Patents Issued in January 26, 2017
  • Publication number: 20170021906
    Abstract: A portable propulsion system for a watercraft may include a shaft, a propeller, an outer casing, and a flexible strap. The shaft may have a prop end section, a drive end section, and a rotational axis extending from the prop end section to the drive end section. The propeller may be connected to the prop end section of the shaft. The drive end section may be configured for removable connection to a driver for rotation of the propeller via rotation of the shaft about the rotational axis to propel the watercraft. The outer casing may be disposed around the shaft. The flexible strap may have first and second end sections connected to the outer casing in respective first and second regions.
    Type: Application
    Filed: October 3, 2016
    Publication date: January 26, 2017
    Inventor: Gene L. Keough
  • Publication number: 20170021907
    Abstract: The purpose of this invention, which is referred to as a vacuustat, is to generate buoyancy in the atmosphere by means of an evacuated or partially evacuated container, rather than by using a lighter-than-air lifting gas such as hydrogen or helium. This particular vacuustat design comprises a flexible airtight membrane supported by a fractal tensegrity internal structure consisting of a relatively small mass of compressive members forced into higher-order buckling modes through use of tension members. The advantages of such a design over conventional aerostats include superior buoyancy control for ascent and descent, greatly increased flight endurance, and cost-effectiveness in operation. This particular vacuustat design has a much greater lifting efficiency than previous designs, and should also be easier and more cost-effective to manufacture.
    Type: Application
    Filed: July 23, 2015
    Publication date: January 26, 2017
    Inventor: Nathan Rapport
  • Publication number: 20170021908
    Abstract: A pressure bulkhead (1) for an aircraft fuselage (3) having a sandwich structure (5) which defines a central axis (9) and which extends between a circumferential edge area (7), wherein the sandwich structure (5) includes an inner cover layer (13), an outer cover layer (17), and a core layer (19), which extends between the inner and outer cover layers (13, 17) and connects them.
    Type: Application
    Filed: July 22, 2016
    Publication date: January 26, 2017
    Inventors: Paul JORN, Karim GRASE
  • Publication number: 20170021909
    Abstract: A ball-lock type fastening device for connecting a work piece to a structure is disclosed. The fastening device includes a number of features designed to improve the reliability, repeatability and strength of the locking mechanism compared to traditional ball-lock fasteners. The features include the shape of the locking balls, the shape of the retention housing which engages the locking balls, and mechanisms for controlling deployment and retraction of the locking balls.
    Type: Application
    Filed: July 20, 2015
    Publication date: January 26, 2017
    Inventors: MATTHEW A. NEAL, STEPHEN R. BERG, MICHAEL J. EHRLICH, CHARLES R. SMITH
  • Publication number: 20170021910
    Abstract: A sandwich structure with an outer cover layer, inner cover layer, core layer, and pins extending through the core layer. The sandwich structure has a large core thickness resistant to crack formation and to detachment of the cover layers from the core layer. An anchor layer is between the outer and inner cover layers and divides the core layer, at least in areas, into an outer core layer section and inner core layer section. An outer group of pins extends through the outer core layer section and an inner group of pins extends through the inner core layer section. The outer group pins are connected to the anchor layer with their first end and to the outer cover layer with their opposite second end, and the inner group pins are connected to the anchor layer with their first end and to the inner cover layer with their opposite second end.
    Type: Application
    Filed: July 22, 2016
    Publication date: January 26, 2017
    Inventors: Paul Joern, Karim Grase
  • Publication number: 20170021911
    Abstract: A coupling device for supporting a first wing section against a second wing section of an aircraft, and configured for passive flight load alleviation includes a housing including a chamber including a first portion and a second portion and filled with a fluid, a piston device movably arranged in the chamber and separating the first portion from the second portion in a fluid tight manner, a first fluid pathway connecting the first portion to the second portion, a first pressure relief valve arranged in the first fluid pathway and blocking the first fluid pathway, if the pressure in the second portion is smaller than a first relief pressure and opening the first fluid pathway, if the pressure in the second portion is greater than the first relief pressure. In addition, the coupling device can be used to actuate the second wing section against the first wing section.
