Abstract: A package transport device includes: a main body (a vehicle main body, a first vehicle main body, and a second vehicle main body); a rail holder (connector) held by a rail located above the main body; a turntable that is provided between the main body and the rail holder and rotates the main body; a slider portion that extends with respect to the main body; and a package holder that holds a package attached to the slider portion.

Abstract: Embodiments described herein relate to providing authenticated access to passenger-specific information at a seatback device of a vehicle based on connection with personal passenger devices. A method includes obtaining a unique identifier associated with a passenger device that is wirelessly connected with a seatback device located in a vehicle. The method includes determining whether an account data for a passenger corresponding to the seatback device includes an indication of the unique identifier. The method includes automatically causing, based on a determination that the account data includes the indication of the unique identifier associated with the passenger device, at least a portion of the account data to be displayed at the seatback device.

Abstract: The invention provides an aircraft passenger accommodation unit comprising a seat, a shell defining an opening that allows a passenger to egress between an aisle and the seat and a door, comprising a base portion, translatable in a first direction across the opening of the shell, between a retracted position and an extended position, and a second portion, translatable relative to the base portion in a second direction that is transverse to the first direction, between a stowed position and a deployed position. When the second portion is in the deployed position, the base portion is able to translate between the extended position and the retracted position. The invention also provides a method of opening and a method of closing a door.

Abstract: A system includes a stowable cupholder apparatus. The stowable cupholder apparatus includes a cupholder member defined by: a top planar member, the top planar member having a cup hole configured to accommodate a cup; a rear planar member extending from the top planar member; and a base planar member extending from the rear planar member, wherein a gap exists between the top planar member and the base planar member. The stowable cupholder apparatus may include a cup grip ring member attached to the top planar member, the cup grip ring member including a ring and cup grip fingers extending inwardly away from the ring. The stowable cupholder apparatus may include a hinge attached to the rear planar member and configured to attach to a structure, wherein the hinge has a range of motion configured to move the cupholder member between a stowed position and a deployed position.

Abstract: A VTOL aircraft (moving object) includes: a first communication path allowing a cabin (passenger compartment) and a component compartment to communicate with each other; and a second communication path for opening the component compartment to the outside of a fuselage. A portion of air in the cabin flows through a first circulation path and returns to the cabin, and the remaining air in the cabin flows through the first communication path and is introduced into the component compartment. A portion of air in the component compartment flows through a second circulation path and returns to the component compartment, and the remaining air in the component compartment flows through the second communication path and is discharged to the outside of the fuselage.

Abstract: A gas turbine engine including a core air passage, a combustor, and a steam line. The combustor is located in the core air passage and combusts hydrogen fuel producing combustion gases. The steam line is fluidly coupled to the core air passage at a position downstream of the combustor to receive a portion of the combustion gases. A conduit thermally coupled to an external surface of an aircraft may be fluidly coupled to the steam line to receive the combustion gases and to heat the external surface. The gas turbine engine may also include a water vapor condenser fluidly connected to the steam line to receive the combustion gases and to condense the water vapor of the combustion gases. At least one nozzle may be fluidly coupled to the water vapor condenser to inject the condensed water into the core air passage.

Abstract: A parachute assembly may comprise a canopy and one or more reefing lines. The one or more reefing lines may limit inflation of the canopy to attenuate impulse load or otherwise mitigate forces exerted by the parachute assembly on cargo or an occupant during deployment of the canopy. The one or more reefing lines may be broken in stages to selectively limit inflation of the canopy followed by selectively permitting inflation of the canopy in stages.

Abstract: A parachute retention system may include a container and a replaceable flap. The container can be attached to a vehicle and can hold a parachute. The container may have a first attachment member. A replaceable flap may have a second attachment member that connects to the first attachment member and that has a flexible barrier portion for enclosing at least a portion of the container to retain the parachute therein.

Abstract: This invention provides an integrated pilot autonomous ejection system with skydiving safety/training which combines sensors, hardware and software technologies to improve pilot training and safety. It offers pilots state-of-the-art cost-effective Virtual Reality Skydiving and flight simulations which prepares pilots on skydiving after ejections and for the dangers of Vertigo and G-LOC which can result in a crash in seconds. Related flight data including cameras which constantly monitors pilots can be used for debriefings/accident investigations which can be done in minutes. The goal is to improve pilot safety during the transition to fully autonomous fleets of fighter jets which have better warrior capabilities.

