Patents Issued in May 14, 2020
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Publication number: 20200148346Abstract: A method for an aircraft is provided in one example embodiment and may include determining a transition from an airplane mode to a helicopter mode for a propulsion system of the aircraft, wherein the propulsion system comprises a plurality of rotor blades; determining whether a descent rate condition is satisfied, wherein the descent rate condition is associated with a maximum allowable descent rate for the aircraft; and controlling a collective pitch angle for the plurality of rotor blades based on the descent rate condition.Type: ApplicationFiled: November 13, 2018Publication date: May 14, 2020Applicant: Textron Innovations Inc.Inventors: Stephen Yibum Chung, Eric Ricardo Gonzalez, Russell C. Peters, Matthew Edward Louis
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Publication number: 20200148347Abstract: An aircraft including an airframe and a plurality of propulsion assemblies coupled to the airframe, wherein each propulsion assembly includes an electric motor, a propeller coupled to the electric motor, and a tilt mechanism that connects the propulsion assembly to the airframe and transforms the propulsion assembly between a forward configuration and a hover configuration; wherein the plurality of propulsion assemblies is transformable between a forward arrangement and a hover arrangement, wherein each of the plurality of propulsion assemblies is in the forward configuration in the forward arrangement, wherein each of the plurality of propulsion assemblies is in the hover configuration in the hover arrangement, wherein the spacing between at least two of the propellers of the plurality of propulsion assemblies changes between the forward arrangement and the hover arrangement.Type: ApplicationFiled: May 10, 2019Publication date: May 14, 2020Inventors: JoeBen Bevirt, Edward Stilson, Alex Stoll, Gregor Veble Mikic
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Publication number: 20200148348Abstract: A tethered drone system and method includes a tethered drone and a tether. The tether includes a conductor to communicate at least power and control signals. The tethered drone system further includes a control system configured to receive the tethered drone. The control system provides power for the tethered drone. The control system includes a user interface for managing the control signals.Type: ApplicationFiled: June 13, 2018Publication date: May 14, 2020Applicant: PearTrack Security Systems, Inc.Inventors: Aiden Nathaniel Bradley, Nathaniel T. Bradley, Joshua S. Paugh
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Publication number: 20200148349Abstract: An aircraft-based object manipulation system and methods are provided herein. The system includes an airframe capable of flight. A plurality of sensors configured to identify a physical characteristic of an object. An object manipulation system is configured to adjust a position the object, and to secure the object to the airframe. A processor communicatively configured to control operation of the object manipulation system based on information from the plurality of sensors.Type: ApplicationFiled: November 13, 2018Publication date: May 14, 2020Inventors: William Robert Bosworth, Martin Kearney-Fischer
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Publication number: 20200148350Abstract: An unmanned aircraft includes an aircraft main body, a motherboard disposed inside the aircraft main body, and a top cover mounted on the aircraft main body and configured to seal the motherboard inside the aircraft main body. The unmanned aircraft also includes a battery, a gimbal assembly module, and an antenna assembly disposed at a lower portion of the aircraft main body. The battery is disposed at a rear lower portion of the aircraft main body, the gimbal assembly module is located at a front lower portion of the aircraft main body, and the antenna assembly is between the battery and the gimbal assembly module.Type: ApplicationFiled: October 8, 2019Publication date: May 14, 2020Inventors: Guisheng NONG, Lei ZHANG, Yin TANG
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Publication number: 20200148351Abstract: A cleaning method includes controlling an unmanned aerial vehicle (UAV) to fly to a region of a wall body according to a path to be cleaned, and, in response to detecting a cleaning prohibition identifier associated with the region, recognizing the region as a cleaning prohibition region and controlling the UAV to fly over the cleaning prohibition region without cleaning the cleaning prohibition region.Type: ApplicationFiled: December 29, 2019Publication date: May 14, 2020Inventors: Ang LIU, Yuwei WU
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Publication number: 20200148352Abstract: An unmanned aerial vehicle (UAV) includes a central body, a first arm and a second arm each attached to the central body and extending away from the central body, a first propulsion unit supported at a distal end of the first arm and a second propulsion unit supported at a distal end of the second arm, and one or more actuators configured to adjust an orientation of the first propulsion unit and an orientation of the second propulsion unit relative to the central body during flight of the UAV. The first arm and the second arm are configured to be reversibly folded against the central body. Each of the first propulsion unit and the second propulsion unit includes rotor blades configured to rotate to generate lift for the UAV, and a motor configured to drive the rotor blades.Type: ApplicationFiled: January 8, 2020Publication date: May 14, 2020Inventors: Yumian DENG, Tao ZHAO
