Patents Issued in March 30, 2017
  • Publication number: 20170088245
    Abstract: A method is provided for manufacturing a rotor body of a Magnus-type rotor. The method includes providing a plurality of arcuate panels, wherein each of the panels has an arc-length less than a predetermined circumference of the rotor body. The method further includes positioning at least three such arcuate panels in mutual edge-wise abutment to form circumferentially a hollow cylindrical loop, wherein longitudinal edges of adjacent panels are mutually attached to each other. The method further optionally includes co-axially stacking one above another at least two loops of substantially similar diameter. The method further includes connecting edges of adjacent loops to define the rotor body of a predetermined height.
    Type: Application
    Filed: March 24, 2015
    Publication date: March 30, 2017
    Inventors: Jarkko VÄINÄMÖ, Martin HILDEBRAND, Christopher STANLEY
  • Publication number: 20170088246
    Abstract: A storage system for a boat includes one or more storage compartments situated in a bow of a boat. An air flow path includes an air inlet opening, the storage compartment, and an air outlet opening. A fan is situated to move air along the air flow path. The fan may be positioned proximate one of the air inlet and the air outlet, for example.
    Type: Application
    Filed: December 12, 2016
    Publication date: March 30, 2017
    Inventors: Randy Wayne HOPPER, Bradley G. GARRINGER
  • Publication number: 20170088247
    Abstract: A rotary wing aircraft is provided including an airframe having a nose section located at a forward end. A window assembly is coupled to the nose section. The window assembly includes a frame and a transparent armored window. The frame has a large opening and a lip extends from a portion of the frame adjacent the large opening. The transparent armored window is formed from a plurality of layers and has a shape generally complementary to the large opening. When the transparent armored window is received within the large opening of the frame, a portion of the transparent armored window is attached to a portion of the lip.
    Type: Application
    Filed: March 18, 2014
    Publication date: March 30, 2017
    Inventor: Craig Hallquist
  • Publication number: 20170088248
    Abstract: A profile for connecting a floor structure. The profile comprises a web with a recess along a longitudinal direction of the profile. The web is adapted to reach into a gap in the floor structure in order to provide the connection of the floor structure. At a first end of the web two lips extending in the longitudinal direction of the profile are attached wherein the lips are adapted to prevent a release of the profile from the gap. The disclosure further relates to a sealing system for a floor structure as well as an aircraft with a sealing system and a method for connecting a floor structure.
    Type: Application
    Filed: September 27, 2016
    Publication date: March 30, 2017
    Inventors: Gerd STAHL, Florian MACKE, Andreas ADAM
  • Publication number: 20170088249
    Abstract: The present disclosure refers to the configuration and manufacturing process of a rib for the construction of an aircraft torsion box. In the method, a flat stack of plies of composite material is layered up, which is then cut to form a flat pre-form having an outer contour having flanges, and an internal contour having two or more diagonal trusses with flanges at opposite sides. The flat pre-form is press-formed to fold the flanges of the outer and internal contour to form a rib pre-form, which is finally cured. The present disclosure also refers to a composite rib having a unitary body by forming a single pre-form of stacked plies. The present disclosure allows the manufacture of the rib in one-shot process, integrating all the ribs components such that the assembly time and cost of the rib are minimized.
    Type: Application
    Filed: September 29, 2016
    Publication date: March 30, 2017
    Inventors: Carlos GARCÍA NIETO, Iker VELEZ DE MENDIZABAL ALONSO, Enrique GUINALDO FERNANDEZ, Soledad CRESPO PEÑA
  • Publication number: 20170088250
    Abstract: Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has an elastically deformable skin defining a first surface. The trailing edge has a first end to be fixed to the wing and a second end opposite the first end that is to move relative to the first end. A flap is movably coupled to the second end of the trailing edge. The flap is movable between a stowed position and a deployed position. The trailing edge is to elastically elongate when the flap moves from the stowed position to the deployed position and the trailing edge is to elastically collapse when the flap moves from the deployed position to the stowed position.