    Type: Application
    Filed: July 19, 2016
    Publication date: January 26, 2017
    Applicants: Airbus Defence and Space GmbH, Airbus Group Limited
    Inventors: Andreas Wildschek, Stefan Storm, Stephen Rolston, Martin Herring
  • Publication number: 20170021912
    Abstract: A fairing system for a rotary wing aircraft is provided including a shaft fairing mounted for rotation about a first axis of rotation. A de-rotation system contained with the shaft fairing includes a toroidal continuously variable transmission configured to control the rotation of the shaft fairing about the first axis of rotation. A position control system includes at least one position sensor and a controller. The at least one position sensor is configured to monitor a position of the shaft fairing relative to the first axis of rotation. The controller is operably coupled to the at least one position sensor and the de-rotation system. The controller is configured to adjust a gear ratio of the toroidal continuously variable transmission in response to a sensed position of the shaft fairing.
    Type: Application
    Filed: December 19, 2013
    Publication date: January 26, 2017
    Inventor: John C. Cox
  • Publication number: 20170021913
    Abstract: The device for automatic management of an actuator controlled by a servo-valve, includes a sensor for measuring the actual value of a parameter at the output of the actuator for a given control command, a computation unit for computing a theoretical value of said parameter, by applying the control command to a nominal performance model which models the operation of the actuator exhibiting nominal performance, a computation unit for computing the difference between the measured actual value of the parameter and the computed theoretical value of said parameter, a control unit for computing an adapted gain as a function of this difference, and a link for applying the adapted gain to the servo-valve for it to use it as gain value, so as to allow the actuator to restore nominal performance.
    Type: Application
    Filed: July 18, 2016
    Publication date: January 26, 2017
    Applicant: Airbus Operations S.A.S.
    Inventor: Pierre Fabre
  • Publication number: 20170021914
    Abstract: An improved flight control system comprising a flight control surface of an aircraft or spacecraft, a first optical fiber having a fiber optic sensor configured to sense a first parameter associated with the flight control surface at a first position and a second fiber optic sensor configured to sense a second parameter associated with the flight control surface at a second location, an interrogator connected to the first optical fiber and configured to convert the sensed parameters from both the first fiber optic sensor and the second fiber optic sensor into an electrical signal, and the interrogator communicating with a flight control computer.
    Type: Application
    Filed: December 8, 2014
    Publication date: January 26, 2017
    Inventors: George L. Small, Glynn Lloyd, Seth E. Gitnes
  • Publication number: 20170021915
    Abstract: Apparatus, methods, and systems for adjusting a center of mass of a drone may include a balance track and a repositionable weight. The balance track may be configured to extend outwardly from a central region of the drone. The balance track may include a plurality of weight-balance fixation positions. The repositionable weight may be configured to be secured at any one of the plurality of weight-balance fixation positions. In various embodiments the repositionable weight may include an electronic component. Various embodiments may include a another balance track configured to extend outwardly from the central region along a second axis that is different from a first axis of the other balance track.
    Type: Application
    Filed: October 5, 2016
    Publication date: January 26, 2017
    Inventors: Brad Lee Vaughn, Charles Wheeler Sweet, Vincent Kemler, Aine Mary Shivnan, Kaustubh Balkrishna Gondkar, James York Wilson, Michael Franco Taveira, Donald Hutson
  • Publication number: 20170021916
    Abstract: A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.
    Type: Application
    Filed: April 5, 2016
    Publication date: January 26, 2017
    Applicant: Icon Aircraft, Inc.
    Inventors: Matthew Gionta, Jon Karkow, John Roncz, Dieter Koehler, David Lednicer
  • Publication number: 20170021917
    Abstract: Aerodynamically oriented thermal protection system (TPS) for hypersonic aerospace vehicles which is based on a suitable spike—forebody configuration. The conical forebody semi-angle is much smaller than the cone-shaped spike tip semi-angle. As a result a separated recirculating flow is established in the region after the spike tip and a series of expansion waves are formed near the forebody—main body intersection. The separated recirculating flow shields the forebody from heat following the shock wave, and the expansion waves prevent high temperatures in the area of the forebody—main body intersection and beyond. Due to the spike tip large shock wave angle the whole of the aerospace vehicle lies within the spike tip shock wave cone and, thus, shock wave—shock wave interactions are avoided. The proposed spike—forebody configuration substantially reduces aerodynamic heating and, therefore, a conventional TPS with the associated mass penalty, and safety, reliability, maintenance and cost drawbacks is avoided.
