.Inventor: Nicholas Brodeur
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Publication number: 20180170570Abstract: A control system for an aircraft refueling boom controls the movements of the boom in certain areas in a total field of movement volume of possible boom movements based on the location of the boom in the total field of movement volume and based on the current rate of movement of the boom in the total field of movement volume.Type: ApplicationFiled: February 13, 2018Publication date: June 21, 2018Applicant: The Boeing CompanyInventors: Kimberly Hinson, Jung Soon Jang, Richard Golob, Justin Cleve Hatcher, Jeffrey Lee Musgrave
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Publication number: 20180170571Abstract: In one embodiment, a method of determining the onset of a stall condition in a vehicle is provided. The method comprises: measuring, with a stall detection system, data which would indicate the presence of turbulent fluid flowing proximate to a foil; determining from the data whether an onset of a stall condition has occurred; and upon determining the onset of the stall condition, performing at least one of: issuing an alert, and causing the vehicle to avoid or exit the stall condition, and cease such activity when the onset of the stall condition no longer exists.Type: ApplicationFiled: December 21, 2016Publication date: June 21, 2018Inventors: Jason Garde, Grant Lodden, Xiao Zhu Fan, Matthew Wiebold
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Publication number: 20180170572Abstract: In one example, a method includes receiving, over an aircraft data communications bus, a plurality of non-pneumatic inputs corresponding to aircraft operational parameters. The method further includes processing the plurality of non-pneumatic inputs through an artificial intelligence network to generate an air data output value, and outputting the air data output value to a consuming system for use when a pneumatic-based air data output value is determined to be unreliable.Type: ApplicationFiled: February 15, 2018Publication date: June 21, 2018Inventors: Kaare Josef Anderson, Brian Daniel Matheis, Derrick D. Hongerholt, William Kunik
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Publication number: 20180170573Abstract: A system for tracking a vehicle includes a transceiver configured to receive a first signal including first surveillance data from the vehicle at a first time, and receive a second signal from the vehicle at a second time. The system further includes processing circuitry configured to determine a first location and a first course of the vehicle at the first time based on the first surveillance data, and determine a change in power level from the first signal to the second signal. The processing circuitry is further configured to predict a maneuver for the vehicle based on the first location, the first course, and the change in power level from the first signal to the second signal.Type: ApplicationFiled: December 16, 2016Publication date: June 21, 2018Inventors: Guoqing Wang, Ruy C. Brandao, Rong Zhang, Zhong Chen, Ray Zhang
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Publication number: 20180170574Abstract: The example embodiments are directed to a device and method for matching together aircraft status reports. In one example, the method includes detecting, via a user interface, a selection of an aircraft from among a plurality of aircraft that have provided aircraft status reports, determining a group of aircraft status reports, from among the received status reports, which were generated by the respective aircraft during a flight of the respective aircraft, based on metadata of the received aircraft status reports, and displaying, via the user interface, the group of aircraft status reports determined to be provided by the respective aircraft during the flight. By linking together status reports from an entire flight, analysis may be performed on data from across an entire flight instead of an individual status report thereby improving flight data analysis and subsequent actions taken based on that analysis.Type: ApplicationFiled: December 21, 2016Publication date: June 21, 2018Inventors: Robert Samuel KAHN, Laird Eldon BECKER, III, Michael Dean FULLINGTON, Roopa GIDUGU
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Publication number: 20180170575Abstract: A wireless engine monitoring system for an aircraft engine includes a housing and wireless transceiver that receives engine data, including engine data relating to environmental engine emissions. A processor processes the engine data and generates an alarm report when the environmental engine emissions exceed a threshold.Type: ApplicationFiled: January 30, 2018Publication date: June 21, 2018Inventor: James J. ZIARNO
