Abstract: A cabin air ventilation system for a plurality of seat rows in an aircraft and an aircraft with such a cabin air ventilation system. The air ventilation system comprises a main body configured to be mounted to an underside of an overhead stowage compartment, the main body defining an inner volume, and a plurality of air ventilation outlets arranged in the main body, each of the ventilation outlets being configured to generate an airflow from the inner volume of the main body to one of the plurality of seat rows. At least some of the plurality of air ventilation outlets are arranged to generate the respective airflow to different seat rows.

Abstract: A water extractor for an environmental control system of an aircraft includes a separation mechanism configured to divide an airflow into a first airflow and a second airflow. The separation mechanism includes an inlet conduit, a body in fluid communication with the inlet conduit, and at least one coalescing feature arranged within an interior of the body. A water extraction vessel is arranged in fluid communication with the separation mechanism. The water extraction vessel includes a first portion for receiving the first airflow and a second portion for receiving the second airflow. The first portion is configured to collect and remove water from the first airflow.

Abstract: A hybrid aircraft powerplant includes a turbine engine having a first shaft configured to output power from the turbine engine, a bypass fan, and an electric machine. The hybrid aircraft powerplant further includes a first mechanism configured to selectively engage the first shaft with a second shaft connected to the electric machine such that the power is output from the turbine engine to the electric machine. The hybrid aircraft powerplant further includes a second mechanism configured to selectively engage the first shaft with a third shaft connected to the bypass fan to output the power from the turbine engine to the bypass fan.

Abstract: A propulsion system including an electric motor, the output of which drives a propeller, and a reversible fuel cell comprising a cathode and an anode connected to the electric motor, a supply line connecting the fuel cell to the dihydrogen tank and a feed line connecting the fuel cell to the temporary water tank.

Abstract: A multi-material component is provided including two members formed of different materials joined together at a multi-material join. The two members have complementary protrusions that form a multi-material join with a zig-zag interface, such that a tension between them is experienced in at least part as a shear force at the interface between the protrusions. The component further includes a third member connected to the first member by a lattice, which is capable of elastic deformation so as to substantially isolate the interface between the complementary protrusions from deformation of the third member such as that caused by thermal expansion. Methods of designing and constructing such a component in a single piece via additive manufacturing are provided. The component is particularly suitable for use in pylons connecting jet engines to aircraft wings.

Abstract: A swivel access structure for an engine nacelle, including a door plate, a first fastener, second fasteners, a door frame, and one or more flame shields. The door plate is selectively rotatable about the first fastener, and the second fasteners selectively release the door plate to allow its rotation about the first fastener from a closed configuration to an open configuration. The door plate is rotatably attached to the door frame via the first fastener. The door frame has a frame opening covered by the door plate when the door plate is in the closed configuration and exposed when the door plate is in the open configuration. The one or more flame shields cover an inner side of the door plate and/or an inner side of the door frame. The swivel access structure provides access within the nacelle without spring arrangements that are more susceptible to fail fire testing.

Abstract: A power control device is provided for an aircraft. The power control device may include at least one first battery, a second battery having a lower power density and higher energy density than the at least one first battery, at least one lift motor connected, via a first electrical path, to the at least one first battery, a cruise motor connected, via a second electrical path, to the second battery, and a power control circuit configured to control the at least one first battery, the second battery, the at least one lift motor, and the cruise motor.

Abstract: A method of controlling an aircraft engine includes determining a reference thrust that corresponds to a thrust setting parameter at a selected aircraft operating parameter for a current airspeed according to a predefined relationship. An adjustment factor is determined based on a relationship between the current aircraft operating parameter and the selected aircraft operating parameter. A prescribed thrust at the current aircraft operating parameter is determined by applying the adjustment factor to the reference thrust. A value of a thrust setting parameter that provides the prescribed thrust at the current aircraft operating parameter is used to operate the aircraft engine at the prescribed thrust.