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Publication number: 20200148353Abstract: The present invention relates to the field of air vehicle technologies and provides an unmanned aerial vehicle (UAV), including a vehicle body and arms connected to the vehicle body. The arm is hinged to the vehicle body by using a spherical hinge portion and may be folded or unfolded relative to the vehicle body. Through the forgoing manner, the arm is connected to the vehicle body of the UAV by using the spherical hinge. The arm can be folded and unfolded smoothly without interference, which conforms to known operation habits of users, so that after the entire UAV is folded, the structure becomes more compact and easier to carry. In addition, it can be effectively avoided that the UAV is damaged due to impact in the carrying process.Type: ApplicationFiled: January 20, 2020Publication date: May 14, 2020Inventor: Feng NI
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Publication number: 20200148354Abstract: An autonomous thrust vectoring ring wing pod is disclosed. A plurality of distributed propulsion element (thruster) layout within a self-articulating ring wing pod allows the pod to selectively control its thrust vector by controlling each propulsion element in the pod. This arrangement allows autonomous and independent control of the tilting of the ring wing relative to the aircraft. The ring wing pod acts as both a nacelle to house the propulsion elements as well as a lifting surface when in wing-borne flight. The autonomous thrust vectoring ring wing pod also provides superior aircraft attitude control in wing-borne flight, thus negating the need for conventional surface controls.Type: ApplicationFiled: November 8, 2018Publication date: May 14, 2020Applicant: Textron Innovations Inc.Inventors: Kevin Morris, Nicholas Brodeur, Carlos Fenny
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Publication number: 20200148355Abstract: A modular weapon carriage and deployment (MWCD) system includes a strongback structure mountable to an aircraft. Left and right guide struts have respective upper ends attached to the strongback structure in spaced lateral positions. Each guide strut extends downward in a parallel arrangement. Each guide strut comprising a vertically-extending first engaging surface. Left and right suspension modules are engageable to opposite lateral sides of a first airborne store. Each suspension module includes a vertical channel that receives the engaging surface of the corresponding one of the left and right guide struts for relative vertical translation. A locking mechanism controllably locks to first engaging surface of the corresponding one of the left and right guide struts.Type: ApplicationFiled: November 14, 2018Publication date: May 14, 2020Inventor: Jerry Provenza
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Publication number: 20200148356Abstract: An airborne store support assembly includes an ejector housing assembly that receives a fluid-actuated ejector piston. Extension of the piston pushes apart an airborne store from an aircraft for separation after release. A selectable force gas generator (SFGG) includes a total number of more than one gas-generating unit in fluid communication with the ejector housing assembly to actuate the fluid-actuated ejector piston with a selected amount of force. A communication interface in communication with the SFGG supplies at least one firing signal that causes a selected subset of the more than one gas-generating unit that corresponds to the selected amount of force that is dynamically determined by a controller based on flight parameters of at least one of an attitude, a rate of motion, and a rate of acceleration of the aircraft.Type: ApplicationFiled: November 14, 2018Publication date: May 14, 2020Inventor: Jerry Provenza
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Publication number: 20200148357Abstract: An aircraft store ejector systems and subsystems thereof. Embodiments can include a two-reservoir re-pressurization system wherein a remote reservoir is used to maintain desired pressure in a local ejector reservoir. The system can include a release valve having a vent valve and valve piston. The release valve can control release of pressurized gas to a pitch control valve. The pitch control valve can be configured to distribute the pressurized gas between two or more ejector piston assemblies. One or more of the ejector piston assemblies can include multiple concentric piston stages and piston chambers, the piston chambers configured to contain a volume of gas. The ejector piston assemblies can be configured to compress the volume of gas within the piston chambers as the piston stages are extended out from the aircraft. Such compression can provide a return force to the piston stages.Type: ApplicationFiled: August 22, 2019Publication date: May 14, 2020Inventors: Lee Allen Tobias, Sohrab John Talebian, Robert Ronald Evans
