Abstract: A self-contained marine propulsion impeller system, whereby, the impeller is driven from an outer perimeter of a cylinder, thereby, creating thrust. The impeller is connected to an inner wall of the cylinder. The cylinder has a primary end located opposite a secondary end. The primary end of the cylinder has a primary sealing member and a primary bearing member. The secondary end of the cylinder has a secondary sealing member and a secondary bearing member. A plurality of magnets are connected to an outer perimeter wall of the cylinder. The plurality of magnets are located between the first bearing member and the second bearing member. The cylinder is surrounded by a housing. At least one coil winding is connected to an inner wall surface of the housing. The rotating cylinder is suspended within the housing by the first bearing member and the secondary bearing member.

Abstract: A Shipboard Auditory Sensor (SAS) for detection and classification of acoustic signaling at sea is capable of detecting whistles blasts from other vessels in accordance with Rules 34 and 35 of COLREGS to support autonomous operations in a maritime environment.

Abstract: An airframe leading edge part designed to be replaceable fixed to a structural portion which during use moves through the air. The airframe leading edge part includes first and second longitudinal joint edges adapted to fit the structural portion. At least one joint is provided between the structural portion and at least one of the longitudinal joint edges. The joint is adapted to break in the event of a object strikes and deforms the airframe leading edge part during use. The joint is designed to break at beforehand determined maximum joint strength of the joint. Also a repair method for exchanging a damaged leading edge.

Abstract: A method of making a panel assembly that includes forming a thermoplastic panel, placing a thermoset portion into a pocket in a mold, placing an attachment member into the pocket in the mold, positioning the thermoplastic panel in the mold, cooling the thermoplastic panel while heating the thermoset portion to flow at least a portion of the thermoset portion into openings defined in the thermoplastic panel, and cooling the panel assembly so that the thermoset portion hardens, thereby securing the attachment member to the thermoplastic panel.

Abstract: A hybrid carbon/fiberglass structural component or beam for an aircraft is constructed with layers of strips of glass fibers interspersed with layers of strips of unidirectional carbon fibers where the carbon fibers are oriented only in alignment with or along the longitudinal direction of the length of the beam thereby adding strength and stiffness to the beam while reducing weight and manufacturing costs.

Abstract: A flow body for an aircraft with a leading edge and a trailing edge includes a first spar, a second spar, and an external skin that spans from the leading edge to the trailing edge and on both sides rests on the spars. At least one of the first spar and the second spar includes a web and two spaced-apart flanges that enclose the web, on which flanges the skin that spans the respective spar is arranged. At least one of the first spar and the second spar includes at least one load introduction fin that forms an integral component with the web and extends outwards by way of one of the flanges and the skin that rests on the spars.

Abstract: There is provided a system for predicting loading of a landing gear including, a plurality sensors positioned proximate to the landing gear. The plurality of sensors measure strain applied to the landing gear, and each sensor yielding strain data. The system further includes a processor that receives the strain data from the plurality of sensors and predicts at least one ground load based on strain data. There is further provided a method for predicting loading of a landing gear. The method includes powering a plurality of sensors located proximate to a landing gear structure, interrogating the plurality of sensors via data acquisition circuitry to yield strain data, instructing the data acquisition circuitry as to a sampling rate and data resolution to be used for the interrogating, and, finally, processing the strain data to predict a ground load.

Abstract: Control system (1) comprising a control rod (5) extending between a first zone (2) situated in a hydraulic chamber delimited by a chamber wall (3) and a second zone (4) situated outside the hydraulic chamber. The control system (1) further comprising a seal (6) arranged around and against this control rod (5) to oppose the passage of fluid between the first and second zones (2, 4). The system further comprises a guide piece (7) assembled removably with respect to the chamber wall (3), the seal (6) is assembled inside the guide piece (7) so as to allow relative movement of the rod (5) with respect to the guide piece (7) while at the same time achieving sealing between the first and second zones (2, 4).