    Type: Application
    Filed: April 5, 2016
    Publication date: January 26, 2017
    Inventor: NIKOLAOS KEHAYAS
  • Publication number: 20170021918
    Abstract: A system and method for damage detection and for evaluating the real operation conditions for structural platforms using structural health monitoring is integrated to a system and method that permits for the platform to provide a flexible geometric control considering a self-adapting morphing which is capable of providing better operating structural platform performance.
    Type: Application
    Filed: July 24, 2015
    Publication date: January 26, 2017
    Inventors: Paulo Anchieta DA SILVA, Tomaz LAZANHA, Ricardo Pinheiro RULLI, Fernando DOTTA
  • Publication number: 20170021919
    Abstract: A landing gear box of an aircraft comprising a front door with independent opening and a rear door with opening mechanically connected to the landing gear, including an orifice in the rear door provided with a closure member and a drive mechanism allowing movement of this closure member independently of any movement of the rear door.
    Type: Application
    Filed: July 21, 2016
    Publication date: January 26, 2017
    Inventor: Francis Dazet
  • Publication number: 20170021920
    Abstract: Systems and methods are disclosed for aircraft braking and taxiing systems for use in, for example, an aircraft. In this regard, a system may comprise an electric motor and a clutch. The electric motor may include a first output shaft and a second output shaft. The clutch may selectively engaging the motor to at least one of a driver transmission and a brake transmission, wherein, in response to engagement with the driver transmission, the electric motor drives, exclusively, an aircraft wheel via the first output shaft, wherein, in response to engagement with the brake transmission, the electric motor drives, exclusively, a brake clamping system via the second output shaft to apply force to an aircraft brake disk stack.
    Type: Application
    Filed: July 20, 2015
    Publication date: January 26, 2017
    Applicant: GOODRICH CORPORATION
    Inventors: David Drennen, Kevin Rehfus
  • Publication number: 20170021921
    Abstract: A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly.
    Type: Application
    Filed: July 22, 2016
    Publication date: January 26, 2017
    Applicant: Borealis Technical Limited
    Inventors: Isaiah W. Cox, Joseph J. Cox, Jonathan S. Edelson, Yonatan Rotenberg, John Hanson
  • Publication number: 20170021922
    Abstract: Embodiments are directed to obtaining data from at least one sensor, processing, by a processor, the data to determine an independent rotor phase lag for each of a plurality of axes associated with a rotorcraft, and issuing, by the processor, at least one command to provide for on-axis moments in accordance with the independent rotor phase lag for each of the axes.
    Type: Application
    Filed: April 2, 2014
    Publication date: January 26, 2017
    Inventors: Anthony Litwinowicz, Kenneth S. Wittmer, Matthew T. Luszcz
  • Publication number: 20170021923
    Abstract: A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) system including: a rearward facing tang extending from a rear fuselage portion of a VTOL UAV; one or more metallic contacts disposed on an exterior surface of the tang; a UAV pod including a landing surface; and an opening disposed in the landing surface to receive the tang.
    Type: Application
    Filed: February 11, 2016
    Publication date: January 26, 2017
    Inventors: Christopher Eugene Fisher, Jason Sidharthadev Mukherjee, William Arden Lott
  • Publication number: 20170021924
    Abstract: A tail sitter aircraft is capable of forward flight and hover operations. The tail sitter aircraft includes a wing and first and second prop-nacelles supportively disposed on the wing. Each of the first and second prop-nacelles includes an articulable rotor, which is rotatable about variable rotational axes and which includes blades that are collectively and cyclically controllable in both forward flight and hover regimes.
    Type: Application
    Filed: May 18, 2016
    Publication date: January 26, 2017
    Inventors: Stephen Kubik, Joseph T. Driscoll, Frank P. D'Anna, Mark R. Alber, Timothy Fred Lauder, Cody Fegely
  • Publication number: 20170021925
    Abstract: Methods and systems for an Automated Readiness Evaluation System (ARES), which is adapted for use with unmanned aircraft systems (UAS). The ARES (and UAS with such an ARES) is configured for a particular task or application selected by the user based upon their level of specific knowledge. The system may include: hardware components with communication protocols; a task, module data, and skill level repository; a user device; and an optional base system. Methods are provided for configuration, calibration, error checking, and operation of a UAS whereby the ARES serves as a mission planner by calculating the mission parameters for a user-selected task to minimize mission failure by determining the variables for task completion.