Abstract: A fuel quantity indicator system (FQIS) for an aircraft or other vehicle includes memory/data storage and a fuel quantity processing unit (FQPU). A neural network trained via machine learning and running on the FQPU receives fuel quantity (FQ) inputs from fuel tank sensors, e.g., tank density, fuel volume, water presence within the tank, at or near a given measurement time. The neural network additionally receives fuel flow (FF) inputs from flow sensors at the measurement time, indicating fuel flow to engines and auxiliary power units (APU) of the vehicle. Based on the FQ inputs and the FF inputs, the neural network calculates an estimated fuel quantity (EFQ) remaining, e.g., across all fuel tanks at or near a particular measurement time.

Abstract: A tank comprising one or several anti-sloshing wall arrangements, with a frame portion and a door portion wherein the frame portion is fixed to a tank wall of the tank, and it edges an opening, and wherein the door portion is configured to selectively close or unclose the opening. Also an aircraft comprising such tank and at least one engine, the engine being configured to be fed with fuel, in particular with liquid hydrogen, contained in the tank.

Abstract: A tank for an aircraft, the tank comprising two pressure bulkheads which are connected to each other by a tank wall which is at least partially formed by a portion of a skin of the aircraft's fuselage. The tank further comprises at least one anti-sloshing wall at least partially enclosing one or several openings and at least partially formed by a belonging frame stabilizing the skin. Also a fuselage with such tank, and an aircraft with such fuselage.

Abstract: An aircraft comprising a dihydrogen transport pipe, a pipe shroud around the transport pipe, a dihydrogen tank, a chamber delimiting a fluidtight volume containing a system fluidically connected to the transport pipe which joins the pipe shroud through a chimney, an extraction chamber into which the chimney and the pipe shroud open, and a device for extracting to the outside the gases present in the extraction chamber.

Abstract: An aircraft comprising at least one secondary structure which separates an inner zone from an outer zone and at least one hydrogen supplying device connecting a hydrogen tank and a motor, and having at least one portion fitted with shut-off valves for isolating it in the event of a leak. The portion has at least one outer enclosure, at least one inner element that is located in the outer enclosure and carries the hydrogen, and at least one interior zone located between the inner element and the outer enclosure, the hydrogen supplying device comprising at least one ventilation system configured to vent gases present in the interior zone toward the outer zone of the secondary structure.

Abstract: An aircraft propulsion system includes a primary energy conversion device that uses a cryogenic fuel and air to generate power and thermal energy. The primary energy conversion device is mounted to a first structure of an aircraft. A bottoming cycle includes a working fluid that is circulated within a closed circuit that includes a bottoming compressor section and a bottoming turbine section. At least a portion of the bottoming cycle is mounted to a second structure of the aircraft that is different from the first structure. A primary heat exchanger provides communication of thermal energy from the primary conversion device to the working fluid of the bottoming cycle and is mounted within the first structure of the aircraft proximate the primary energy conversion device.

Abstract: An aircraft propulsion system includes at least two gas turbine engines and a bottoming cycle system where a working fluid is circulated within a closed circuit that includes a bottoming compressor section and a bottoming turbine section. Each of the at least two gas turbine engines include a primary heat exchanger for communicating thermal energy into the working fluid of the bottoming cycle.

Abstract: An aircraft propulsion system includes a core engine, a first bottoming cycle and a second bottoming cycle that utilize different working fluids having different critical temperatures such that each of the bottoming cycles have different heat absorption capabilities.

Abstract: An aircraft fuel tank venting and inerting arrangement comprising a fuel tank, a venting fluid flow path between the fuel tank and a venting outlet, an inerting fluid flow path for delivering inerting fluid to the fuel tank, at least part of the venting fluid flow path being provided by a fluid flow conduit and at least part of the inerting fluid flow path being provided by the fluid flow conduit. An aircraft comprising such an arrangement and a method of venting and inerting an aircraft fuel tank.

Abstract: A hydrogen fuel including a safety marker and a method and apparatus for adding the safety marker to the hydrogen fuel. The hydrogen fuel may be stored in a tank in a liquid phase and then heated to at least one of a gaseous phase and a supercritical phase. The safety marker may be added to the hydrogen fuel when the hydrogen fuel is in the at least one of the gaseous phase and the supercritical phase after heating the hydrogen fuel. The hydrogen fuel may be delivered in the at least one of the gaseous phase and the supercritical phase to a power generator, such as a gas turbine engine. The safety marker may be a visual safety marker, such as a noble gas, or an odorant.