Abstract: A roll stabilization system for an aircraft ejection seat may be provided. An integral seat sequencer may activate an ejection sequence causing an aircraft ejection seat to be ejected from an aircraft. In various instances, particularly with lighter occupants of the aircraft ejection seat, the aircraft ejection seat may begin a rotational movement. To ameliorate this rotational movement, a roll correction rocket motor is installed on the aircraft ejection seat and selectively activated by the integral seat sequencer in the event that an undesired rotational movement is detected.

Abstract: An assembly is provided for an aerial vehicle. This assembly includes a vehicle body, a gas turbine engine and a support structure. The vehicle body includes a body section. The gas turbine engine includes a stationary structure. The gas turbine engine is housed within the vehicle body. The support structure extends between and is connected to the body section and the stationary structure. The support structure supports the gas turbine engine within the vehicle body. The body section, the stationary structure and the support structure are included in a monolithic body.

Abstract: A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the gear train.

Abstract: Described herein are drone designs, and methods for making same, wherein drones are constructed from interlocking modular nacelles of different types allowing nacelles to be added as needed to increase payload capacity, flight time, and mission capability as the application requires. The modular nacelles can be attached together into an aggregate structure, called a collective, as desired to yield an infinitely expandable and extensible drone. Since each nacelle includes its own battery, nacelles can be added as needed to achieve whatever capability is needed for the application at hand without having to customize the design of the drone.

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines, a first thermal bus, and a first heat exchanger. The first thermal bus includes a first heat transfer fluid in a closed loop flow sequence, between the first gas turbine engine, the or each first electric machine, and the first heat exchanger. Waste heat energy generated by at least one of the first gas turbine engine, and the or each first electric machine, is transferred to first heat transfer fluid. When airspeed of aircraft is less than Mn0.6, the first heat exchanger transfers the waste heat energy from the first heat transfer fluid to a first dissipation medium. When the airspeed of the aircraft is greater than Mn0.6, the first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a second dissipation medium.

Abstract: A thermal management system for an aircraft includes a first thermal bus including one or more first heat sources, a heat sink, a vapour compression system, and one or more second heat sources. The vapour compression system includes a compressor, a condenser, a receiver, a first side of a recuperator, an expansion valve, an evaporator, a second side of the recuperator, and the compressor. A first heat flow (Q1) of waste heat energy generated by the first heat sources is transferred via the first heat transfer fluid to the heat sink. A second heat flow (Q2) of waste heat energy generated by the second heat source(s) being transferred via the evaporator to a refrigerant. A third heat flow (Q3) of heat energy in the refrigerant is transferred via the condenser to the first heat transfer fluid. The controller is configured to ensure that: 1.1*Q2<Q3<3.0*Q2.

Abstract: An aircraft solid state power controller for controlling electric power in an aircraft comprises: a solid state power switching device for switching the electric power, the solid state power switching device comprising an input node, an output node and a control node; a first bypass diode electrically connected between the input node of the solid state power switching device and the control node of the solid state power switching device; and a switchable bypass electrically connected between the input node of the solid state power switching device, and he output node of the solid state power switching device. The switchable bypass comprises a second bypass diode and a bypass switch. An electric bypass current (Ibypass) flowing through the second bypass diode is switchable by switching the bypass switch on and off. The aircraft solid state power controller further comprises a bypass controller configured for switching the bypass switch on/off.

Abstract: A system and method for collecting and analyzing time sequences of signal data produced by a product development effort including but not limited to aircraft signals. A time sequence signal data analyzer receives a signal event specification, searches time sequenced signal data for time slices that meet the signal event specification, analyzes a located time slice that meets the event specification to determine if it satisfies a criterion; and generates a data structure that (a) indicates a portion of the time sequenced signal data that meets the signal event specification and (b) indicates whether or not the portion of the time sequenced signal data that meets the event specification satisfies the analysis criterion or criteria.