    Type: Application
    Filed: December 12, 2016
    Publication date: March 30, 2017
    Inventors: Christopher K. Droney, Blaine K. Rawdon
  • Publication number: 20170088251
    Abstract: Actuators and methods useful in the operation aircraft flight control surfaces are disclosed. Some of the actuators and methods disclosed may be useful in the operation flight control surfaces when a fault condition such as a jam associated with an actuator is detected. An exemplary electromechanical actuator disclosed comprises: a motor; a first screw configured for translation movement relative to a structure of the aircraft when driven by the motor; a second screw mounted in series with the first screw; and a fuse element coupling the first screw and the second screw together to permit translation movement of the second screw together with the first screw. The fuse element may permit at least partial disengagement of the second screw from the first screw to permit translation of the second screw relative to the first screw. The fuse element may also allow an active flutter damping of the flight control surface. The fuse element may comprise magneto-rheological fluid.
    Type: Application
    Filed: May 13, 2015
    Publication date: March 30, 2017
    Inventors: Gustave NFONGUEM, Patrick CHOUINARD, Jean-Sébastien PLANTE, Marc DENNINGER, Vlad ILIESCU
  • Publication number: 20170088252
    Abstract: The invention relates to an actuator (4) for controlling a flight control surface (3) of an aircraft, comprising:—a primary route (5) comprising a first member (8) for generating a first torque, and a first drive shaft (10) having an end (18) able to be connected to the first member (8) and an end (19) able to be connected to the control surface (3),—a secondary route (6) comprising a second member (24) for generating a second torque and a second drive shaft (26) having an end (45) able to be connected to the second member (24) and an end (46) able to be connected to the control surface (3), in which actuator the second drive shaft (10) is hollow and extends around the first drive shaft (26).
    Type: Application
    Filed: May 21, 2015
    Publication date: March 30, 2017
    Inventors: Louis CHAVIGNIER, Marc LEBRUN, Severin VIENNOT
  • Publication number: 20170088253
    Abstract: An apparatus and method for controlling a yaw moment of a flight vehicle, such as an aircraft. A wing structure of the flight vehicle has a first opening or actuator positioned by a first apex section of a first side of the wing, and has a second opening or actuator positioned away from or at a distance from a second apex section of a second side of the wing. The first side and the second side can each be positioned or located opposite a centerline of the wing or wing structure. A pressure source or other pressure supply device is in communication with the first opening or actuator and the second opening or actuator to which a pressurized fluid, such as air, is controlled and delivered to control or vary the yaw moment of the flight vehicle.
    Type: Application
    Filed: February 24, 2016
    Publication date: March 30, 2017
    Inventors: David R. Williams, Jürgen Seidel
  • Publication number: 20170088254
    Abstract: A flying object includes a main body, an engine, a power system and an ultra-high-pressure fluid injection dynamic orbit-transfer system which includes a pressure storage device for storing a predetermined amount of ultrahigh-pressure gas, a central automatic control system, at least one air pipeline connected to the pressure storage device, and a nozzle assembly provided on the main body and connected to the air pipeline. The nozzle assembly includes a plurality of nozzle units. Each of the nozzle units includes a nozzle body having a nozzle hole, and is arranged and aligned adjacent to at least another the nozzle unit. The central automatic control system is configured to selectively activate at least two of the nozzle units for ejection of ultrahigh-pressure gas so as to controllably alter a flying locus of the flying object.
    Type: Application
    Filed: July 1, 2016
    Publication date: March 30, 2017
    Inventor: RuiQing Hong
  • Publication number: 20170088255
    Abstract: An aircraft active flow control dielectric barrier discharge (DBD) device may include a machinable ceramic dielectric support having an aerodynamic surface shaped to form an exposed flush part of an airfoil surface on an aircraft. The DBD device may include at least two electrodes configured to be oppositely charged and spaced apart from each other on the dielectric support.
    Type: Application
    Filed: September 24, 2015
    Publication date: March 30, 2017
    Applicant: THE BOEING COMPANY
    Inventor: Dejan Nikic
  • Publication number: 20170088256
    Abstract: A hydraulic cylinder includes: a cylinder tube; a piston; a piston rod; a pair of end covers; and a snubbing mechanism configured to reduce the moving speed of the piston after the piston reaches the vicinity of the end of its stroke. The snubbing mechanism includes: a supply/discharge port formed in an associated one of the end covers; a valve configured to open and close the supply/discharge port; a connector configured to connect the valve and the piston together; and at least one recess extending from the edge of the supply/discharge port. When the piston approaches the end of its stroke, the valve closes the supply/discharge port to form a throttle oil passage, and hydraulic oil is discharged through the throttle oil passage to reduce the moving speed of the piston.