Abstract: A system and method of alerting a pilot of an aircraft are provided. The method includes obtaining a track list of detected objects; for each detected object, determining a first alert factor based on a rate of closure to the aircraft and determining a second alert factor based on an azimuth. An alert list is created including each of the detected objects along with its corresponding first and second alert factors. The alert list is ordered in an order of priority, and the alerts are displayed on a light bar disposed in a cockpit of the aircraft.

Abstract: Systems and methods for enabling charged (ionized) air mass measurement for reliable air data computation onboard an aircraft. Ionic charge sensing may be used to derive air data having improved reliability. The systems and methods for ionic charge sensing employ an emitter electrode and two or more collector electrodes, which electrodes are disposed in proximity to the exterior skin of the aircraft and exposed to ambient air. The emitter electrode is positioned forward of the collector electrodes. The system further includes a solid-state ionic air data module that converts currents from the collector electrodes into air data parameter values. More specifically, the ionic air data module is configured to sense currents induced in the collector electrodes in response to corona discharge produced by the high-voltage emitter electrode.

Abstract: A system and method for monitoring and verification of digital gyroscopic sensors determines a primary angular velocity vector via a primary digital gyroscopic sensor triad and two or more backup angular velocity vectors via backup analog gyroscopic sensor triads. Based on additional aiding parameters, the aircraft attitude and heading reference system (AHRS) determines a primary attitude solution based on the primary angular velocity vector and one or more backup attitude solutions based on the backup angular velocity vectors. If no other faults are present with respect to the primary and backup gyroscopic sensor triads (e.g., the primary and backup triads are otherwise consistent in their measurements), and the primary attitude solution sufficiently deviates from the backup attitude solutions, the AHRS detects a solution fault in the primary gyroscopic sensor triad.

Abstract: An abnormality warning system provides an abnormality warning for multiple motor systems that drive a motor used correspondingly to each of multiple rotors included in an electric aircraft. The abnormality warning system includes an abnormality determination unit and a warning level setting unit. The abnormality determination unit determines an abnormal one of the motor systems. The warning level setting unit sets a warning level to warn abnormality, based on at least position information of the rotor in the electric aircraft or the usage of the rotor corresponding to a motor system determined to be abnormal by the abnormality determination unit.

Abstract: The present disclosure relates to a system for monitoring and/or detecting an operational state of a movable component of an aircraft, wherein the system has a movable component and a monitoring device, wherein the system also has a combination sensor connected to the monitoring device, which is designed and arranged to detect a kinematic and/or kinetic state of the component, wherein the monitoring device is designed to monitor and/or detect an operational state of the component.

Abstract: A vision-based navigation method that does not depend on GPS signal for landing AAM aircraft. The Vision-Based Approach and Landing System (VALS) uses images captured from a camera for Advanced Air Mobility (AAM) approach and landing in GPS-denied environments, which offers a potential Alternative Position, Navigation, and Timing (APNT) solution. VALS utilizes a computer vision algorithm called Coplanar Pose from Orthography and Scaling with Iterations (COPOSIT) to estimate the position and orientation of the camera based on coplanar features. VALS also includes an extended Kalman filter that uses IMU measurements in a prediction step and the COPOSIT estimation results in a correction element. Combining IMU with vision creates a sensor fusion navigation solution for GPS-denied environments.

Abstract: Systems and methods are disclosed for lighting a vehicle. A system includes a plurality of lights disposed on a vertical take-off and landing (VTOL) vehicle configured to turn on and off, change color, and/or change intensity. The system further includes a controller configured to determine a lighting scheme for the plurality of lights, the lighting scheme including a setting for the plurality of lights, the setting including one or more of turning the plurality of lights on or off, setting a color of the plurality of lights, and setting an intensity of the plurality of lights, determine a location in or associated with the VTOL vehicle, wherein the lighting scheme is configured to guide a person to the location, and transmit a signal to the one or more lights to execute the lighting scheme to guide the person to the determined location.