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Publication number: 20180170576Abstract: A conductive fastener system for connecting a composite structure to a support structure includes a composite structure hole that extends through the composite structure and shares a common axis with a support structure hole that extends at least partially through the support structure. A fastener comprising a shank having an outer surface passes through the composite structure hole and at least partially through the support structure hole and provides an annular space between the outer surface of the shank and the inner surface of the composite structure hole. The annular space is filled with a conductive paste that comprises conductive particles suspended in a bonding agent.Type: ApplicationFiled: December 20, 2016Publication date: June 21, 2018Applicant: The Boeing CompanyInventor: Shahriar Khosravani
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Publication number: 20180170577Abstract: A method of operating an aircraft headlight system of an aircraft, the aircraft headlight system having at least one headlight, includes the steps of operating the aircraft headlight system in a landing light mode during a descent of the aircraft, with the at least one headlight emitting a landing light output in the landing light mode; operating the aircraft headlight system in a taxi light mode during taxiing of the aircraft, with the at least one headlight emitting a taxi light output in the taxi light mode; and transforming the landing light output into the taxi light output after touch-down of the aircraft by operating the aircraft headlight system in at least one intermediate lighting mode between operating the aircraft headlight system in the landing light mode and operating the aircraft headlight system in the taxi light mode.Type: ApplicationFiled: December 18, 2017Publication date: June 21, 2018Inventors: Andre HESSLING-VON HEIMENDAHL, Christian SCHOEN
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Publication number: 20180170578Abstract: Devices for protecting aircraft against bad weather. A device for protecting a wing of an aircraft including a load-bearing structure for a protective wall for the wing, the load-bearing structure having a supporting frame having at least two uprights linked by at least one cross member, at least one upright, at the end of the frame having a linking attachment arrangement permitting at least rotation about an axis perpendicular to the surface, the other uprights, each having one foot with an arrangement configured to facilitate the movement of the frame over the surface on which the frame rests. The protection device enables immediate, rapid and easy positioning requiring very few operators.Type: ApplicationFiled: December 14, 2017Publication date: June 21, 2018Inventors: Stéphane MATEO, Romain HECTOR, Christophe COUET
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Publication number: 20180170579Abstract: Systems and methods are provided by which a treatment fluid (e.g., a liquid corrosion inhibitor) may be applied onto the interior surfaces of an aircraft fuselage which employ an automated guided vehicle (AGV) comprising a carriage assembly and a robotic spray system carried by the carriage assembly supported by a support platform positioned laterally of an aircraft fuselage in alignment with the cabin door opening thereof. The AGV may thus be deployable through the cabin door opening of the fuselage to a deployed position within the interior of the fuselage so as to be moveable along a longitudinal axis of the fuselage to allow the robotic spray assembly to spray the treatment fluid onto interior surfaces of the fuselage. A sealing door assembly located rearwardly of the AGV which is moveable relative to a door opening in the fuselage may also be provided so as to sealingly close the door opening of the fuselage when the AGV is deployed within the interior of the fuselage.Type: ApplicationFiled: December 19, 2016Publication date: June 21, 2018Inventors: Rogério Scafutto SCOTTON, Natália Vianna CORREIA, Luiz Fernando DOS SANTOS, Thomas WARING, Richard WARING
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Publication number: 20180170580Abstract: The present invention relates to method for monitoring an engine (1) of an aircraft (2) operating in a given environment. The invention is characterized in that it comprises the implementation, via means for data processing (31), of the steps of: (a) receiving a sequence of n-tuples (x1-exec . . . xn-exec; yexec) of physical-parameter values relating to said aircraft (2) engine (1), including at least one endogenous parameter specific to the operation of the engine (1) and at least one exogenous parameter specific to said environment; (b) For each n-tuple (x1-exec . . . xn-exec, yexec) of the received sequence, calculating, according to a regression model, a standardized value (yexec-norm) of the endogenous parameter in relation to the exogenous parameters; (c) identifying at least one stabilized phase in said normalized sequence of n-tuples (x1-exec . . .Type: ApplicationFiled: November 10, 2015Publication date: June 21, 2018Inventors: Aurelie GOUBY, Guillaume BOTHIER