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Publication number: 20200148358Abstract: A crop duster dump gate opens and closes to turn on and off the flow of payload out of the hopper. The traditional mechanical gate is actuated by the pilot through mechanical linkages. The effort required by the pilot to open and close the gate requires significant force and can lead to fatigue or injury. The powered dump gate system is an add-on to the existing traditional mechanical gate system by a booster that is hydraulic, pneumatic, or electric. The powered dump gate eliminates strenuous effort by the pilot and requires no change to the pilot's work environment and methods.Type: ApplicationFiled: November 14, 2018Publication date: May 14, 2020Inventor: Troy Robert Reabe
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Publication number: 20200148359Abstract: A rescue basket having the capacity to safely hold two full-sized individuals increases the efficiency and effectiveness of helicopter water rescue and recovery operations. The rescue basket includes an open end, which affords an additional option for loading passengers, along with a door mechanism that can at least partially close off the open end for passenger safety. The rescue basket includes a flotation system that maintains the basket at a desired flotation level when completely immersed in water, along with sufficient reserve buoyancy to safely maintain the passengers above water when loaded. Methods of performing a water rescue utilizing the present rescue basket on board of a helicopter are also provided.Type: ApplicationFiled: March 28, 2019Publication date: May 14, 2020Applicant: The Government of the United States of America, as represented by the Secretary of Homeland SecurityInventors: Spencer Smith, Riely Brande, Nolan Richerson, Benjamin Crutchfield, Christian Breviario, Ronald Adrezin, Michael Plumley, Marion Lewandowski
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Publication number: 20200148360Abstract: A bistable gripper for an aerial vehicle may include a base, a first finger, a second finger, a switching pad, a first elastic connector, and a second elastic connector. The base may include a first beam and a second beam. The first finger may be pivotably attached to the first beam at a first joint, and the second finger may be pivotably attached to the second beam at a second joint. The switching pad may be configured for moving relative to the base. The first elastic connector may be attached to the switching pad and the first finger, and the second elastic connector may be attached to the switching pad and the second finger. The bistable gripper may be configured for switching between a closed stable state and an open stable state.Type: ApplicationFiled: November 8, 2019Publication date: May 14, 2020Inventors: Haijie Zhang, Jianguo Zhao, Jiefeng Sun
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Publication number: 20200148361Abstract: A restraint assembly includes a fitting base, a bushing, and a restraint roller disk, according to various embodiments. The fitting base includes a fitting lower surface and a fitting upper surface that is angled relative to the fitting lower surface, according to various embodiments. The fitting base may be configured to be coupled, via an anchor, to a rail upper surface of a guide rail of the cargo system. In various embodiments, the bushing is configured to be disposed about the anchor. In various embodiments, the restraint roller disk includes a roller upper surface and a roller lower surface, wherein the restraint roller disk is configured to be rotatably coupled about the bushing and the roller lower surface is configured to engage the fitting upper surface of the fitting base.Type: ApplicationFiled: January 13, 2020Publication date: May 14, 2020Applicant: GOODRICH CORPORATIONInventors: Wallace Harold Larson, Troy Joseph Herberholz, Ryan Pfau, Brian Landis
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Publication number: 20200148362Abstract: An example seat pan for an aircraft includes a first portion having a first end and a second portion that is adjacent to the first portion and is adjustable to be in a first position in which the second portion forms a seating surface together with the first portion, the seating surface having a width that is wider than a width of the first end of the first portion. The second portion is adjustable to alternatively be in a second position in which the first end of the first portion extends beyond the second portion to be insertable into a footwell.Type: ApplicationFiled: January 16, 2020Publication date: May 14, 2020Inventors: James P. Mehlos, Tony Bravetti
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Publication number: 20200148363Abstract: The present invention essentially relates to an arrangement of individual seats intended to be installed in a cabin of an aeroplane, the arrangement of seats comprising at least one assembly of two seats turned towards the interior in the direction of the longitudinal axis of the arrangement, characterised in that: an end assembly comprises a first seat and a second seat, each seat being convertible between a sitting position and a recumbent position in which the seat defines a bed surface, and an intermediate element having a surface, referred to as the intermediate surface, located in the same plane as the bed surfaces of the first seat and of the second seat, such that the bed surfaces of the first seat and of the second seat as well as the intermediate surface form a common bed surface.Type: ApplicationFiled: March 29, 2018Publication date: May 14, 2020Inventors: Jeremy White, Nicholas Sandham, Richard Seale, Omar Chraibi