Abstract: A method for controlling brakes is provided. The method may include the steps of detecting an aircraft speed, determining the aircraft speed is within a range from an antiskid-dropout speed to a locked-wheel-protection-engagement speed, and determining an input of a pressure controller has a value less than a pressure maximum threshold. A current command that is output from the pressure controller may be detected at or above a threshold value. The states of the pressure controller and pressure controller input may be reset in response to the current command being at or above the threshold value for a predetermined duration.

Abstract: An aircraft includes: a plurality of rotor units each including a propeller and a motor that drives the propeller; and a shock absorber covering the entire vertical length of lateral sides of the plurality of rotor units.

Abstract: A multirotor flying vehicle including at least one rotor support frame organized on a geometric grid, with a plurality of rotor assemblies coupled to the at least one rotor support frame. At least one power supply is coupled to and powers the rotor assemblies. A control system is coupled to the rotor assemblies and is configured to operate the vehicle.

Abstract: A compound rotorcraft with a fuselage and at least one main rotor, the fuselage comprising a lower side and an upper side that is opposed to the lower side, the at least one main rotor being arranged at the upper side, wherein at least one propeller is provided and mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing that is arranged at an upper wing root joint area provided at the upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at the lower side of the fuselage, the upper and lower wings being at least interconnected at an associated interconnection region.

Abstract: A non-ducted tail rotor comprising a hub and at least five blades, each of the blades extending to a free end that, in rotation, describes a circle presenting a given “maximum” radius. The hub is rigidly secured to a drive shaft, the hub comprising a hollow circular body centered on an axis of rotation, the body presenting an “internal” radius between the axis of rotation and an outer periphery of the body, the internal radius lying in the range 0.2 times to 0.4 times the maximum radius, each blade presenting a root extended by an airfoil element projecting from the body, extending from the root to the free end, the root being swivel-hinged to the outer periphery about a pitch axis.

Abstract: The invention relates to an aircraft which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft has a support structure, a wing structure, at least three and preferably at least four lifting rotors and at least one thrust drive. The wing structure is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure has at least one mainplane provided with a profile that generates dynamic lift. The wing structure is preferably designed as a tandem wing structure. Each of the lifting rotors is fixed to the support structure, has a propeller and is designed to generate a lifting force for the aircraft by means of a rotation of the propeller, said force acting in a vertical direction. The thrust drive is designed to generate a thrust force on the support structure, said force acting in a horizontal direction. The lifting rotors can have a simple construction, i.e.

Abstract: A system includes a first mast torque transfer system, a second mast torque transfer system coupled to the first mast torque transfer system, and a torque limiting system. The torque limiting system includes a first sensor configured to determine a torque of the first mast torque transfer system, a second sensor configured to determine a torque of the second mast torque transfer system, and a processor configured to determine a differential torque between the torque of the first mast torque transfer system and the torque of the second mast torque transfer system and configured to control at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque.

Abstract: An inflatable package enclosure for use on an aerial vehicle including an inflatable exterior chamber, a first inner cavity positioned within the inflatable exterior chamber, an inflation valve positioned on the inflatable exterior chamber, and a handle on the inflatable exterior chamber for securing the inflatable package enclosure to the aerial vehicle, wherein when the inflatable exterior chamber is inflated and when a package is positioned in the first inner cavity, inner surfaces of the inflatable exterior chamber conform to outer surfaces of the package to secure the package within the inflatable exterior chamber.

Abstract: The disclosure is directed to systems and methods for autonomously picking up water in support of fire fighting missions using aerial vehicles. More particularly, the disclosure is directed to systems and methods for picking up water in support of fire fighting missions using onboard sensing and decision making processes with application of the fire retardant using unmanned aerial vehicles.

Abstract: A method to load stores on an aircraft, the method may be controlled by one or more controller and may include one or more acts of loading stores onto corresponding lift portions; determining a relative position of the aircraft; positioning the stores relative to the determined position of the aircraft; and securing the stores to corresponding hardpoints (HPs) of the aircraft.