    Type: Application
    Filed: June 28, 2016
    Publication date: January 26, 2017
    Inventors: ERRIN T. WELLER, JEFFREY B. FRANKLIN
  • Publication number: 20170021926
    Abstract: A personal propulsion device adapted to achieve flight by discharging a fluid, including a passenger assembly adapted to support an individual person; at least one fluid discharge nozzle coupled to the passenger assembly, where the nozzle is movable with respect to the passenger assembly to define a range of motion, and where the nozzle is biased towards at least one position in the range of motion.
    Type: Application
    Filed: October 6, 2016
    Publication date: January 26, 2017
    Inventors: Raymond Li, Nicholas R. Lewis
  • Publication number: 20170021927
    Abstract: In a general aspect, a device for attaching a towed device to an aircraft in flight can include an attachment cable secured to the towed device. The attachment cable can have one end forming a closed loop and including a loop head. The device can also include a first attachment element secured to the loop head of the attachment cable, The first attachment element can include first electrical connectors. The device can further include a towing cable attached to the aircraft and a second attachment element attached to one end of the towing cable. The second attachment element can be configured to cooperate mechanically and electrically with the first attachment element. The second attachment element can include second electrical connectors configured to cooperate with the first electrical connectors. The device can still further include fasteners or guides configured to hold the loop head of the attachment cable off the ground.
    Type: Application
    Filed: October 6, 2016
    Publication date: January 26, 2017
    Inventor: Alexis GIORDANA
  • Publication number: 20170021928
    Abstract: A mounting arm assembly movable between stowed and deployed configurations, includes a pivot arm pivotally engaging an armrest of a seat; a tilt arm engaging the pivot arm; and a mount engaging the tilt arm for supporting a personal electronic device.
    Type: Application
    Filed: June 24, 2016
    Publication date: January 26, 2017
    Inventor: Johnny A. Satterfield
  • Publication number: 20170021929
    Abstract: In a preferred embodiment, a modular lavatory system for replacing a conventional lavatory monument in an aircraft cabin includes a base lavatory module including a fore sidewall, an aft sidewall, and an aisle wall that form a housing enclosing a toilet unit. A first sidewall of the fore sidewall and the aft sidewall may include a widening region positioned above a passenger seat headrest height. The modular lavatory system may include at least two interchangeable modules configured for mounting against the other sidewall of the base lavatory module. A footprint of the base lavatory module may be smaller than the conventional lavatory monument footprint, such that an extra cabin space is created proximate the other sidewall of the base lavatory module after replacement of the conventional lavatory monument with the modular lavatory system. The at least two interchangeable modules may each be dimensioned for installation within the extra space.
    Type: Application
    Filed: October 7, 2016
    Publication date: January 26, 2017
    Applicant: B/E AEROSPACE, INC
    Inventors: Jefferey MCKEE, Trevor SKELLY
  • Publication number: 20170021930
    Abstract: In a preferred embodiment, a cradle recline mechanism for an aircraft passenger seat includes a guide mechanism for guiding a seat bottom of the aircraft passenger seat forward and lower as the seat bottom moves from an upright sitting position to a cradle recline sitting position, where a rear portion of the seat bottom is lowered more than a front portion of the seat bottom, causing the seat bottom to angle upwards from a bottom edge of the seat back. A seat back of the passenger seat may be pivotably connected to the seat bottom such that it is pulled forward and down with the movement of the seat bottom, with the recline angle determined by a rigid support mechanism disposed behind the seat back. Passenger weight may be counterbalanced using a moveable control mechanism such as a locking gas spring.
    Type: Application
    Filed: October 8, 2016
    Publication date: January 26, 2017
    Applicant: B/E AEROSPACE, INC.
    Inventor: Robert J. HENSHAW
  • Publication number: 20170021931
    Abstract: In a preferred embodiment, an aircraft passenger seat includes a seat back and a laterally-expanding tray table including a telescoping table segment and a main table segment having an interior pocket for receiving the telescoping table segment in a retracted position, where the telescoping table segment is adjacent to the main table segment in a fully extended position to form a contiguous table surface. The seat back may include a mounting region for stowing the laterally-expanding tray table, including a latching mechanism for latching the main table segment in a stowed position. The mounting region may extend across half the width of the seat back. The seat back may include storage region(s) horizontally adjacent to the mounting region, each storage region configured to stow a passenger convenience feature.