Abstract: An automatic umbilical connector separating mechanism is separable in the same direction as the motion of a flying object. After the two connectors are connected, they are securely held in place by trigger mechanisms to prevent self-loosening and signal loss. When the flying object is launched and slides on the launch rail, the connector frame moves forward, releasing the trigger mechanisms. With tension from the chains and the force from the spring, the male connector frame pulls the male connector in the opposite direction. As a result, the automatic umbilical connector separating mechanism moves in the same direction as the flying object on the pins and guide holes of the connector frames. After the guide pins reach the end of their travel, the spring pulls the male connector frame up the launch pad, while the spring-loaded hinge folds the female connector frame into the flying object body.

Abstract: Examples are disclosed that relate to automated tracking of aircraft turnaround. One example provides a method, comprising obtaining object classification data for a plurality of image frames, the object classification data comprising location data for a fuselage of the aircraft and location data for a loadable object, determining a first distance between the fuselage and the loadable object in a first frame of the plurality of image frames, and determining a second distance between the fuselage and the loadable object in a second, later frame of the plurality of image frames. The method further comprises determining that the loadable object is being loaded based at least on the second distance being less than the first distance, or determining that the loadable object is being unloaded based at least on the second distance being greater than the first distance, and outputting the determination.

Abstract: Example implementations relate to predicting the health of an aircraft component based on a hybrid digital twin. A computing system receives nominal operational data and operational data from aircraft sensors based on flights by an aircraft to evaluate an aircraft component on the aircraft. The computing system can estimate first parameters corresponding to the aircraft component based on a nominal digital twin using the nominal operational data outside respective alerts corresponding to the aircraft component and second parameters corresponding to the aircraft component based on an operational digital twin using the operational data. The computing system then estimates a first health parameter and a second health parameter for the aircraft component based on the first parameters and the second parameters, respectively.

Abstract: A satellite comprising a body and a generally planar structure extending from the body. One or more radio frequency “RF” antennas, an amplification system for rf signals, and a power distribution system for the amplification system are mounted on the generally planar structure. Two or all of the power distribution system, the one or more RF antennas and the amplification system are arranged on respective parallel boards forming part of the generally planar structure. One or more of the parallel boards and the components mounted thereon may be connected to another similar board to form, respectively a larger power distribution system, antenna array or amplification system, for example arranged in a plurality of modules, each comprising at least one antenna, at least one power distribution system and at least one amplifier supported on at least two respective boards.

Abstract: A driving mechanism controller included in a capturing device causes one or more driving mechanisms to spread a tethering member having an elongated shape to the outside of a housing by a target spread length. The driving mechanism controller, when an artificial space object is located in the area surrounded by the tethering member, causes the one or more driving mechanisms to retract the tethering member to the inside of the housing until at least a part of the tethering member comes into contact with the artificial space object. The tethering member is stable in a first shape having a curved section orthogonal to a linear extending direction of the tethering member.

Abstract: When a deorbiting satellite, which is one of artificial satellites belonging to a first satellite constellation, deorbits and drops from an orbit of a first orbital altitude zone, a second satellite constellation widens a relative angle of any adjacent two orbital planes of a plurality of orbital planes and thereby allocates a free orbit area in a second orbital altitude zone. The deorbiting satellite passes through the free orbit area of the second orbital altitude zone.

Abstract: A spacecraft is disclosed including a frame, an electrical device powered and/or controlled by electrical cables, and a system for orienting the electrical device, which orientation system includes at least two rotary actuators with non-parallel axes (?a, ?b), a junction part between the two rotary actuators, one or more guide forks, arranged outside the junction part and fastened to the latter, each guide fork including fingers configured to support the electrical cables and to form a guide path for said cables so that the electrical cables never exert, on the rotary actuators, a torque higher than the torque capacity of the actuators, at least one of the forks having a main axis which passes through the center of intersection of the axes of rotation of the actuators.