Abstract: There is described a system and method for setting virtual boundaries (402A-D) on an interactive sidewall display device (202) in a vehicle (102), the virtual boundaries (402A-D) defining individual passenger-specific regions for user interaction.

Abstract: A suite divider for a passenger suite seating arrangement including separate first and second panels adapted to be deployed along a top of a partition wall separating laterally adjacent passenger suites, the first and second panels adapted to be stowed near respective first and second ends of the partition wall to connect the laterally adjacent passenger suites, and horizontally driven together to separate the laterally adjacent passenger suites.

Abstract: A system and method for aircraft passenger seating allows traditional passenger seats, which have fixed configurations, to meet new specifications. A bottom frame and backrest frame from a traditional passenger seat is used to form a new passenger seat. Features, such as improved cushioning, telescopic or fixed headrests, rotatable or fixed footrests and improve armrest assemblies may be added as part of the new passenger seat.

Abstract: A cooling assembly (15) includes a conduit (16) including a side wall (17) and a fan (20) that includes a rotating electric machine (32), a power supply module (35) including three distinct single-phase self-transformers (79a, 79b, 79c), each single-phase self-transformer being magnetically decoupled from one another, each single-phase self-transformer (79a, 79b, 79c) surrounding the side wall (17) of the conduit.

Abstract: Systems and methods are disclosed for providing a controlled temperature in a control volume. Such systems include a main chamber (defining the control volume), a mixing chamber and a gasflow source. The mixing chamber is in selective fluid communication with the main chamber, and has at least one mixing chamber inlet, and a ram air inlet for allowing ram airflow at a first temperature to be channeled into the mixing chamber. The gasflow source provides a source gasflow at a greater, second temperature to the mixing chamber. The mixing chamber provides the mixing chamber outflow at a third temperature by selectively allowing the ram airflow and the source gasflow in the mixing chamber to mix therein, or, by selectively allowing the ram airflow in the mixing chamber to flow to the main chamber (in absence of source gasflow). A controller is operative to provide a desired level for the third temperature.

Abstract: An apparatus, method for making, and product by process for a parachute, the parachute having a conductive network and a set of fabrics; the conductive network including a set of conductive elements and a set of devices; wherein a first subset of conductive elements of the set of conductive elements is incorporated with a second subset of fabrics of the set of fabrics and third subset of devices of the set of devices incorporated is incorporated with a fourth subset of fabrics of the set of fabrics.

Abstract: Systems and methods for delivering packages via aerial vehicles are disclosed. The system can comprise a label that includes a parachute to enable the packages to be dropped from the aerial vehicle, yet land at the package's destination without damage. The system can include a self-adhesive backing, a plurality of parachute cords, a parachute, and a breakaway cover. The parachute cords can include a shock absorber to reduce the shock on the package of the parachute opening. The parachute and/or the breakaway cover can include graphics to provide address, velocity, or spin information for the package. The parachute cords can include a harness to separate the cords and reduce tangling of the cords and spinning of the parachute canopy with respect to the package.

Abstract: An aircrew member must be properly positioned during flight to have a view inside and outside of the cockpit and to reach all aircraft controls. However, if an ejection event occurs, the aircrew member should be properly aligned with a thrust direction of the ejection seat to prevent injury. A retracting backrest for an ejection seat is deployed pre-flight to a desired flight position. A release mechanism engages a positioning member to secure the retracting backrest in the flight position. In response to an eject signal, the release mechanism disengages from the positioning member, and both the aircrew member and the retracting backrest are hauled back to properly align the aircrew member for ejection.