    Type: Application
    Filed: August 23, 2016
    Publication date: March 30, 2017
    Inventors: Taku Kondo, Takaaki Onishi, Shogo Hagihara
  • Publication number: 20170088257
    Abstract: A vibration control system for a rotorcraft includes at least one of an integrated actuator and an intermediate actuator associated with a first source of vibration, a sensor configured to sense vibration from the first source of vibration, a dedicated actuator configured for association with a fuselage, and a controller configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.
    Type: Application
    Filed: September 30, 2015
    Publication date: March 30, 2017
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: David E. Heverly, II, Rupinder Singh, Taeoh Lee, Michael Smith
  • Publication number: 20170088258
    Abstract: A head for a rotor of a rotorcraft, the head comprising a cap extending radially from an axis of rotation in elevation towards a periphery and extending in azimuth over 360 degrees, the cap extending in thickness between an inside face that is to face a hub of the rotor and an outside face overlying the inside face, the periphery being crenellated to define a succession of crenellations and of notches, each notch allowing a blade of the rotor to perform flapping motion.
    Type: Application
    Filed: September 28, 2016
    Publication date: March 30, 2017
    Applicant: AIRBUS HELICOPTERS
    Inventors: David ALFANO, Damien DESVIGNE, Raphael FUKARI
  • Publication number: 20170088259
    Abstract: A method involves operating an aerial vehicle in a hover-flight orientation. The aerial vehicle is connected to a tether that defines a tether sphere having a radius based on a length of the tether, and the tether is connected to a ground station. The method involves positioning the aerial vehicle at a first location that is substantially on the tether sphere. The method involves transitioning the aerial vehicle from the hover-flight orientation to a forward-flight orientation, such that the aerial vehicle moves from the tether sphere. And the method involves operating the aerial vehicle in the forward-flight orientation to ascend at an angle of ascent to a second location that is substantially on the tether sphere. The first and second locations are substantially downwind of the ground station.
    Type: Application
    Filed: December 12, 2016
    Publication date: March 30, 2017
    Inventors: Erik Christopher Chubb, Damon Vander Lind
  • Publication number: 20170088260
    Abstract: An airfoil configured for low speed performance in an unmanned aerial vehicle includes an upper surface having an upper surface portion with a top local surface angle magnitude of less than 5 degrees at a subsection of a chord and a lower surface having a lower surface portion with a bottom local surface angle magnitude of less than 5 degrees at the subsection of the chord. The chord is defined by a line starting at a leading edge of the airfoil and extending to a trailing edge of the airfoil.
    Type: Application
    Filed: September 25, 2015
    Publication date: March 30, 2017
    Applicant: The Boeing Company
    Inventors: Bradley M. Hopping, Timothy M. Garrett
  • Publication number: 20170088261
    Abstract: An unmanned aerial vehicle (UAV) having at least one sensor for detecting the presence of a survivor in a search and rescue area. The at least one sensor is preferably an ultra-wide band (UWB) transceiver sensor. The UAV includes a UAV data link transceiver for wirelessly communicating information concerning the survivor to a command center.
    Type: Application
    Filed: September 29, 2015
    Publication date: March 30, 2017
    Inventors: Melwyn F. Sequeira, Mohammad Mohiuddin
  • Publication number: 20170088262
    Abstract: An automated quick release mechanism for a three-ring release comprising a pneumatic or hydraulic cylinder with a hardened metal pin engaging a loop of the three ring release. When engaged with the three-ring release, the pin is held in an extended position to engage the loop of the release. Actuation to withdraw the pin disengages the pin from the string loop, allowing the three-ring release to open.
    Type: Application
    Filed: August 1, 2016
    Publication date: March 30, 2017
    Applicant: The United States of America as Represented by the Secretary of Agriculture
    Inventor: Kevin Brown
  • Publication number: 20170088263
    Abstract: The present disclosure includes cargo loading systems and components including cargo systems utilizing one or more air cushions to elevate one or more cargo shuttles. The air cushions are formed by one or more air curtains, which include pressure compensating seals. The seals allow the air curtains to contact and seal against a floor panel, reducing leakage from the air cushion.