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Publication number: 20180170581Abstract: A magnetic levitation reaction sphere includes a spherical-housing-shaped rotor and three groups of stators. Each group includes two stators using the sphere center of the rotor as a symcenter. Axes of the three groups are mutually orthogonal. Each stator comprises a stator core and a coil array. An air gap is reserved between an inner surface of each stator core and the outer surface of the rotor. Through grooves are radially formed in the stator cores. The coil arrays are disc-type motor stator windings. Two effective sides of each coil in each coil array are respectively placed in two through grooves of the corresponding stator core. The magnetic levitation reaction sphere has low cost; levitation and rotation driving are integrated; the magnetic levitation reaction sphere has a simple and compact structure, a small size and a low mass, and relates to inherent stable levitation; and the levitation control is simple.Type: ApplicationFiled: March 15, 2016Publication date: June 21, 2018Inventors: Ming ZHANG, Yu ZHU, Anlin CHEN, Kaiming YANG, Rong CHENG, Feng LIU, Jinchun HU, Chuxiong HU, Dengfeng XU, Haihua MU
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Publication number: 20180170582Abstract: A system (100) for feeding propellant to an igniter, the system comprising: a tank (10) presenting an admission (11) and an outlet (12); a liquid propellant feed line connected to the admission (11) of the tank (10); and a propellant outlet line connecting an outlet (12) of the tank (10) to an igniter (40); the system being characterized in that said tank (10) presents an inside volume filled with heat storage spheres (20), said storage spheres (20) being adapted to store heat and to transmit it to a fluid passing through said tank (10), in such a manner as to vaporize a liquid propellant passing through said tank (10).Type: ApplicationFiled: June 9, 2016Publication date: June 21, 2018Applicant: ARIANEGROUP SASInventor: Davide DURI
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Publication number: 20180170583Abstract: The present disclosure provides, among other things, a deployable solar array comprising: an array of electromagnetic transducer devices such as photovoltaic devices; and a flexible, elongated, rectangular sheet for supporting the array of electromagnetic transducer devices composed of a composite laminate having a predetermined pattern of graphite fiber plies which impart a predefined tension in the planar surface of the sheet so that it curls into a planar sheet with a uniform radius of curvature along its major axis.Type: ApplicationFiled: February 6, 2018Publication date: June 21, 2018Inventors: Kenneth Loyd Steele, Theodore Garry Stern
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Publication number: 20180170584Abstract: A lightweight passive attenuator (1) for spacecraft includes two omega cross-section rings (2), placed symmetrically and defining a gap therebetween, and being the main load path of the light passive attenuator (1). A plurality of damper elements (3) are placed in the gap defined between the two omega cross-section rings (2), and not in the main load path of the light passive attenuator (1), such that the omega cross-section rings (2) and the damper elements (3) are assembled at their ends by attachment elements. The omega cross-section rings (2) have a protruding central part (5) with a plurality of holes (6) for connection with adjacent structures (7, 8) of the spacecraft.Type: ApplicationFiled: June 16, 2015Publication date: June 21, 2018Inventor: Miguel LANCHO DONCEL
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Publication number: 20180170585Abstract: The present disclosure relates to a mechanism for releasably securing components of a spacecraft together during launch until such time as the mechanism is commanded to release those components. Upon command, the components are then released with extremely low shock forces being transmitted to the previously secured components due to the release.Type: ApplicationFiled: December 20, 2017Publication date: June 21, 2018Inventors: Gavin HAY, Gregg G. BULL
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Publication number: 20180170586Abstract: Provided herein are various improvements to satellite or payload deployment systems and equipment. In one example, a satellite deployment apparatus is provided. The satellite deployment apparatus includes opposing retention members configured to engage protrusions of a satellite and hold the satellite with respect to a baseplate. The satellite deployment apparatus includes at least one pusher element configured to preload a deployment force on the satellite against the opposing retention members when the protrusions of the satellite are captive in the opposing retention members, and a deployment mechanism configured to spread the opposing retention members responsive to triggering by an actuator system and release the protrusions of the satellite for deployment of the satellite away from the baseplate using at least the deployment force.Type: ApplicationFiled: December 19, 2016Publication date: June 21, 2018Inventor: Brian James Riskas