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Publication number: 20200148364Abstract: A pillow includes a support body. A shape-adapting frame is within the support body. The shape-adapting frame is configured to be moved into and maintained in a desired position. At least one sensor is configured to detect at least one condition. The sensor(s) may be in communication with a monitoring control unit of a monitoring system.Type: ApplicationFiled: November 13, 2018Publication date: May 14, 2020Applicant: THE BOEING COMPANYInventors: Cynthia A. Vandewall, Swati Chopra, Brian Keller, Blake Lane, Shuai Mu, Elizabeth O'Hearn, Chuyu Ruan, Craig Vogel
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Publication number: 20200148365Abstract: Provided are seat tracks comprising composite frames and methods of fabricating such seat tracks. A composite frame comprises two sets of fibers having different orientations. The first fibers may extend parallel to the principal axis of the track, while the second fibers may extend within planes perpendicular to that axis. Various characteristics of these fibers may be specifically selected such that the mechanical strength of the frame in the principal axis direction is greater than other directions. In other words, the composite frame may have anisotropic properties. This difference ensures that adequate support is provided during both normal conditions and extreme conditions. Specifically, during the normal operating conditions, most loads may be directed vertically, while at the extreme conditions most loads may be directed horizontally.Type: ApplicationFiled: December 20, 2019Publication date: May 14, 2020Applicant: The Boeing CompanyInventor: Khambrel A. Simpson
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Publication number: 20200148366Abstract: A seat base includes a plurality of linear actuators each having a first end pivotally mounted to a base member and a second end pivotally mounted to a seat member. A controller is adapted for controlling an extension length of each of the plurality of linear actuators in a coordinated manner for adjusting a position of the seat member with six degrees-of-freedom and for damping vibration of the seat member. An active vibration mitigation method for reducing vibrations of an aircraft seat includes receiving vibration data from one or more accelerometers mounted to the aircraft seat and determining a vibration profile based on the vibration data. When vibration mitigation is warranted, control signals for damping vibration are determined and transmitted to a plurality of linear actuators adapted to support the aircraft seat.Type: ApplicationFiled: October 22, 2019Publication date: May 14, 2020Inventors: Stephen Howard Fagan, Paul Stokholm Warren, Emily O'Kelley Pearson, Jeremy Joseph Kneuper, Phillip Kendrick
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Publication number: 20200148367Abstract: An aircraft air distribution assembly providing integrated personally controllable air flow and cabin air flow is presented. The aircraft air distribution assembly comprises a plenum and a flow restriction system. The plenum is connected to a plurality of personal air outlets configured to provide the personally controllable air flow. The flow restriction system extends through at least one wall of the plenum, the flow restriction system configured to set a pressure for the cabin air flow.Type: ApplicationFiled: November 8, 2018Publication date: May 14, 2020Inventor: Bryce Avery Vandyke
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Publication number: 20200148368Abstract: A vented leading-edge assembly is provided, the assembly including: a slat having a bay and a top skin delimiting a portion of the bay; a spar being arranged in the slat, the spar dividing the bay in a front bay and an aft bay; and a plurality of channel sidewalls being arranged between the top skin and the spar, the plurality of channel sidewalls defining a plurality of channels between the front bay and the aft bay, wherein at least a portion of the spar defines lower channel walls for the plurality of channels.Type: ApplicationFiled: October 8, 2019Publication date: May 14, 2020Applicant: Airbus Operations GmbHInventors: Stefan Bensmann, Marcus Erban
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Publication number: 20200148369Abstract: Briefly, the disclosure relates to apparatuses and methods to enclose electrical contacts for de-icing equipment utilized on fixed-wing aircraft and rotary-wing aircraft, such as helicopters and tiltrotor aircraft. In some implementations, enclosing electrical contacts for a de-ice heater blanket may ensure that high-quality electrical connections are made between conductors of one or more de-icing cables and the electrical contacts of the de-ice heater blanket. Such high-quality electrical connections may be maintained even during aircraft operations conducted in below-freezing ambient environments, rainy and/or wet environments, dusty desert environments, and so forth.Type: ApplicationFiled: November 13, 2018Publication date: May 14, 2020Inventor: Nicholas Allen Torske