    Type: Application
    Filed: December 9, 2016
    Publication date: March 30, 2017
    Applicant: Goodrich Corporation
    Inventor: Richard Himmelmann
  • Publication number: 20170088264
    Abstract: An aircraft passenger service unit kit comprises an overhead passenger service unit panel including at least one hinge pin extending along an edge portion of the overhead passenger service unit panel; and an elastic fixing element for fixing the overhead passenger service unit panel to an aircraft support structure. The fixing element comprises at least one first end, which is configured for rotatably connecting with the at least one hinge pin; and at least one opposing second end, which is configured for engaging with a mounting rail of the aircraft support structure. The overhead passenger service unit panel further comprises a forcing element, which is configured for acting onto the fixing element generating a tension within the fixing element for securely fixing the at least one second end of the fixing element to the mounting rail.
    Type: Application
    Filed: September 27, 2016
    Publication date: March 30, 2017
    Inventors: Andre HESSLING-VON HEIMENDAHL, Anil Kumar JHA
  • Publication number: 20170088265
    Abstract: A seatback holder for cellular phones or iPads® configured to mount to the top ledge of a seat pocket or the top ledge of a tray tabletop on an aircraft seatback to hold a cellular phone or an iPad® at eye level while viewing video entertainment hands free.
    Type: Application
    Filed: February 11, 2016
    Publication date: March 30, 2017
    Inventor: David Douglas Brick
  • Publication number: 20170088266
    Abstract: A seat integrating a loudspeaker system includes a seat having a seat body with a horizontally oriented seat bottom and a seat back secured thereto. The seat back includes an upper end and a lower end, wherein the lower end is positioned adjacent the seat bottom. The loudspeaker system includes a sound assembly mounted within the seat for selective movement between a storage orientation in which the sound assembly is housed and hidden within a support housing mounted along the seat and a use orientation extending from the support housing in which the sound assembly is positioned for use.
    Type: Application
    Filed: December 12, 2016
    Publication date: March 30, 2017
    Inventor: Dennis A. Tracy
  • Publication number: 20170088267
    Abstract: Passenger seating arrangements for an airliner or other conveyance including a plurality of individual suites arranged into longitudinal columns. Lateral aisles extending from longitudinal aisles lead to branch aisles that provide access to suites spaced apart from the longitudinal aisles, and each lateral aisle can be shared to provide access to two outboard suites. Suites are arranged to maximize seating density and privacy, and each suite is equipped with premium features and amenities for use by occupants during flight.
    Type: Application
    Filed: September 29, 2016
    Publication date: March 30, 2017
    Inventors: Mark B. Dowty, Tracy N. Pence, Matt Round, Vien McArthur Nguyen, Martin Hong Lun Mo, Erik Eivind Sutton Nilsen, Anthony Michael Charles, Brian Jeremy Conner, Harry Howard Hanson
  • Publication number: 20170088268
    Abstract: Described are passenger seat armrests and consoles (1) having laterally translating armrest doors (200) that open and close to allow for deployment and stowage of tray tables (300). The armrest doors may be guided through their translation by slides or a linkage that controls their motion. The armrest doors may also translate in two-dimensions, incorporating a vertical translation as well as a lateral translation. The resulting motion allows for better placement of the deployable tray tables within the armrest or console and a reduction in wasted space. The passenger seat armrests may also incorporate cocktail trays (100) that can be integrated into the armrest doors or the armrest or console itself.
    Type: Application
    Filed: April 2, 2015
    Publication date: March 30, 2017
    Applicant: Zodiac Seats US LLC
    Inventors: Marc W. Kinard, Ty Parker, Raul G. Reyes, John D. Allen
  • Publication number: 20170088269
    Abstract: The vehicle seat of the present disclosure has a base unit, a tray, and a connection terminal. The base unit is disposed on a rear side of the backrest and has a storage section. The tray has a through-hole or a notch which a connection device of a predetermined size passes and is disposed so as to be movable between a storage position located in the storage section of the base unit and an open position of the tray unfolded from the storage position. The connection terminal that is disposed on the base unit at a position that meets with the through-hole or the notch of the tray located at the storage position.
    Type: Application
    Filed: September 15, 2016
    Publication date: March 30, 2017
    Inventors: GOICHI MATSUDA, KANAME TOMITA
  • Publication number: 20170088270
    Abstract: An outflow valve is provided. The outflow valve includes a frame and a first door rotatably coupled to the frame. The first door has a first side opposite a second side and a bellmouth. The bellmouth is defined by a super-ellipse, with a major axis of the super-ellipse substantially parallel to the second side and a minor axis of the super-ellipse substantially perpendicular to the second side. The outflow valve also includes a second door rotatably coupled to the frame. The first door and the second door are substantially simultaneously movable between at least a first position and a second position.