    Type: Application
    Filed: October 7, 2016
    Publication date: January 26, 2017
    Applicant: B/E AEROSPACE, INC.
    Inventors: Benjamin D. Stephens, Mark A. Kruse, Francis X. Garing
  • Publication number: 20170021932
    Abstract: Described are pivoting and sliding tray tables (10) that move through a substantially constant plane from a stowed position to a deployed position for use with passenger seats. The tray table (10) rides on two elements (14, 18) that themselves ride along guide tracks or guide rails (21, 22, 23) to provide a combination rotating and translating motion during deployment. In the deployed position, the tray table may be displaced linearly but is restricted from rotation. The tray table may be moved to accommodate passengers of differing size or to allow ingress and egress from the passenger seat with a reduced risk of unintentional rotation.
    Type: Application
    Filed: April 7, 2015
    Publication date: January 26, 2017
    Applicant: ZODIAC SEATS FRANCE
    Inventor: Jean-Charles MARAIS
  • Publication number: 20170021933
    Abstract: In a preferred embodiment, an aircraft passenger seat base frame can include spaced left and right spreaders supporting a seat pan and a seatback. Additionally, a front transverse structural member and a rear transverse structural member can each interconnect with the left and right spreaders. An in-flight entertainment component compartment defined in the seat pan at least in part by placement of the front transverse structural member and the rear transverse structural member can enclose an in-flight entertainment component, wherein the front transverse structural member is positioned for aligning in a vertical plane with at least a portion of the in-flight entertainment component, and the rear transverse structural member is positioned for aligning in a horizontal plane with at least a portion of the in-flight entertainment component.
    Type: Application
    Filed: October 7, 2016
    Publication date: January 26, 2017
    Applicant: B/E AEROSPACE, INC.
    Inventors: Alexander Nicholas POZZI, Benjamin D. STEPHENS, Mark A. KRUSE, Francis X. GARING
  • Publication number: 20170021934
    Abstract: An ice detecting apparatus comprising: a body including at least one ice detector mounted thereon and having an ice detecting surface and a scraping member so mounted relative to said body as to allow their movement one relative to the other and configured for scraping ice from said detecting surface during said movement.
    Type: Application
    Filed: January 27, 2015
    Publication date: January 26, 2017
    Inventors: Michael Levkovitch, Yehuda Kalman, Maayan Dermer, Michaela Alon, Nachum Levi, Dov Davidor, Evgeny Vadrovnik
  • Publication number: 20170021935
    Abstract: An engine assembly for an aircraft, comprising a mast. The engine assembly comprises an engine with a horizontal engine axis, an engine shaft having a first end rigidly connected to the engine and a second end, and a reducer having an input shaft meshing with the second end, and an output shaft to which a propeller is fixed. The engine assembly is configured such that the engine is fixed to the mast by a rigid connection, the reducer is fixed to the mast by means of flexible fasteners, the rotation between the engine shaft and the input shaft being driven via a slide link, the engine shaft has a first part and a second part and, therebetween, a flexible part assuring a tolerance to an angular misalignment between the axis of the second part and the axis of the first part.
    Type: Application
    Filed: June 20, 2016
    Publication date: January 26, 2017
    Inventor: Jacques Hervé Marche
  • Publication number: 20170021936
    Abstract: The invention deals with the restriction on the mode change of an engine due to latching in the case of restarting the engine that has stopped in flight. A FADEC that controls an engine of an aircraft in accordance with a mode, includes a latch operating section that latches the mode, and an in-parking/in-flight determining section that determines whether the aircraft is on the ground or flying off the ground. The latch operating section operates when the in-parking/in-flight determining section determines the aircraft is on the ground, and does not operate when the in-parking/in-flight determining section determines that the aircraft is in fight.
    Type: Application
    Filed: October 7, 2016
    Publication date: January 26, 2017
    Inventor: Yoshihiro NAGASHIMA
  • Publication number: 20170021937
    Abstract: A nacelle for a propulsion unit includes at least one scoop opening to the external air, and a canal supplying external air from the scoop to two ducts which separate downstream of the canal, forming a dividing lip, and at least one exchanger to cool a stream of fluid entering the exchanger. The exchanger is arranged in the region of and in contact with the separation lip. The external air circulates from the scoop towards the two ducts making it possible to cool the stream of fluid entering the exchanger.