Abstract: A fluid transfer interface is provided. The fluid transfer interface includes one or more of first and second interface portions. The first interface portion includes a first portion of a fluid connector and one or more ferromagnetic surfaces. The second interface portion includes an extendable second portion of the fluid connector and one or more electropermanent magnets, laterally disposed around the second portion of the fluid connector, configured to be magnetized or demagnetized in unison. The one or more electropermanent magnets are further configured to provide attraction force to the one or more ferromagnetic surfaces when magnetized and couple the first interface portion to the second interface portion and provide no attraction force to the one or more ferromagnetic surfaces when demagnetized and allow the first interface portion to be decoupled from the second interface portion.

Abstract: A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.

Abstract: A unified data library is referred to by a surveillance satellite group to track a flying object, a surveillance ground facility to control the surveillance satellite group, a communication satellite group to transfer flying object information acquired by the surveillance satellite group, a communication ground facility to control the communication satellite group, a coping asset to cope with the flying object, and a coping ground facility to control the coping asset. The unified data library includes a database having stored therein orbit information of the surveillance satellite group, orbit information of the communication satellite group, position information of the coping asset, and a plurality of flying path models having flying paths of the flying object modeled therein.

Abstract: The system is configured to generate a display of a tagging interface. The tagging interface may include a stitching selector. In response to a user selection of (1) a destination element that includes a first name identifier, (2) a source element that includes at least one of the plurality of pixels such that at least one of the plurality of pixels corresponding to longitude-time points comprising a second name identifier, and (3) the stitching selector, the system can be configured to indicate that the source element comprises the first name identifier.

Abstract: A landing and docking system for an unmanned aerial vehicle (UAV), the system comprises two main parts, a docking unit configured to be attached to a UAV and a mating ground base platform. The docking unit has clamping arms that can swing outwardly by hinges that have a spring function, and a downwardly extending cone portion shaped to mate with a corresponding drogue shaped receptacle in the ground platform. The clamping arms comprise inwardly extending hook parts to hold the docking unit in place in the ground base platform. The system preferably comprises a sensor array in the cone, that comprises at least one but preferably at least two or more sensors such as optical lenses and/or other sensors. The system with sensor array thus provides a rugged and sturdy alternative to conventional camera carrying UAVs with gimbal mounted camera.

Abstract: An apparatus and methods for producing at extremely high production speeds small pouches filled with tobacco or other granular, powdered or solid content is provided. An endless web substrate, with or without flavor film thereon, is formed into a tubular shape with a longitudinal seam. The tube is cut to individual lengths, and a procession of tubes is crimp-closed at one end, filled and crimp-closed at the other end to complete pouch production. During production, the seams formed at the crimped ends of the pouch are parallel to one another and the longitudinal seam of the pouch is midway between the sides of the pouch and orthogonal to the seams formed at the crimped ends of the pouch.

Abstract: A medical dispensing system with dispensing and pathway components, each of which of a plurality of dispensers and pathways, respectively. The dispensing and pathway components are controlled to minimize contamination between the items being dispensed. Both the dispensing and pathway components have arcs around which the dispensers and pathways are arranged.

Abstract: At least one example embodiment relates to a system for filling a plurality of containers with oral products. The system comprises a container station and a shuttle assembly. The container station is configured to provide a plurality of containers. The shuttle assembly is configured to move between a first shuttle position to receive a plurality of oral products and a second shuttle position to deposit the oral products into the containers. At least one example embodiment relates to a method of filling a plurality of containers with oral products.

Abstract: Methods and apparatus for unitizing groups of individual packages into pallet loads, stabilizing the loads and facilitating general movement of the pallets, including the loading and unloading of pallets into and out of transport vehicles, includes wrapping the loads with stretchable crepe paper, rather than conventional plastic wrap material. Crepe paper can be produced and recycled with less environmental impact than plastic wrap. These methods involve a new use for crepe paper, and a new use for conventional plastic-wrapping equipment.