    Type: Application
    Filed: September 24, 2015
    Publication date: March 30, 2017
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Daniel Brown, Yogendra Yogi Sheoran, Bruce Dan Bouldin, William Facinelli
  • Publication number: 20170088271
    Abstract: Systems and methods are disclosed for providing a controlled temperature in a control volume. Such systems include a main chamber (defining the control volume), a mixing chamber and a gasflow source. The mixing chamber is in selective fluid communication with the main chamber, and has at least one mixing chamber inlet, and a ram air inlet for allowing ram airflow at a first temperature to be channeled into the mixing chamber. The gasflow source provides a source gasflow at a greater, second temperature to the mixing chamber. The mixing chamber provides the mixing chamber outflow at a third temperature by selectively allowing the ram airflow and the source gasflow in the mixing chamber to mix therein, or, by selectively allowing the ram airflow in the mixing chamber to flow to the main chamber (in absence of source gasflow). A controller is operative to provide a desired level for the third temperature.
    Type: Application
    Filed: March 25, 2015
    Publication date: March 30, 2017
    Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
    Inventors: Alexander Barladian, Arie Smolansky
  • Publication number: 20170088272
    Abstract: Aspects of the present disclosure relate to systems and methods for automated fire detection, such as in aircraft galleys, or other areas where power sources may result in fire or smoke. The system includes one or more detectors to monitor for smoke or fire in an aircraft galley. Upon detection of smoke or fire, a signal is sent from the one or more detectors to a controller. In response to the incoming signal, the controller sends a signal to a galley power source. The signal provided to the galley power source ceases the application of power to one or more devices located in the galley, extinguishing the source of the fire or smoke. The controller may also send a notification signal to alert the crew to the potential fire hazard. A method of operation is also disclosed.
    Type: Application
    Filed: September 28, 2015
    Publication date: March 30, 2017
    Inventors: Charles Steven Meis, Rachel Meis, Jon Christopher Meis
  • Publication number: 20170088273
    Abstract: According to various embodiments, disclosed is a slide configured to be supported on a ground surface at a slide angle, comprising a support structure, a sliding surface supported by the support structure, and a weakened support region in the support structure, wherein the weakened support region enables the slide to buckle and the slide angle to change in response to a bending load imposed on the slide. According to various embodiments, the slide is an aircraft evacuation slide.
    Type: Application
    Filed: September 24, 2015
    Publication date: March 30, 2017
    Applicant: GOODRICH CORPORATION
    Inventors: Craig Erwin Prevost, Steven Evans
  • Publication number: 20170088274
    Abstract: An evacuation system is provided. The system may comprise a girt coupled to a door sill and an evacuation slide. The evacuation slide may comprise a head end coupled to the girt, an extension, a hinge portion coupled between the head end and the extension, and a lane diverter coupled to the evacuation slide. A method is also provided. The method may include opening a door to expose a door sill, inflating the evacuation slide with the evacuation slide coupled to the door sill, bending a hinge portion of the slide in response to a door sill height being less than or equal to a predetermined height, and redirecting a slide lane to a side exit.
    Type: Application
    Filed: September 25, 2015
    Publication date: March 30, 2017
    Applicant: GOODRICH CORPORATION
    Inventors: Drew Hartman, Jaro Volny
  • Publication number: 20170088275
    Abstract: A turbine engine nozzle can include a primary outer wall extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, to form a core nozzle. The turbine engine nozzle also includes a single engine core cowl extending from the engine core area to an annular cowl terminus to form a core compartment vent nozzle. The core compartment vent nozzle exhausts air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall.
    Type: Application
    Filed: September 30, 2015
    Publication date: March 30, 2017
    Inventors: Robert H. Willie, Paul R. Tretow, David F. Cerra
  • Publication number: 20170088276
    Abstract: A propulsion assembly for an aircraft, the assembly including a turbojet having at least one unducted propulsive propeller, and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having a streamlined profile defined by two opposite side faces extending transversely between a leading edge and a trailing edge. The pylon includes a plurality of blow nozzles situated in the vicinity of its trailing edge and configured to blow air taken from a pressurized portion of the turbojet, the blow nozzles being positioned over at least a fraction of the trailing edge of the pylon that extends longitudinally facing at least a portion of the propeller. A method of reducing the noise generated by a pylon attaching a turbojet to an aircraft is presented.