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Publication number: 20200148370Abstract: A gas distribution assembly for providing gas to an actuator for opening an aircraft door and to an aircraft evacuation slide, the assembly comprising a single common gas supply and valve means for controlling distribution of gas from the common supply between the slide and the door actuator based on door opening position.Type: ApplicationFiled: July 31, 2019Publication date: May 14, 2020Inventors: Hélène BERGONNIER, Bruno SEMINEL
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Publication number: 20200148371Abstract: An evacuation assembly may comprise an evacuation slide and a first yoke coupled to the evacuation slide. The first yoke may comprise a first strap and a second strap. The first strap may be longer than the second strap. The evacuation assembly may optionally include a second yoke coupled to the evacuation slide. A first strap of the second yoke may be longer than a second strap of the second yoke.Type: ApplicationFiled: December 27, 2019Publication date: May 14, 2020Applicant: GOODRICH CORPORATIONInventors: Jaro S. Volny, Drew Hartman
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Publication number: 20200148372Abstract: An example hybrid aircraft propulsion system includes one or more power units configured to output electrical energy onto one or more electrical busses; a plurality of propulsors; and a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from at least one of the one or more electrical busses.Type: ApplicationFiled: November 8, 2018Publication date: May 14, 2020Inventor: Stephen Andrew Long
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Publication number: 20200148373Abstract: An example hybrid aircraft propulsion system includes a plurality of power units configured to output electrical energy onto one or more electrical busses; one or more propulsors; and one or more electrical machines, each respective electrical machine configured to drive a respective propulsor of the one or more propulsors using electrical energy received from at least one of the one or more electrical busses.Type: ApplicationFiled: November 8, 2018Publication date: May 14, 2020Inventor: Stephen Andrew Long
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Publication number: 20200148374Abstract: In a hybrid flight vehicle, having four rotors attached to a frame and configured to produce propelling force to propel the frame, a gas turbine engine attached to the frame and configured to rotate when fuel is supplied, a generator connected to an output shaft of the engine and configured to generate electric power when driven by the engine, a battery configured to store the electrical power generated by the generator, and four first electric motors each connected to the rotors to drive associated one of the rotors when the electric power is supplied from the battery, and an electronic control unit configured to control flight by regulating driving of the four rotors by the first electric motors. In the vehicle, the output shaft of the engine is attached parallel to at least one among yaw axis, pitch axis and roll axis of the frame.Type: ApplicationFiled: October 22, 2019Publication date: May 14, 2020Inventor: Keisuke Kawai
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Publication number: 20200148375Abstract: Systems and methods for distributing in an aircraft are provided. More particularly, in one embodiment, a system can include one or more gas turbine engines configured to provide propulsion and electrical power to an aircraft. The system can further include one or more electrical engines configured to provide propulsion for the aircraft. The system can include one or more first electrical power systems configured to provide power to the one or more electrical engines for one or more electrical power propulsion loads for the aircraft. The system can further include one or more second electrical power systems configured to provide power for one or more non-propulsion electrical power loads of the aircraft.Type: ApplicationFiled: October 2, 2019Publication date: May 14, 2020Inventor: Hao Huang
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Publication number: 20200148376Abstract: In a hybrid flight vehicle, having multiple rotors attached to a frame, a gas turbine engine to drive the rotors; a generator connected to the gas engine to generate electric power, a battery store the electrical power generated by the generator. multiple first electric motors connected to the rotors to drive the same by the electric power supplied from the battery, a second electric motor connected to the gas turbine engine to motor the engine by the electric power supplied from the battery and a control unit to control flight, wherein the control unit stops supply of the fuel to the engine when a detected residual of the battery is equal to or greater than a predetermined value, and supplies electric power to the second electric motor to motor the engine when a detected temperature of the engine is equal to or higher than a predetermined temperature.Type: ApplicationFiled: October 22, 2019Publication date: May 14, 2020Inventor: Keisuke Kawai