Abstract: According to illustrative embodiments, a novel pallet wrap is provided. In some preferred embodiments, the pallet wrap includes: an expandable slit sheet paper having a slit pattern including a plurality of slits extending in a cross direction that forms a plurality of open cells upon expansion in a machine direction, and a non-slit paper support wrap, wherein said expandable slit sheet paper is configured to be wrapped around a pallet assembly and said paper support wrap is configured to surround at least a portion of said expandable slit sheet paper wrapped around said pallet assembly.

Abstract: A binding machine is configured to wind and bind an object to be bound with a band-shaped tape. The binding machine includes: a tape holder configured to hold a first end that is one end of a first part that is a part of the tape; and a tape remover configured to abut against the first end and configured to remove the tape from the tape holder.

Abstract: A binding machine is configured to wind and bind an object to be bound with a band-shaped tape. The binding machine includes: a tape feeder configured to hold a first end that is one end of a first part which is a part of the tape, configured to move the tape to a position overlapping with a second end that is another end of the first part, and configured to surround the object to be bound with the tape. The tape feeder includes a tape holder configured to hold the tape by moving in a lateral direction of the tape from a side edge side of the tape and clamping the first end.

Abstract: A system for compressing and packing pipe insulation includes a compression member that is movable along a first axis to compress pieces of pipe insulation. A stacking bay includes opposing walls that are spaced apart from one another. At least one of the two opposing walls is movable relative to the other of the two opposing walls along a second axis to adjust a lateral distance between the opposing walls to accommodate an increasing size of the pieces of pipe insulation along the second axis. The first axis is generally orthogonal to the second axis. A packing member that applies a force along a third axis to the pieces of pipe insulation after being compressed. The third axis is generally orthogonal to the first and second axes. The first axis is generally orthogonal to the second axis. The compression member is aligned with a space formed between the opposing walls.

Abstract: A binding machine is configured to wind and bind an object to be bound with a binding material. The binding machine includes: a binding material feeder configured to move a first end that is one end of a first part which is a part of the binding material to a position overlapping a second end that is another end of the first part, and configured to surround the object to be bound with the binding material; and a binding portion configured to bind an overlapped part where the first end and the second end are overlapped.

Abstract: A tape clamping method is used for clamping a band-shaped tape surrounding an object to be bound with a staple. The method includes: overlapping a first end that is one end of the tape and a second end that is another end of the tape; and clamping the tape by deforming the staple in a manner of clamping an overlapped part of the first end and the second end from an outer side of at least one of a pair of side edges of the tape.

Abstract: A method for packaging products in a substantially oxygen free environment. The method includes providing a containment environment including a main chamber formed by main chamber walls, an exhaust portion for removing ambient air from the main chamber, an intake portion for introducing inert gas into the main chamber, and a selectively sealable access point for providing access into and out of the main chamber. The method includes providing a bulk product dispenser and one or more individual bottles into the main chamber, and sealing the main chamber at least by closing the sealable access point. The method includes purging ambient air from the main chamber through the exhaust portion and introducing inert gas into the main chamber through the intake portion. The method includes transferring a product from the bulk product dispenser to each of the one or more individual bottles, and sealing each of the individual bottles.

Abstract: A fixture for unpacking a carton, wherein the fixture includes a fixed portion and a rotating portion. The fixed portion includes a first frame, a first plurality of suction components, and a first driving component arranged on the first frame. The a rotating portion includes a second frame connected to the first frame and capable of rotating or being fixed relative to the first frame under the driving of the first driving component, a third frame arranged on the second frame, a second plurality of suction components arranged on the third frame, and a second driving component connected to the second frame and the third frame.

Abstract: System, method, and device for fabricating a capsule are provided. A gripping apparatus includes a rotary actuator and a rotary linkage disposed about a periphery of the rotary actuator. A plurality of intermediate linkages is coupled to the rotary linkage. Each intermediate linkage includes an input end portion coupled to the rotary linkage, an output end portion disposed below the input end portion, and a jaw disposed on the output end portion. The gripping apparatus includes a plurality of compliance linkages. Each compliance linkage includes a first end portion coupled to either the output end portion or the jaw of a respective intermediate linkage, and a second end portion substantially orthogonal to the respective intermediate linkage.