    Type: Application
    Filed: June 15, 2016
    Publication date: March 30, 2017
    Inventors: Mathieu Simon Paul GRUBER, Timothy DELTEIL Mc WILLIAMS
  • Publication number: 20170088277
    Abstract: This disclosure generally relates to a hybrid solid-state propulsion system for aerial vehicles which includes a thermoelectric generator. The thermoelectric generator includes a first heat exchanger disposed within an exhaust duct of an unmanned aerial vehicle. The thermoelectric generator further includes a first ceramic layer disposed on the first heat exchanger and a first and second metal tab bonded to the first ceramic layer. The thermoelectric generator further includes a second metal tab bonded to a second ceramic layer. At least one N-type thermoelectric leg is disposed between the first metal tab bonded to the first ceramic layer and the metal tab bonded to the second ceramic layer. Further, at least one P-type thermoelectric leg is disposed between the second metal tab bonded to the first ceramic layer and the metal tab bonded to the second ceramic layer.
    Type: Application
    Filed: May 24, 2016
    Publication date: March 30, 2017
    Applicant: Reebeez, Inc
    Inventor: Ankita Ghoshal
  • Publication number: 20170088278
    Abstract: Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.
    Type: Application
    Filed: September 24, 2015
    Publication date: March 30, 2017
    Inventors: Julio Antonio Beltrami DA SILVA, Clovis Augusto Eça FERREIRA, Wanderley MONTORO, Alberto Dei CASTELLI, José Darci FLOR, JR., Marcelo NOGUEIRA, Cleber SOARES
  • Publication number: 20170088279
    Abstract: Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box. The upper pylon connection member and the lower pylon connection box respectively define opposed lower and upper mounting surfaces which establish a mounting plane that slopes downwardly and rearwardly relative to aircraft travel direction. At least one connector assembly connects the upper pylon connection member and a lower pylon connection box to one another at the opposed respective lower and upper mounting surfaces thereof.
    Type: Application
    Filed: September 24, 2015
    Publication date: March 30, 2017
    Inventors: Alberto Dei CASTELLI, Clovis Augusto Eça FERREIRA, Wanderley MONTORO, Aldemiro Lorenzini FILHO, Carlos Alberto BONES, JR., Juliano DE OLIVEIRA
  • Publication number: 20170088280
    Abstract: A motor mount assembly is provided for coupling a propeller motor to a body of an unmanned aerial vehicle (UAV). The motor mount assembly includes a floating portion and acts to attenuate frequencies of vibration from the propeller motor during operation, which modifies the corresponding noise that is produced and reduces stresses on the various components. The floating portion is surrounded on all sides by isolation portions (e.g., made of elastomers or other materials) that are held within a casing that attaches to the body of the UAV. In one implementation, the motor mount assembly is modular such that one or more of the isolation portions may be replaced with different isolation portions (e.g., having different attenuation properties), depending on the direction and nature of the vibrations from the propeller motor that are to be attenuated for a particular application.
    Type: Application
    Filed: September 25, 2015
    Publication date: March 30, 2017
    Inventors: Brian C. Beckman, Matthew Lee Skeels
  • Publication number: 20170088281
    Abstract: A device for regulating the speed of rotation of at least one main rotor of a rotorcraft, which speed is known as the speed NR. Such a rotorcraft comprises at least one manual flight control member for delivering a collective pitch control setpoint C for the blades of the at least one main rotor, the control setpoint C being a function of a current position of the at least one control member; and detector means enabling a current state to be detected from at least two distinct states of the rotorcraft, namely a “ground” state in which the rotorcraft is in contact with the ground, at least in part, and a “flight” state in which the rotorcraft is at least being sustained in the air.
    Type: Application
    Filed: September 22, 2016
    Publication date: March 30, 2017
    Applicant: AIRBUS HELICOPTERS
    Inventors: Jean-Baptiste VALLART, Setareh TAHERI, Nicolas CERTAIN
  • Publication number: 20170088282
    Abstract: Systems and methods provide for a nitrogen generation and oxygen distribution system. According to one aspect, the system includes an NGS and an oxygen distribution processor coupled to the NGS. The NGS creates nitrogen enriched air as the primary product for fuel tank use, and oxygen enriched air as a secondary product. The oxygen distribution processor is operative to determine a number of flight parameters, and from those parameters, provide an oxygen distribution command to an oxygen distribution valve in order to prevent the oxygen enriched air from being distributed, to route the oxygen enriched air to the ambient environment, or to route the oxygen enriched air to an aircraft engine to increase combustion efficiency.