Abstract: An unmanned vehicle includes at least one navigation sensor configured to measure navigation data indicative of an environment, at least one status sensor configured to measure status data indicative of operating parameters of a hardware system and a computing system. The computing system includes a navigation engine configured to receive the navigation data and status data and plan a path through the environment and a security engine. The security engine is configured to detect that an unauthorized user is attempting to access the navigation data or the status data, send an alert to an authorized user indicating that the unauthorized user is attempting to access navigation data or status data, and send, to the unauthorized user, simulated data including one or both of simulated navigation data and simulated status data.

Abstract: The avionic calculator is suitable for being carried on-board an aircraft and comprises a multi-core processor configured for executing avionic software applications. The processor includes at least one primary core for communicating with at least one avionic equipment distinct from the calculator, each avionic equipment being carried on-board the aircraft and belonging to an avionic domain; at least one secondary core for communicating with at least one electronic device external to the avionic domain; and a tertiary core for performing at least one filtering of a data message received from a respective device external to the avionic domain and intended for a respective avionic equipment of the avionic domain. Each avionic software application being executable by the at least one primary core or the at least one secondary core.

Abstract: A system for determining the number of passengers in a vehicle, comprising a plurality of sensors arranged to collect data concerning a cabin of the vehicle, wherein the plurality of sensors comprises at least one mm-wave-radar-sensor, and a computation unit, wherein the computation unit is connected to the plurality of sensors and configured to evaluate the data collected by the plurality of sensors in order to determine the number of passengers within the vehicle. Also provided is the vehicle with the system and a method for determining the number of passengers in the vehicle.

Abstract: A ducted fan engine is deiced using a ground support deicing apparatus having a support structure, a plurality of sonic wave transmitters, an imaging device, and a controller that controls the sonic wave transmitters to emit sonic waves at varying frequencies. A deicing program causes the controller to control (a) providing imaging signals to obtain image data from imaging sensors, (b) receiving image data provided by each of the imaging sensors, and generates images of at least one component part of the engine, (c) detecting a presence or an absence of ice on the at least one component part of the engine, and (d) controlling the plurality of sonic wave transmitters to emit sonic waves in a given frequency range so as to remove the ice from the component part of the engine.

Abstract: A method is described for manufacturing a structural element in composite material extending along a straight or curvilinear longitudinal direction, having a Z-shaped cross section and comprising, in its final configuration, a central web and two flanges extending at a given final angle from opposite end portions of the web in respective directions opposite to one another; the method including the steps of: arranging a plurality of layers of composite material on a shaped portion of a forming mold; laminating the layers on the shaped portion so that the web is arranged, at least partially, in its final configuration, that a first flange is arranged in its final configuration at the final angle with respect to the portion of the web arranged in its final configuration, and that a second flange is arranged in its initial configuration at an initial angle distinct from, and greater than, said final angle with respect to the portion of the web arranged in its final configuration; moving a movable portion of the f

Abstract: Embodiments of the present disclosure are directed to systems and methods for autonomously performing and/or facilitating drone diagnostic functions. Prior to a mission of a UAV, an inspection station comprising at least one imaging sensor and at least one directional force sensor may be used to perform a plurality of air worthiness inspections and/or maintenance checks with little to no human intervention. Once the UAV has been determined to be air worthy, it is approved for a subsequent mission.

Abstract: Bi-modal propulsion systems and related methods are generally described. In some embodiments, a bi-modal propulsion system may employ a single propellant for both chemical thruster(s), operating at elevated pressures, and electrical thruster(s) (e.g., electro spray thruster), operating at reduced pressures. The propellant pressure may be reduced to a desired operational range of the electrical thruster(s) using any appropriate construction including, for example, capillaries configured to reduce the pressure of the propellant to an operational range of the electrical thruster(s). In some embodiments, the reduced pressure of the propellant may be lower than a vapor pressure of at least one volatile component of the propellant, leading to the formation of “bubbles” within the propellant line. The presence of alternating gas and liquid phases along a flow path between a propellant tank and the electrical thruster(s) may help to electrically insulate the electrical thruster from the rest of the system.