    Type: Application
    Filed: March 10, 2015
    Publication date: January 26, 2017
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Sara BUSTILLO, Maria NATAL
  • Publication number: 20170021938
    Abstract: A heat exchange system for an aircraft includes an aircraft controller for controlling an operation of an aircraft, a thermoelectric device having a low temperature side and a high temperature side. Heat is transferred away from the inlet line to the outlet line through the thermoelectric device when a predetermined condition is met.
    Type: Application
    Filed: December 17, 2015
    Publication date: January 26, 2017
    Inventors: Charles E. Lents, William E. Rhoden
  • Publication number: 20170021939
    Abstract: A method and device for displaying at least one position indicator for an aircraft. The display device includes at least one unit for generating information for determining, during a flight of the aircraft, a control value representative of the movement by a first pilot of his joystick relative to at least one of the roll and pitch axes of the aircraft, at least one computation unit for computing a piloting command representative of the control value determined by the unit for generating information, and one display unit for displaying at least one symbol on at least one screen intended for the second pilot and directly visible by the latter, the symbol representing the position indicator and being displayed on the screen in a position illustrating the piloting command on the screen.
    Type: Application
    Filed: July 15, 2016
    Publication date: January 26, 2017
    Inventors: Franck CROSTA, Christophe CAIL
  • Publication number: 20170021940
    Abstract: Landing gear lights having multiple degrees of rotation are described herein. One disclosed example apparatus includes an aircraft landing gear light fixture having a first spherical portion, and a light assembly coupled to the light fixture, where the light assembly includes a second spherical portion adjacent the first spherical portion. The disclosed example apparatus also includes first and second pivots to allow the light assembly to rotate relative to the light fixture about two axes, where the rotation of the light assembly relative to the light fixture occurs by the first and second spherical portions moving relative to one another.
    Type: Application
    Filed: July 22, 2015
    Publication date: January 26, 2017
    Inventors: Frank Nogales, Khiem Nguyen Pham
  • Publication number: 20170021941
    Abstract: A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) storage and launch system includes a UAV pod having a UAV pod processor and a UAV selectively enclosed in the UAV pod, the UAV having only two rotors.
    Type: Application
    Filed: February 10, 2016
    Publication date: January 26, 2017
    Inventors: Christopher Eugene Fisher, Jason Sidharthadev Mukherjee, William Arden Lott
  • Publication number: 20170021942
    Abstract: An unmanned aerial vehicle (UAV) storage and launch system includes a UAV pod having an open position and a closed position, the closed position establishing an interior that is weather resistant to an environment external to the UAV pod and a vertical takeoff and landing (VTOL) UAV enclosed in the UAV pod so that the UAV pod in the closed position provides a weather resistant interior for the VTOL UAV.
    Type: Application
    Filed: February 11, 2016
    Publication date: January 26, 2017
    Inventors: Christopher Eugene Fisher, Jason Sidharthadev Mukherjee, William Arden Lott
  • Publication number: 20170021943
    Abstract: A capturing hook for engaging a cable during capture and release of an aerial vehicle may comprise a first and second gate pivotally supported at their first ends by a base portion and each being movable between a closed position and an open position, but spring-biased to the closed position. The capturing hook may further include a latch device comprising a movable locking part biased by a return spring to a locked position to lock the second gate in the closed position.
    Type: Application
    Filed: October 12, 2016
    Publication date: January 26, 2017
    Inventors: James Peverill, Adam Woodworth, Benjamin Freudberg, Dan Cottrell
  • Publication number: 20170021944
    Abstract: An aerial vehicle landing station comprising a first post and a second post, wherein the second post is spaced apart from the first post and a cable to capture an aerial vehicle, wherein the cable is stretched between the first post and the second post and configured to support the weight of the aerial vehicle once captured and the cable may provide a charging current to the aerial vehicle once captured. One or more markers may be further positioned on the cable to designate a landing point, wherein the one or more markers are configured to be visually tracked by the aerial vehicle. A cable management device coupled to the cable via one or more pulleys may regulate tension of the cable. A communications transceiver at the aerial vehicle landing station may wirelessly communicate data with the aerial vehicle.