    Type: Application
    Filed: September 25, 2015
    Publication date: March 30, 2017
    Inventors: Richard J. Loftis, Andrew L. Armatorio, Colin W. Hart
  • Publication number: 20170088283
    Abstract: An aircraft propeller drive system has a gear to be driven by an engine and having a first plurality of teeth. A torsion bar has a first end driven by the gear and a second end rotatable relative to the first end about a torsion axis by a torsion angle. An output shaft is driven by the second end and is adapted for connection to a propeller. A clutch has a driven member rotationally fixed to the output shaft and a driving member having a second plurality of teeth. The first and second pluralities of teeth engage each other when a variation in the torsion angle from a mean torsion angle is greater than a predetermined angle. Torque is transferred between the gear and the output shaft via the clutch when the first and second pluralities of teeth engage each other.
    Type: Application
    Filed: September 30, 2015
    Publication date: March 30, 2017
    Inventors: Harald MITTERMAIER, Johann BAYERL, Michael DOPONA, Thomas BAUMGARTNER
  • Publication number: 20170088284
    Abstract: A flight deck display that represents the overall health of the airplane by combining energy state, system state and configuration state into one integrated representation that is triggered by the on-board engine indication and crew alerting system. The computer system for controlling the display unit is configured to display an airplane status indicator in the form of a symbolic representation of the airplane that persists across displays. The status indicator shows the energy state of the airplane and how energy is being added or subtracted from it in terms of altitude, airspeed, thrust, wind, etc. As the airplane gains energy, there is a projection of excess energy shown in front of the airplane. As the airplane loses energy, an alerting indicator will appear around the airplane symbol if the performance of the airplane becomes is too low.
    Type: Application
    Filed: September 25, 2015
    Publication date: March 30, 2017
    Applicant: THE BOEING COMPANY
    Inventor: Barbara E. Holder
  • Publication number: 20170088285
    Abstract: Aircraft instrumentation systems and controllers are provided. An aircraft instrumentation system includes a display and a controller. The controller is configured to monitor an electronic circuit breaker (ECB) status of each of a plurality of aircraft systems. The controller is further configured to generate, for each of the plurality of aircraft systems, a visual indicator that indicates the ECB status. The controller is yet further configured to generate an image arrangement that includes the visual indicator for each of the plurality of aircraft systems and to generate a signal that causes a display to present the image arrangement.
    Type: Application
    Filed: September 29, 2015
    Publication date: March 30, 2017
    Inventors: Carl Edward Wischmeyer, Frank Manochio
  • Publication number: 20170088286
    Abstract: An emergency lighting system (ELS) for an aircraft has a capacitor, at least one of an onboard power system and a ground power unit configured to charge the capacitor, and a light emitting diode (LED) selectively powered by the capacitor.
    Type: Application
    Filed: September 30, 2015
    Publication date: March 30, 2017
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventor: Erik John Oltheten
  • Publication number: 20170088287
    Abstract: A tail dock anti-collision system for augmenting positioning of an aircraft in a maintenance facility which comprises lateral alignment sensors disposed on opposing sides of the aircraft and a backup tracking sensor directed toward the tail section. A processor, for example a programmable logic controller, is coupled to, and operatively controls, the sensors to provide an indication to a principal guide of the aircraft docking procedure of the relative position of the aircraft with respect to a centerline and platform of the maintenance facility.
    Type: Application
    Filed: September 22, 2016
    Publication date: March 30, 2017
    Inventors: Bruce Clifford, Neil T. Heeke
  • Publication number: 20170088288
    Abstract: A multi-zone battery station is provided, comprising a plurality of landing areas configured to support a UAV. The battery station may permit battery life to be reloaded onto a UAV, which may include recharging a battery of the UAV or exchanging the UAV battery for a new battery. The different zones may accommodate different UAV types, different battery types, or operate in accordance with different energy provision rules. A marker may be provided on a landing area to aid in guiding the UAV to an appropriate landing area.