Abstract: Circular mass accelerators for off-world applications are disclosed herein. An example system includes a base assembly that is configured to interface with a supporting surface, a vertical support assembly extending from the base assembly, a first drive positioned, a shaft connected to the first drive, a hub assembly having a spool, the hub assembly being coupled to a second drive that is located on a terminal end of the shaft, a first tether and a second tether that can be spooled onto and unspooled from the spool by the second drive, and payloads positioned each of the tethers, the payloads being releasably coupled to tethers in such a way that the payloads can be released upon the payloads being rotated to a target launch velocity.

Abstract: An orbital satellite has a bus formed of a bus module and a payload module. Both the bus module and the payload modules may include a pair of panels integrally formed at an angle of for example 90° with respect to each other. Components and electronics supporting the satellite systems may be mounted on the panels of the bus and payload modules. Heat generated by the components and electronics are conducted between panels of the bus module and/or payload module. Sufficient heat transfer between panels occurs as a result of their being integrally formed with each other.

Abstract: A drone with railway driving capabilities has a drone body and at propeller arms. Each propeller arm has a propeller assembly having a propeller driven by a motor assembly. The propeller assembly of at least one propeller arm has a rotatably mounted propeller guard placed coaxially with the propeller. The propeller guard is shaped as a train wheel and is driven by the motor assembly. The propeller arm has an actuated joint for providing the propeller assembly with at least one rotation degree of freedom so that the propeller can be rotated between a flight mode and a driving mode and back. The flight mode involves a more horizontal orientation of the propeller assembly for providing an upwardly directed thrust force to the drone, in operational use, and the driving mode involves a more vertical orientation of the propeller assembly for allowing the respective propeller guard to drive on the railway track.

Abstract: A fixed-wing unmanned aerial vehicle (UAV) includes a propeller gimbal operably coupled to the body of the UAV at the forward end and the propeller gimbal is configured to pivot the propeller about a gimbal pivot axis to change a propeller angle. A controller of the UAV may be configured to control an attitude of flight of the UAV by controlling operation of the motor, the propeller gimbal, and the control surface assembly. The controller may be further configured to determine in-flight trajectory modifications that may require high maneuverability via high angle-of-attack attitudes of flight that are implemented via the propeller gimbal and trajectories determined from a dynamics model of the fixed-wing UAV.

Abstract: An operation system includes: a connecting cable; a winder configured to cause a tensile force to act on the connecting cable; a delivered amount detecting section configured to detect the delivered amount of the connecting cable; a direction detecting section configured to detect a direction of a force acting on a to-be-detected part of the connecting cable; and a position determination section configured to determine a position of an unmanned aircraft. The position determination section determines a distance from a predetermined reference position to the unmanned aircraft based on a detection result from the delivered amount detecting section. The position determination section determines an orientation of the unmanned aircraft on the basis of the to-be-detected part based on a detection result from the direction detecting section.

Abstract: Provided is an unmanned aircraft which is capable of stably taking off. In one example, the unmanned aircraft has an aircraft body which includes an information acquisition device, a plurality of rotary wings, and a protective member disposed around the rotary wings. Each of the rotary wings has a rotation axis which is tilted with respect to a vertical direction by a given angle, such that the rotary wings generate a forward thrust force. The aircraft body has a lower edge which includes a middle lower edge and a forward lower edge, wherein the protective member has a lower edge including the forward lower edge. The forward lower edge is located above the middle lower edge, and the forward lower edge has a rear end located backward of a rear end of the rotary wing.

Abstract: An unmanned aerial vehicle comprises a central body; at least one rotor motor configured to drive at least one propeller to rotate, rotation of the at least one propeller generating thrust and causing the unmanned aerial vehicle to fly; and an integrated micro hybrid generator system configured to provide power to the at least one rotor motor. The integrated micro hybrid generator system includes an engine configured to generate mechanical energy, and a generator motor directly coupled to the engine and configured to generate AC power using the mechanical energy generated by the engine.

Abstract: A method, apparatus, and system for supplying power during the takeoff and landing of an Urban Air Mobility (UAM) aircraft is disclosed herein. A power supplying method is performed by a power supply system comprising a drone and a hub.