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Publication number: 20180170587Abstract: A folding unit for producing packages from sealed packs having at least one flap to be folded, the folding unit including a conveying device carrying at least one pushing element arranged for interacting with the at least one flap, and a supporting element onto which the conveying device abuts when the at least one pushing element interacts with the at least one flap. The conveying device also includes at least one rolling element rolling onto the supporting element.Type: ApplicationFiled: February 19, 2015Publication date: June 21, 2018Applicant: TETRA LAVAL HOLDINGS & FINANCE S.A.Inventor: Andrea CATELLANI
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Publication number: 20180170588Abstract: Machine and method for producing electronic-cigarette cartridges; being provided: a fill conveyor which feeds bottom shells of the cartridges along a fill path; a filling device located along the fill path to feed a measure of a liquid substance downwards into each bottom shell; an assembly conveyor which feeds bottom shells along an assembly path; a transfer station where the bottom shells are transferred from the fill conveyor to the assembly conveyor; and at least a first assembly device located along the assembly path to fit each bottom shell with a corresponding top cap.Type: ApplicationFiled: March 20, 2015Publication date: June 21, 2018Inventor: Fulvio Boldrini
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Publication number: 20180170589Abstract: In an embodiment, an apparatus includes a body comprising an inner body wall and an outer body wall centered about a longitudinal axis. The inner body wall and the outer body wall form a ridge at a first end of the body, and the ridge is configured to receive a force applied to the apparatus. The apparatus includes a base at a second end of the body. The base includes a flange configured to form a seal against a container wall and an aperture centered about the longitudinal axis. The base is centered about the longitudinal axis. The apparatus includes an inlet protruding from the base in a direction towards the first end of the body, and the inlet is configured to secure the apparatus to a nozzle of a cartridge. The apparatus is configured to force a material into the cartridge in response to the force applied to the apparatus.Type: ApplicationFiled: February 20, 2018Publication date: June 21, 2018Inventors: Sean Benjamin Warner, Richard A. Luepke
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Publication number: 20180170590Abstract: Various embodiments of a product packing apparatus are disclosed. Embodiments may include a rotating head assembly configured to selectively rotate all or a portion of unique feed lines, to generate a desired packaging configuration. For example, embodiments of the present approach may be used to package bottles or cans of various beverage varieties. A plurality of feedlines may direct beverage varieties towards a rotating head assembly. Each feedline may deliver a specific beverage variety. Depending on the desired packaging configuration, some feedlines may divert around the rotating head assembly, whereas others deliver beverage varieties in linear arrays to the rotating head assembly. The rotating head assembly rotates a select portion of the beverage varieties to generate a desired packaging configuration of beverage varieties.Type: ApplicationFiled: April 6, 2017Publication date: June 21, 2018Inventor: Mark Howell WOJDYLA
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Publication number: 20180170591Abstract: [Problem] It is an object of the present invention to provide a medicine packaging apparatus which has a high reading accuracy for identification information such as an engraved mark attached to a medicine and can provide a superior inspection performance. [Means for Solving the Problem] A medicine packaging apparatus 10 has a medicine preparing and dispensing portion 20, a packaging portion 150, a pre-packaging photographing portion 100 for reading identification information attached to a medicine in a phase before the medicines are packaged by the packaging portion 150, an individually supplying portion 60 which can individually supply the plurality of medicines received from the side of the medicine preparing and dispensing portion 20 to the side of the pre-packaging photographing portion 100 and a control part 200.Type: ApplicationFiled: June 24, 2016Publication date: June 21, 2018Applicant: YUYAMA MFG. CO., LTD.Inventors: Naoki KOIKE, Ryosuke FUKAMORI, Hikaru KATAYAMA, Takuma HIRAOKA