Abstract: An aircraft is provided and includes a fixed frame including a ledge and a seat pan on which seating elements for seating an aircraft crewperson are disposable. The seat pan includes a hinge about which the seat pan is pivotable relative to the fixed frame and a flange disposable on the ledge to establish a first pivot position for the seat pan relative to the fixed frame and a seat pan lifter coupled to the fixed frame and selectively interposable between the flange and the ledge to establish a second pivot position for the seat pan relative to the fixed frame.

Abstract: An inflatable evacuation device for an aircraft may include at least one chamber and at least one canopy support in fluid communication with the at least one chamber. A retention device may be configured to restrict inflation of the at least one canopy support during inflation of the at least one chamber.

Abstract: An electrical network for an aircraft. The aircraft includes at least one variable pitch propulsor. The electrical network includes a wound field synchronous AC electrical generator having a wound rotor driven by an internal combustion engine. The network further includes a voltage regulator configured to regulate output voltage of the electrical generator by regulating rotor winding magnetic field strength, and a synchronous AC drive motor coupled to a respective variable pitch propulsor and provided with power from the output of the electrical generator.

Abstract: The disclosure herein relates to power leveling mechanisms comprising a high frequency controller. The power leveling mechanism receives a power demand signal indicating a power requirement of a vehicle and determines a high frequency component of the power demand signal. The power leveling mechanism also provides a signal to a primary propulsion system and provides, via the high frequency controller, a high bandwidth signal based on the high frequency component to an auxiliary propulsion system.

Abstract: A gas turbine engine nacelle comprising an intake liner. The liner includes a plurality of cells. Each cell includes an open radially inner end in fluid communication with an interior side of the nacelle, and an open radially outer end in fluid communication with an exterior side of the nacelle. Each open end of each cell defines a respective cross sectional area. The intake liner further comprises radially inner and outer facing sheets overlying a respective radially inner and outer open ends of the respective cell. Each facing sheet defines at least one aperture overlying at least one cell, an overlying portion of the respective aperture having a smaller cross sectional area than the respective open end of the respective cell.

Abstract: A keyboard module configured for use in an avionics touchscreen system is disclosed. The keyboard module is configured to display, via a visual display in the avionics touchscreen system and responsive to a selection of an application program generated widget for focus via a touchscreen surface in the avionics touchscreen system, a virtual keyboard. The virtual keyboard includes a text box widget configured to display clip data stored in clipboard memory provided by the avionics touchscreen system, a copy widget configured to cause data in a first widget provided by the application program that is in focus to be copied to the clipboard memory, and a paste widget configured to cause the clip data in the clipboard memory and displayed in the text box widget to be pasted to a second widget provided by the application program that is in focus.

Abstract: A containment system for containing all or part of a radome and an external subassembly that is protected by the radome is disclosed. One embodiment of the containment system comprises a fabric material and an attachment system for attaching the fabric material to the radome and to the radome attachment ring. An increased strength radome for covering the external subassembly is also disclosed.

Abstract: An apparatus comprises a time-of-flight ranging sensor that scans in two or more directions relative to the apparatus over a series of scanning cycles. A processor computes, and to communicates to the time-of-flight ranging sensor, a pulse repetition rate (PRR) for the time-of-flight ranging sensor for each of the two or more directions based on information about surrounding terrain of the apparatus and a sensor pointing schedule for the time-of-flight ranging sensor that indicates directions that the time-of-flight ranging sensor is scheduled to point at time during the scanning cycles. In addition or lieu of computing the PRR, the processor(s) matches returns from pulses of the time-of-flight ranging sensor to the pulses probabilistically based on a current map of the vehicle's surroundings and scan coherence analysis for shapes in the returns. The current map can then be updated based on the matched returns for the next iteration.

Abstract: Disclosed is a glide path indicator (2) comprising a light emitter (20) configured to emit a visible light signal that defines a glide path (14) for use by a pilot of an approaching aircraft (10), and a camera (22) configured to capture images of the approaching aircraft (10), the camera (22) being arranged such that at least part of the glide path (14) defined by the light emitter (20) is located within a field of view of the camera (22). The glide path indicator (2) may be mounted to a vehicle (4), for example, an aircraft carrier. The glide path indicator (2) may further comprise a stabilization module (26) configured to stabilize the light emitter (20) and the camera (22) so as to reduce or eliminate the effects of the vehicle's motion on the glide path (14) and the field of view of the camera (22).