    Type: Application
    Filed: December 12, 2016
    Publication date: March 30, 2017
    Inventor: Mingyu Wang
  • Publication number: 20170088289
    Abstract: A method and kit for detecting leaks in an aircraft wing (5) including: providing an aircraft wing structure having at an outboard end a wing tip (11) and at an inboard end a wing root (9) and at least one rib disposed between the wing root (9) and the wing tip (11), there being in a first rib section (13) of the wing (5) a first rib (19) closest to the wing root (9); placing a gas-impermeable bladder (43) over the wing root (9); forming a gas-tight circumferential seal between the bladder (43) and an outer surface of the wing (5) in the first rib section (13); introducing a gas into the aircraft wing (5); and sensing for leaks in the aircraft wing (5).
    Type: Application
    Filed: September 26, 2016
    Publication date: March 30, 2017
    Inventor: Giovanni TOVAZZI
  • Publication number: 20170088290
    Abstract: A remote computing system is described that includes at least one processor and at least one module. The at least one module is operable by the at least one processor to receive first operational data collected by a first line-replaceable-unit of a first aircraft during flight operations of the first aircraft, and receive second operational data collected by at least one second line-replaceable-unit of at least one second aircraft during flight operations of the at least one second aircraft. The at least one module is further operable by the at least one processor to predict, based at least in part on the first operational data and the second operational data, a failure condition associated with the first line-replaceable-unit of the first aircraft, and output, based on the impending failure condition, an indication of the predicted failure condition.
    Type: Application
    Filed: December 14, 2016
    Publication date: March 30, 2017
    Inventor: Roland Szeto
  • Publication number: 20170088291
    Abstract: A gyroscopic orbiter with vertical takeoff and vertical landing capabilities can transition between different functional modes while in-flight. The orbiter typically includes a fuselage, a front boom, a front propulsion unit, a rear boom, and a rear propulsion unit. The front boom is mounted at two pivot points to a bow of the fuselage by the front boom. The rear boom is mounted at two pivot points to a stern of the fuselage by the rear boom. One functional mode is the vertical takeoff and landing mode, wherein the propulsion units are oriented parallel to each other and are directed upward. Another functional mode is the shuttle mode, wherein the propulsion units are oriented at an angle with each other, and the front propulsion unit is directed forward. Another functional mode is the high speed mode, wherein the propulsion units are oriented collinear with a roll axis of the fuselage.
    Type: Application
    Filed: June 16, 2016
    Publication date: March 30, 2017
    Inventor: Thomas Norman Hesse
  • Publication number: 20170088292
    Abstract: A deployable assembly comprises a supporting structure, a set of panels, each being linked to the adjacent panel by a hinge defining an intermediate axis of rotation, capable of switching from a stowed configuration in which the panels are folded one on top of the other to a deployed configuration, by rotation of the panels about the respective intermediate axes of rotation, wherein the panels are arranged substantially in the same plane, an articulation device defining a main axis of rotation of the set of panels relative to the supporting structure. The set of panels is rotationally mobile about the intermediate axes of rotation and the main axis of rotation to switch from the stowed configuration to the deployed configuration and the set of panels is only rotationally mobile about the main axis of rotation in deployed configuration to orient the set of panels relative to the supporting structure.
    Type: Application
    Filed: September 12, 2016
    Publication date: March 30, 2017
    Inventors: Julien DUCARNE, Julien GRAVE, Xavier REUTENAUER
  • Publication number: 20170088293
    Abstract: A space vehicle engine (10) comprising a chemical thruster having a nozzle (30) for ejecting combustion gas, together with a Hall effect thruster. The engine is arranged in such a manner that the nozzle serves as the ejection channel for particles ejected by the Hall effect thruster when it is in operation. The engine can deliver high thrust with low specific impulse or relatively low thrust with large specific impulse.
    Type: Application
    Filed: May 13, 2015
    Publication date: March 30, 2017
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Stéphan Joseph ZURBACH, Frédéric Raphaël Jean MARCHANDISE
  • Publication number: 20170088294
    Abstract: Thermal control louvers for CubeSats or small spacecraft may include a plurality of springs attached to a back panel of the thermal control louvers. The thermal control louvers may also include a front panel, which includes at least two end panels interlocked with one or more middle panels. The front panel may secure the springs, shafts, and flaps to the back panel.
    Type: Application
    Filed: September 28, 2015
    Publication date: March 30, 2017
    Inventor: ALLISON L. WILLINGHAM