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Publication number: 20200148377Abstract: A method for securing an engine using an adjustable mounting assembly is provided including adjusting an extendible element of the adjustable mounted assembly from a first position to a second position. Another extendible element of the adjustable mounting assembly is adjusted from a third position to a fourth position. The engine is mounted using the adjustable mounted assembly with the extendible element in the second position and another extendible element in the fourth position.Type: ApplicationFiled: October 4, 2019Publication date: May 14, 2020Inventors: Jon McBride, Scott A. Chasen
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Publication number: 20200148378Abstract: In order to bring the primary structure of an engine mounting pylon of an aircraft as close as possible to a wing box: —an aircraft wing includes a wing box made partly by a front spar and an intermediate spar; —a mounting pylon including a primary structure in the form of a box having transverse reinforcement ribs; and —attachment means for attaching the primary structure of the mounting pylon on the wing box. These attachment means include a row of bolts along which each bolt passes through a structural part of the pylon on one hand, and on the other hand a fitting attached to one of the front and intermediate spars.Type: ApplicationFiled: April 9, 2018Publication date: May 14, 2020Applicant: Airbus Operations S.A.S.Inventors: Olivier Pautis, Laurent Lafont, Rohan Nanda
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Publication number: 20200148379Abstract: A thrust control assembly includes a balk application arrangement which provides, in response to a received balk command to prohibit command of thrust in a balk direction, a balk force on a rotatable thrust lever acting to oppose an attempt by the pilot to move the lever in a direction so as to command or increase thrust in the balk direction. The balk application arrangement controls an auto-throttle actuator to provide the balk force on the thrust lever.Type: ApplicationFiled: November 11, 2019Publication date: May 14, 2020Inventor: Cédric ANTRAYGUE
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Publication number: 20200148380Abstract: Gas-flammability sensing systems and methods may be used to determine the flammability of gas mixtures in measurement volumes such as a fuel tank (e.g., an aircraft fuel tank). Gas-flammability sensing systems include a test cell structured to receive a gas sample, a heater in thermal communication with the test cell, and a gas meter configured to measure a physical property of the gas sample within the test cell related to the combustion state of the gas sample. The heater is configured to heat the gas sample to an elevated temperature less than the autoignition temperature of the gas sample. Methods of determining the flammability of a gas sample include collecting the gas sample, heating the gas sample to the elevated temperature, measuring the physical property of the gas sample after heating, and determining the flammability of a gas sample based upon the measured physical property.Type: ApplicationFiled: January 10, 2020Publication date: May 14, 2020Inventors: Eddie Kwon, Jason Scott Damazo, Philipp Andreas Boettcher, William J. Sweet, Kevin Richard Housen
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Publication number: 20200148381Abstract: A method and apparatus for recording flight information of aircraft, such as position, mass, or type, in order to record the position of a wake turbulence of the aircraft. Weather information can be recorded as affecting the wake turbulence. Such information can be provided into a model or algorithm to determine a path of a wake turbulence. An aircraft on a flight path to encounter the wake turbulence can determine a vortex magnitude of the wake turbulence and determine if an advisory alert needs to be provided if the vortex magnitude satisfies a predetermined threshold.Type: ApplicationFiled: November 11, 2019Publication date: May 14, 2020Inventor: Stefan Alexander Schwindt
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Publication number: 20200148382Abstract: An aerial vehicle includes a communication interface configured to acquire information pertaining to a transportation system from a communication terminal, a propulsion unit for flying, and a controller configured to control the propulsion unit. The controller outputs the information pertaining to the transportation system by controlling at least one of the propulsion unit and the communication interface.Type: ApplicationFiled: January 14, 2020Publication date: May 14, 2020Applicant: KYOCERA CorporationInventors: Shigeki TANABE, Yasuhiro UENO, Hideki MORITA, Isao MASUIKE, Koutaro YAMAUCHI, Manabu SAKUMA, Kenji SHIMADA
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Publication number: 20200148383Abstract: A system includes an RF signaling device configured to record a count of a number of times that an aircraft door or cover has opened or closed, and a management device configured to determine a state of the aircraft door or cover based on communication with the RF signaling device.Type: ApplicationFiled: December 9, 2019Publication date: May 14, 2020Applicant: AEROSENS LLCInventor: Maria-Esther Martinez-Barreiro