Abstract: A coupling module forms an interface between a cabin of a passenger bridge and an aircraft. The coupling module has a projecting roof and a floor arrangement overspanned by the projecting roof. The floor arrangement is pivotable about a horizontal pivot axis relative to the cabin. At least the floor arrangement and the projecting roof have a common pivot axis that is arranged in or beneath the floor arrangement, with the floor arrangement at least indirectly and substantially supporting the projecting roof.

Abstract: An actuator mounting method for mounting at least one actuator involves providing a skin structure and at least one actuator, and fixing the at least one actuator to the inner surface of the skin structure.

Abstract: A machining device may include an electric motor, a blade rotatably driven by the electric motor for machining a workpiece, and a blade cover configured to surround the blade. A resonance sound reduction device may be disposed at the blade cover and may reduce air vibration generated by the rotation of the blade.

Abstract: In one embodiment, a controller instructs an unmanned aerial vehicle (UAV) docked to a landing perch to perform a pre-flight test operation of a pre-flight test routine. The controller receives sensor data associated with the pre-flight test operation from one or more force sensors of the landing perch, in response to the UAV performing the pre-flight test operation. The controller determines whether the sensor data associated with the pre-flight test operation is within an acceptable range. The controller causes the UAV to launch from the landing perch based in part on a determination that UAV has passed the pre-flight test routine.

Abstract: A telescopic boom and reflector assembly for a spacecraft that includes a telescopic boom having a plurality of boom sections that are nested together within a prime batten or where the prime batten is attached to an outermost section of the boom when the boom is in a stowed position, where an innermost and smallest diameter section of the boom is secured to the spacecraft to facilitate testing and integration of the boom and reflector as a unitized assembly. The assembly also includes a reflector having a truss structure configured to allow the reflector to be collapsed into a stowed configuration, where the reflector is mounted to the prime batten. The assembly is configured to be deployed from the spacecraft by releasing the boom in a telescopic manner where the boom sections increase in diameter from the spacecraft outward when the boom is deployed.

Abstract: A Hall effect thruster arranged inside a wall and including a magnetic circuit and an electric circuit including an anode, a first cathode, and a voltage source. The magnetic circuit and the electric circuit are arranged in such a manner as to generate magnetic and electric fields around the wall. In every meridian section, the magnetic circuit presents an upstream magnetic pole and a downstream magnetic pole arranged at the surface of the wall and spaced apart from each other; and the anode and the first cathode are situated on either side of the upstream magnetic pole.

Abstract: An ammunition packing apparatus comprises an ammunition feeder receiving ammunition cartons and horizontally arranging the ammunition cartons in a left or right direction, an ammunition vertical conveyor vertically conveying the ammunition cartons to an ammunition horizontal conveyor, the ammunition horizontal conveyor advancing the ammunition cartons to an ammunition inserter, an ammunition pouch mounter placing and fastening empty ammunition pouches in a flat and stretched position, an ammunition pouch opener opening mouths of the ammunition pouches, and the ammunition inserter advancing and inserting the ammunition cartons into the ammunition pouches, wherein the ammunition inserter includes spade-shaped inserting blades surrounding left and right surfaces and bottom surfaces of the ammunition cartons to allow the ammunition cartons to be inserted without being stuck to rims of the ammunition pouches and ammunition return preventers preventing the ammunition cartons from moving back when the ammunition ins

Abstract: Apparatus and method for induction sealing workpieces, in which a series of workpieces are conveyed along a path extending in a conveyance direction, and each workpiece is exposed to a first electromagnetic field generated by a first induction head and to a second electromagnetic field generated by a second induction head, each of the first and second electromagnetic fields inducing eddy currents through the entirety of each workpiece. Respective magnetic axes of the first and second induction heads are non-parallel to each other such that each workpiece is exposed to a plurality of differently oriented electromagnetic fields as the workpiece is conveyed along the path.