Abstract: A flying driving vehicle having a body, a driving interface coupled to the body configured to enable the body to drive on a surface, and one or more driving actuators configured to provide power to the driving interface, a set of propellers coupled to the body, where the propellers' movement keeps the vehicle in place when the surface is in slope, and a controller for controlling the speed of the driving interface, a rotation speed of the set of propellers and a magnitude and direction of thrust applied by the set of propellers.

Abstract: An unmanned aerial vehicle station includes a takeoff-landing unit for an unmanned aerial vehicle to take off and land, a parcel receiver, a parcel deliverer, a storage that stores a plurality of parcels, a replenishment hangar that houses a plurality of unmanned aerial vehicles and replenishes the housed plurality of unmanned aerial vehicles with energy, a parcel transporter that transports the plurality of parcels between the parcel receiver and the storage and between the parcel deliverer and the storage, and an aircraft transporter that transports the plurality of unmanned aerial vehicles between the takeoff-landing unit and the replenishment hangar.

Abstract: Banknote processing equipment is disclosed, which comprises a chamber having an open end for insertion of a bag into the chamber and an extractor adapted to establish a lower ambient pressure between the chamber and the hag to that within the bag to cause the bag to expand into an open configuration during a banknote filling operation, whereby the banknote processing equipment can deposit banknotes in the bag.

Abstract: A process for packaging a product in which a hood is fitted to a tray. The hood is erected by a process that includes a step of providing a flat blank. The flat blank includes a leading panel and a trailing panel. A flat insert is provided and adhered to a panel selected from the group of the leading panel, the trailing panel of the hood, and combinations thereof. The die used to erect the hood includes a die recess. When the die is positioned within the mold, the central portion of the flat insert becomes spaced apart from the hood top. The die recess provides for space to accommodate the central portion of the flat insert becoming spaced apart from the hood top.

Abstract: A bag sealing system for securing one or more items in a closable bag comprises a moveable frame, a closable bag, a closing device and a driving device. The moveable frame can have an open configuration, intermediate configurations and a closed configuration. The closable bag has an open end and a closed end wherein the open end of the closable bag is coupled to the moveable frame. The closing device is provided for securely closing the open end of the bag via a securing element, and the driving device is coupled to the closing device to actuate the closing device to securely close the closable bag.

Abstract: A vertical form fill and seal system supports a sheet of material having material segments and a tube sized for drawing edges of the elongated sheet of material together in an overlapping configuration to form the sheet into a substantially tube shape. The VFFS also includes a sealer that seals the edges of the material to one another and a gusseting mechanism sized for forming a gusseted tuck in each of a left panel portion of the material and a right panel portion of the material. A cutting mechanism removes a first portion and a second portion of a first segment of the material segments in order to form a first cut and a second cut in the first segment and a sealing mechanism folds and seals the first segment at the first cut and at the second cut to provide an end wall with a substantially flat, rectangular-shaped footprint.

Abstract: The present disclosure discloses sanitary tissue product package(s) and/or arrays of sanitary tissue product packages comprising novel actual shoulder area(s) and/or novel actual shoulder area ratio(s). The packages of the present disclosure may comprise reveal(s) that overlap and show roll size (e.g., roll diameter) and/or abutting roll space and/or actual shoulder area.

Abstract: A corner post application system for a load having corners includes corner post applicators and moveable corner post holders. The corner post applicators include a corner post gripper configured to grasp a corner post, with the corner post applicators configured to move the corner post to a corner of the load. The corner post holders each have a clamp and are moveable between a retracted position and an engaged position, where in the engaged position the clamp is configured to engage a respective corner post to press the corner post against the load at the respective corner. When the corner post holders are in the engaged position the corner post applicators are configured to be retracted with the corner posts being held in engagement with the corners of the load by the corner post holders to enable an enveloping machine to initiate placement of a film over the load.

Abstract: The disclosure provides a multifunction vacuum package machine comprising a base and a top lid hingedly connected with each other. The top surface of the base defines a lower chamber, and the bottom surface of the top lid defines an upper chamber. The base is arranged with a heating system, a vacuum pump set, and a control system. The heating system includes a heater and a pressing strip. The heater is disposed on the base and placed outside the lower chamber, and the pressing strip is disposed on the top lid and placed outside the upper chamber. The vacuum pump set is in communication with the lower chamber via the suction opening provided on the wall of the lower chamber. The control system serves to control the heater and the vacuum pump set to perform heat-sealing and suction operations.