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Publication number: 20200148384Abstract: The present disclosure provides an aircraft (10), as well as systems and methods for reducing current flow to electrical systems onboard an aircraft (10). A signal return network (220) is spaced from a composite structure (210) and first and second non-conductive components (240) are attached between the signal return network (220) and the composite structure (210) at first and second attachment points (242, 244), respectively. A conductive component (250) is attached between the signal return network (220) and the composite structure (210) at a third attachment point (246) for electrically coupling the signal return network (220) to the composite structure (210).Type: ApplicationFiled: November 8, 2017Publication date: May 14, 2020Inventors: Fidele MOUPFOUMA, Amadou Cisse NDOYE, Mohsen JALALI
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Publication number: 20200148385Abstract: A system and method of shifting a premature descent protection envelope for an aircraft has been developed. First, a premature descent protection envelope (PDP) is determined including a first boundary at a first distance from the runway. Next, a nominal approach path is determined for approaching the runway and an approach path angle. Also, a flight path angle of the aircraft is determined. The first boundary is shifted in an upward direction from the runway in response to the aircraft being below the nominal approach path, and the flight path angle being greater than the nominal approach path angle.Type: ApplicationFiled: January 6, 2020Publication date: May 14, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Yasuo Ishihara, Steve Johnson, Kevin J Conner
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Publication number: 20200148386Abstract: A drone includes a light emitter that emits light and circuitry which, in operation, obtains flight state information regarding a flight state of the drone, determines, on the basis of the flight state information, a direction in which the light emitter is to emit light, and controls the light emitter such that the light emitter emits light in the determined direction.Type: ApplicationFiled: January 9, 2020Publication date: May 14, 2020Applicant: PANASONIC INTELLECTUAL PROPERTY CORPORATION OF AMERICAInventors: SHUNSUKE KUHARA, TAKENOBU AOSHIMA
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Publication number: 20200148387Abstract: An unmanned airborne vehicle (UAV) recovery system for in-flight recovery of a fixed wing UAV includes a catching device and a plurality of hover-capable drones, such as multi-rotors. The catching device is for catching the fixed wing UAV via a hook system during flight of the fixed wing UAV and takes the form of a line between the recovery drones. The recovery drones are arranged to support the catching device as it spans a gap in a horizontal orientation with the catching device suspended between at least two recovery drones that are in flight and spaced apart horizontally from each other either side of the gap. During a recovery operation the recovery drones co-ordinate their movement to adopt a flight path relative to a flight path of the fixed wing UAV to define a virtual runway for interception of the fixed wing UAV by the recovery system.Type: ApplicationFiled: April 12, 2018Publication date: May 14, 2020Inventors: Tor Arne JOHANSEN, Thor Inge FOSSEN, Kristian KLAUSEN
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Publication number: 20200148388Abstract: Systems and methods for capturing unmanned aircraft and controlling post-recovery motion of the aircraft are disclosed herein. An aircraft system in accordance with one embodiment of the technology, for example, includes a base assembly and an aircraft capture member attached to and extending from the base assembly. The aircraft capture member has a distal region positioned to intercept an unmanned aircraft in flight. The aircraft capture member comprises an elongated telescoping rod including a plurality of discrete segments having a telescoping arrangement relative to each other. The aircraft capture member is configured to elongate or pay out from a first initial length to a second extended length greater than the first length after an unmanned aircraft intercepts and engages the distal region of the aircraft capture member.Type: ApplicationFiled: May 25, 2018Publication date: May 14, 2020Inventor: Bradley Louis Schrick
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Publication number: 20200148389Abstract: A take-off apparatus and method for unmanned aerial vehicle without landing gear includes an unmanned aerial vehicle, a carrier, a lock/release mechanism, a lift or airspeed sensing module, a signal processing module and a release motion sensing module. The lock/release mechanism locks the unmanned aerial vehicle onto the carrier and controllably releases the unmanned aerial vehicle from the carrier. The lift or airspeed sensing module senses an overall lift or airspeed of the unmanned aerial vehicle. When the lift or speed value of the unmanned aerial vehicle is greater than a predetermined threshold, it drives the lock/release mechanism into an unlocked state so that the unmanned aerial vehicle is released from the carrier and takes off more accurately and successfully.Type: ApplicationFiled: November 12, 2019Publication date: May 14, 2020Inventors: Huan-Jung Lin, Chung-Yan Lin