Abstract: A packaging machine (1) for forming packets (3) of smoking articles (2), in particular cigarettes, comprises movement means for moving groups of smoking articles at least partially wrapped by an inner wrapping sheet (4), along a movement direction, a wrapping wheel (13) to receive the groups of smoking articles wrapped by the inner wrapping sheet (4) and to move them along a substantially circular wrapping path (P), and transfer means (22) to transfer the groups of smoking articles wrapped by the inner wrapping sheet (4) from the movement means to the wrapping wheel. The transfer means (22) transfer the groups of smoking articles wrapped by the inner wrapping sheet (4) along a transfer direction (T) radial with respect to the wrapping path (P), in order to reduce the bulk of the packaging machine (1).

Abstract: A method of expanding a structural support volume of a flexible container can include dispensing a cryogenic fluid into at least one structural support volume and sealing the at least one structural support volume such that it has a closed volume prior to complete conversion of the cryogenic fluid into a gas and expansion of the structural support volume to a pressurized state. The flexible container includes a product volume and at least a portion of the structural support volume extends into the product volume when the structural support volume is expanded.

Abstract: The Adjustable Chute is a user friendly product for consumers to dispose of lawn debris and or grass clippings collected from a grass catcher from a lawn mower. The Adjustable Chute is constructed of durable materials for longevity and reliability purposes. The unique design of the Adjustable Chute with the upper portion rectangular for easy attachment of the grass catchers itself, and lower portion tapered for easy disposal of yard waste or grass clippings, allows hands free transfer of yard waste from a grass catcher through the Adjustable Chute into the waiting collection brown bag. The Adjustable was conceived through personal necessity after realizing how incredibly difficult it is to transfer grass clippings after being collected in a grass catcher from the grass catcher into the brown recycle bag.

Abstract: The present invention relates to a container sleeving method for arranging sleeves around a plurality of containers, the method includes: transporting an array of containers past a sleeve discharge unit; arranging a sleeve of heat shrinkable foil around a container passing by the sleeve discharge unit by shooting the sleeve from the sleeve discharge unit towards the container; detecting whether the sleeve has been correctly arranged around the container; and, if the sleeve has not been arranged correctly around the container, continue transporting one or more containers along the sleeve discharge unit and discontinue shooting one or more sleeves towards the containers.

Abstract: The invention relates to container sleeving system and method. Sleeves of heat shrinkable foil are arranged around the container. The sleeves are supplied by ejecting the sleeve from the sleeve supply. Containers are supplied form a container supply. The sleeve supply arranges the sleeve around the container by moving the sleeve upwardly around the container. A heat shrink oven is arranged for fixing the sleeve to the container. A conveyor transports containers.

Abstract: A packet according to some embodiments of the disclosure is provided for holding a goods package. The packet includes first and second panels which are secured together to form an open-ended pocket. The first panel has an aperture therethrough which is partially overlapped by the second panel. The goods package seats within the open-ended pocket with a protrusion of the goods package extending through the aperture. The engagement of the protrusion though the aperture locks the goods package to the packet.

Abstract: Some embodiments include a package assembly comprising a case formed of a single sheet of packaging material. The single sheet includes three rows of panels. The three rows include first and second edge rows and a middle row disposed between the first and second edge rows. The panels are foldable at fold lines to form the case. A first side of the case includes a first end panel of the middle row extending fully between a top and a bottom and a front and rear of the case and an opposing end panel of the middle row extends over the first end panel. A second side of the case opposite the first side and a front and rear of the case include tear lines configured to separate the case into a cover portion and a tray portion. The first end panel is included with the cover portion.