    Type: Application
    Filed: October 12, 2016
    Publication date: January 26, 2017
    Inventors: James Peverill, Adam Woodworth, Benjamin Freudberg, Dan Cottrell, Terrence McKenna
  • Publication number: 20170021945
    Abstract: Liquid dispensing assemblies including adhesive anchoring assemblies configured to adhere to a support surface external to a device such as a vehicle. An air vehicle includes (a) a fluid adhesive container assembly detachably attached to the air vehicle, wherein the fluid adhesive container assembly comprises: (i) an adhesive container comprising fluid adhesive; and (ii) one or more fibers, wherein the one or more fibers are configured, or a brush of fibers, or a fabric of fibers, is configured to conduct the fluid adhesive and to structurally support an adhesive bond between the one or more fibers and a surface; and (b) means for dispensing the fluid adhesive from the fluid adhesive container, to the one or more fibers.
    Type: Application
    Filed: May 16, 2016
    Publication date: January 26, 2017
    Inventors: Christopher Eugene Fisher, John Peter Zwaan, David R. Thompson, Marc L. Schmalzel, Karl R. Klingbiel, Tyson R. Jensen, Pavel Belik, Eric James Aagaard
  • Publication number: 20170021946
    Abstract: An unmanned aircraft system (UAS) making use of unmanned aerial vehicles (UAVs) for more than one task. The inventors discovered that an improved UAS could be provided by combining one or more of these three elements: (1) hot-swappable modular kits (e.g., a plurality of components useful in UAVs to perform particular user-selectable tasks); (2) an interconnection mechanism for each component with identification protocols that provides both a physical and a data connection; and (3) an intelligent system that interprets the identification protocols and determines the configuration for a selected task, error checking, airworthiness, and calibration. The system and associated methods for the task based drone configuration and verification reduces the possibility of task failure by an operator.
    Type: Application
    Filed: July 11, 2016
    Publication date: January 26, 2017
    Inventors: ERRIN T. WELLER, JEFFREY B. FRANKLIN
  • Publication number: 20170021947
    Abstract: A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom, and/or compactible structures and deployment mechanisms used to form and deploy such satellite modules and power generation tiles associated therewith are provided. Each satellite module and/or power generation tile may be formed of a compactable structure and deployment mechanism capable of reducing the payload area required to deliver the satellite module to an orbital formation within the space-based solar power station and reliably deploy it once in orbit.
    Type: Application
    Filed: July 21, 2016
    Publication date: January 26, 2017
    Applicant: California Institute of Technology
    Inventors: Sergio Pellegrino, Harry A. Atwater, Seyed Ali Hajimiri, Manan Arya, Christophe Leclerc, Nicolas Lee
  • Publication number: 20170021948
    Abstract: Space vehicles are provided, each including a body and a solar panel array system. The body has a longitudinal axis and a plurality of body portions. Adjacent body portions are hinged to one another about a respective body hinge axis to enable the body portions to be selectively pivoted about the respective body hinge axes with respect to one another from an undeployed configuration to a deployed configuration. In the undeployed configuration the body has a first length dimension along a reference axis, and in the deployed configuration the body has a second length dimension along the reference axis. The second length dimension is greater than first length dimension. The solar panel system includes at least two panel sets. Each panel set has at least one solar panel, each panel set being movably mounted to one of the body portions and being selectively deployable from a stowed configuration to an extended configuration.
    Type: Application
    Filed: December 22, 2014
    Publication date: January 26, 2017
    Inventor: Nissim Yehezkel
  • Publication number: 20170021949
    Abstract: The bottom of a capsule is filled with at least two products contained in respective annular rotating containing tanks, which are mounted concentrically, and have a plurality of pairs of radially aligned filling holes; the filling holes of each pair of filling holes being associated with a relative closing device, which is selectively movable between a closing position of both filling holes, a first opening position of one of the two filling holes, and a second opening position of the other filling hole.
    Type: Application
    Filed: July 20, 2016
    Publication date: January 26, 2017
    Inventor: Davide NANNETTI
  • Publication number: 20170021950
    Abstract: A system for loading items into a container-defining sheet. The system includes a support for receiving the container-defining sheet, the support having a top surface provided with a number of apertures equal to the number of cavities embossed in the container-defining sheet. A support illumination board is positioned on a back portion of the support. The illumination board includes a plurality of evenly-spaced-apart support light indicators, each support light indicator being positioned substantially centrally with respect to a corresponding aperture of the support and adapted to back-illuminate one of the containers of the container-defining sheet upon placement of the container-defining sheet into the support. An illumination board controller controls operation of the support light indicators to indicate into which container of the container-defining sheet each item is to be loaded. An enclosure with drawers holding items to be put into the container-defining sheet is also disclosed.