Abstract: Methods and devices for sealing a storage vessel or other apparatus are provided. A piston moves from a first position to a second position within a body to compress a sealing element, such as a metallic ring. One or more attachment elements connect the piston to the body. A removable pipe can be used for pump-out.

Abstract: A packaging material producing machine, comprising a transport device being configured to guide and move a web of packaging material, and a processing system is provided. The processing system comprises a functional unit connected to the at least one carrier and a positioning arrangement that comprises a fixed support and a bar arranged and moveable in parallel with said support, and at least one carrier comprising an attachment device being configured to selectively attach the carrier to only one of said fixed support and said bar.

Abstract: A carousel-type packaging machine comprising a plurality of workstations adapted to carry out a sequence of packaging operations and a rotating carousel arranged to move the containers through said workstations, wherein the carousel is arranged with a horizontal rotation axis and includes counter-rotating gripping members adapted to maintain containers in a constant trim during the rotation of the carousel through the various steps of the packaging process; the gripping members are further equipped with movable grippers controlled by motors associated with the workstations.

Abstract: A packaging material sealing device includes a first sealing jaw and at least a second sealing jaw and at least one movement unit, which includes a first actuator and at least a second actuator for actuating the two sealing jaws along a sealing direction, and at least one control unit. In at least one operating state, the control unit controls the two actuators for setting an asymmetrical sealing force for the two sealing jaws.

Abstract: A dehumidification device of a package thermal-shrinking oven includes at least one thermal-shrinking oven body for being combined with a packaging and conveying strip for conveying an object-to-be-packaged and having a lower portion that is provided with at least one pair of connecting portions, at least one steam conduit having a lower end connected with at least one steam device, at least one thermal isolation board mounted to an upper portion of interior of the steam conduit and enclosing two sides of the packaging and conveying strip, at least one pair of first heaters respectively mounted to two sides of exterior of the steam conduit, at least one second heater mounted to a bottom of interior of the steam conduit, and at least one pair of third heaters respectively mounted to two sides of exterior of the thermal-shrinking oven body.

Abstract: A system for aseptically transferring components from a container into a pharmaceutical isolator. The system includes a single-use flexible container that holds the components, a decontamination device that is mounted on the isolator, and a transfer table that facilitates transferring the components into the isolator. The container is placed on the transfer table and a front end attached to the decontamination device. The interior of the decontamination device and a front end of the container are decontaminated and the transfer table then mechanically brought into a position which allows the components to slide in a gravity-assisted manner into the isolator.

Abstract: A method, apparatus and program product may evaluate a packaging material to determine various metrics associated with the packaging material. An apparatus may be used to sense flaws in packaging material, and in some instances, to accommodate such flaws by temporarily increasing a dispense rate of a packaging material dispenser.

Abstract: A packaging material sealing device, in particular cross seam packaging material sealing device for a vertical packaging machine, includes a first sealing jaw and at least a second sealing jaw, at least one movement unit for actuating the two sealing jaws along a sealing direction, and at least one control unit. In at least one operating state the control unit controls a rotation of the two sealing jaws relative to a transport direction of a packaging material. At least two guiding rails of the movement unit for moving the two sealing jaws along at least the sealing direction each have clearance with respect to their bearings in order to allow rotation of the two sealing jaws relative to the transport direction.

Abstract: Disclosed is a method for producing containers filled with beverages, wherein a container closure has a closure cap screwed onto a mouth of the container, a securing device arranged in a longitudinal direction of the container below the mouth, a connecting strand which connects the securing device to the closure cap, a first fastening section which the connecting strand is attached to the closure cap, and a second fastening section which the connecting strand is arranged on the securing device, wherein the containers are transported using a transport device and are inspected using an inspection device, wherein a rotational position of the container closure relative to the container and/or a rotational position of the container is determined, wherein after the inspection, the containers are provided with a label and/or a print, wherein the determined rotational position of the container closure is taken into account.