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Publication number: 20200148390Abstract: Systems and methods for implementing a modeling language extension for inter-partition communication are provided. Aspects include defining, by a modeling language, a simulation model, defining a simulation model extension, the simulation model extension comprising at least one sampling port communication module and at least one queueing port communication module, and adding the simulation model extension to the simulation model.Type: ApplicationFiled: November 13, 2018Publication date: May 14, 2020Inventor: Dana Eugene Adkins
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Publication number: 20200148391Abstract: An apparatus and method to equalize the pressure in multiple tires supported by a single axle or strut of an airplane is shown. A control block connects the pressurized gas to a distribution block and meter. From the distribution block high pressure lines and no-loss chuck valves connect the pressurized gas to the multiple tires. Steps to be followed as programmed in the meter include startup, testing, calibration, setup and finalize. A permanent record of the steps in equalizing tire pressures is maintained.Type: ApplicationFiled: November 12, 2018Publication date: May 14, 2020Applicant: Three Zero Right, LLCInventors: Ronald R. Sallman, Mark Drew Holland
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Publication number: 20200148392Abstract: A method, apparatus, and system for testing a fuel tank for an aircraft. Electrical power is sent to an optical data concentrator for the fuel tank for the aircraft from a power supply such that the optical data concentrator sends optical signals to optical sensors inside the fuel tank through optical fibers connecting the optical data concentrator to the optical sensors. The electrical power is sent during a phase of manufacturing of the aircraft. Test data is received from the optical data concentrator by a computer system. The test data is based on optical response signals received from the optical sensors. A determination of states for the optical sensors is made by the computer system using the test data. A graphical indication of the states determined for the optical sensors inside the fuel tank is displayed by the computer system in a graphical user interface on a display system.Type: ApplicationFiled: November 8, 2018Publication date: May 14, 2020Inventors: Bryan R. Durr, Timothy Edward Jackson, Eric Scott Gubler
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Publication number: 20200148393Abstract: In an embodiment, a method includes: collecting usage and maintenance data for a rotorcraft at a computer of the rotorcraft; sending the usage and maintenance data to a fleet management server; generating individualized equipment data for the rotorcraft according to the usage and maintenance data at the fleet management server, the individualized equipment data including a lightweight digital representation of the rotorcraft and technical publications for the rotorcraft, the lightweight digital representation including mesh-based 3D visualizations of each component of the rotorcraft, the technical publications having views referencing the mesh-based 3D visualizations; sending the individualized equipment data to the computer of the rotorcraft; and persisting the individualized equipment data at the computer of the rotorcraft.Type: ApplicationFiled: November 9, 2018Publication date: May 14, 2020Inventors: Jeremy Robert Chavez, Peter Shultz, Thomas Kurt Schneider, Mark Howard Thomson, Daniel Wesley Rowe
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Publication number: 20200148394Abstract: An example test fixture includes a lower frame having a first rocker rail and a second rocker rail coupled to the first rocker rail, wherein each of the first rocker rail and the second rocker rail has a respective curved surface that allows the lower frame to tilt about a first axis; a rotatable base coupled to the lower frame; an upper frame having a mounting system configured to couple a transmission of an aircraft to the upper frame; a support frame that couples the upper frame to the rotatable base; and a rotary actuator configured to rotate the rotatable base, the support frame, and the upper frame about a second axis perpendicular to the first axis.Type: ApplicationFiled: November 12, 2018Publication date: May 14, 2020Inventor: Kenneth P. Schilling
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Publication number: 20200148395Abstract: A method for prediction of key performance parameters of an aero-engine in transition condition. Bench test data for an aero-engine in transition condition provided by a research institute is used for establishing a training dataset and a testing dataset first; parameter combination is used for predicting and analyzing engine exhaust temperature based on the idea of information fusion; and the method of rolling windows is used for rolling learning in order to predict the parameters such as low pressure rotor speed and exhaust temperature of an engine from the perspective of practical engineering application.Type: ApplicationFiled: January 26, 2018Publication date: May 14, 2020Inventors: Shuo ZHANG, Jibang LI, Ximing SUN, Min LIU