    Type: Application
    Filed: February 29, 2016
    Publication date: January 26, 2017
    Inventor: Etienne BOUTHIETTE
  • Publication number: 20170021951
    Abstract: A dual syringe fluid pump (100, 200, 300, 400) includes a motor (110, 210, 310, 410) with a rotatable shaft (112, 212, 312, 412), a first syringe (120a, 220a, 320a, 420a) with a first syringe plunger (122a, 222a, 322a, 422a) coupled to the rotatable shaft (112, 212, 312, 412), and a second syringe (120b, 220b, 320b, 420b) with a second syringe plunger (122b, 222b, 322b, 422b) coupled to the rotatable shaft (112, 212, 312, 412). The motor (110, 210, 310, 410) rotates the rotatable shaft (112, 212, 312, 412) to simultaneously move the first syringe plunger (122a, 222a, 322a, 422a) and the second syringe plunger (122b, 222b, 322b, 422b) and at least one of the syringes (120a,b, 220a,b, 320a,b, 420a,b) is adapted to convert the rotation of the rotatable shaft (112, 212, 312, 412) to a linear movement of at least one of the syringe plungers (122a,b, 222a,b, 322a,b, 422a,b).
    Type: Application
    Filed: December 2, 2013
    Publication date: January 26, 2017
    Applicant: Norgren Kloehn, Inc.
    Inventor: Robert R. Teague
  • Publication number: 20170021952
    Abstract: The invention comprises a carpet wrapping apparatus. The apparatus comprises a pair of rotatable rollers for supporting a roll of sheet material and for rotating the roll of sheet material supported thereon and a vertically extending curtain disposed adjacent and spaced from the roll of sheet material so that there is a horizontal gap between the curtain and the roll of sheet material when supported on the rollers. The apparatus also comprises a source of pressurized air directed toward the curtain and a plastic film dispenser disposed above the rollers for dispensing a plastic film between the curtain and the source of pressurized air so that the pressurized air blows the plastic film toward the curtain and into the gap. A method of wrapping a roll of carpet with a plastic film is also disclosed.
    Type: Application
    Filed: July 23, 2015
    Publication date: January 26, 2017
    Inventors: Adam Paul Smith, Ronald Edwin Headrick, JR.
  • Publication number: 20170021953
    Abstract: A method for packaging a frozen food product includes placing a fluid food product into a flexible container, sealing the container and pasteurizing the food product in the sealed container. The method further includes applying a form to at least one surface of the flexible container, the form embossing the container and creating a series of compartments separated by thin segments therebetween, and freezing the product in the container with the form in place.
    Type: Application
    Filed: June 2, 2016
    Publication date: January 26, 2017
    Inventor: David Bruce Walker
  • Publication number: 20170021954
    Abstract: In a method for producing a collection (20) of pre-products by inserting a first pre-product (1) into a second pre-product (3), it is provided according to the invention that a first pre-product (1) and a second pre-product (3) are provided, wherein the second pre-product (3) has a wrapping fold (4) with a fold inner side (5). The second pre-product (3) is conveyed into an insertion position, in which the second pre-product (3) is opened and faces with the fold inner side (5) toward the first pre-product (1). The first pre-product (1) is conveyed into the opened second pre-product (3) and against the fold inner side (5) so as to form the collection (20), the second pre-product (3) assumes the conveying direction of the first pre-product (1), and the collection (20) is provided for further processing.
    Type: Application
    Filed: July 5, 2016
    Publication date: January 26, 2017
    Applicant: Ferag AG
    Inventors: Othmar BRUNSCHWILER, Roland LENGWEILER
  • Publication number: 20170021955
    Abstract: The thermo-forming packaging machine according to one embodiment of the present invention comprises a sealing station, a first forming station for forming trays into a lower film web that is in a first forming plane clamped in the first forming station, and a second forming station for forming lids into an upper film web that is in a second forming plane clamped in the second forming station. The sealing station can be configured to create a sealing seam in a sealing plane. The thermo-forming packaging machine may be characterized in that the first forming plane is provided at least 200 mm below the second forming plane, wherein the first and the second forming planes are at least approximately parallel to each other.
    Type: Application
    Filed: July 21, 2016
    Publication date: January 26, 2017
    Inventor: Elmar Ehrmann