Abstract: A method is provided for controlling a boat. The boat is adapted to float in a body of water. The boat includes a hull having a longitudinal extension along a hull longitudinal axis, a lateral extension along a hull lateral axis and a vertical extension along a hull vertical axis. The boat also includes a set of drive units, the set of drive units comprising at least one drive unit. Each drive unit in the set is arranged such that it, during driving of the boat, is adapted to be at least partially submerged into the body of water; adapted to be pivotable, relative to the hull, around a drive unit longitudinal axis that is substantially parallel to the hull longitudinal axis such that a drive unit roll angle can be varied, and adapted to be pivotable, relative to the hull, around a steering axis that forms an angle with the drive unit longitudinal, axis such that a drive unit steering angle can be varied.

Abstract: Provided is a ventilating apparatus for a drill ship, which allows a drill ship sailing around an arctic region to maintain appropriate temperature and pressure. The ventilating apparatus for the drill ship includes: a derrick forming an enclosed space blocked from the exterior; a moonpool formed under the derrick; an air supply device supplying outside air to the moonpool or the derrick; and an air exhaust device exhausting the supplied outside air out of the top of the derrick.

Abstract: A drainage end cap device for draining fluid from a hollow space in a vehicle, comprising a mounting unit that is durably mountable in a super-imposed manner onto a drainage opening provided in an outer shell of a vehicle, wherein a drainage cap with a drainage channel is provided, the drainage cap being removably mountable to the mounting unit and the drainage channel being at least partly zigzagged over a longitudinal extension of the drainage cap.

Abstract: An aircraft comprising an opening for accessing a compartment and a ladder. The aircraft comprises at least one support. The ladder comprises at least one fastener element connected to a support by a removable connection comprising a pivot axis.

Abstract: A structure having a panel, a stringer, and a rib is disclosed. The stringer includes a stringer flange that is joined to the panel and a stringer web that extends away from the stringer flange. The rib includes a rib web that has first and second faces and a rib foot that has a first rib foot flange that is joined to the stringer web, a second rib foot flange that is joined to the panel and a rib foot web that is joined to the first face of the rib web. The first rib foot flange is connected to the rib foot web by a first corner that includes at least one layer which runs continuously from the first rib foot flange into the rib foot web via the first corner. The second rib foot flange is connected to the rib foot web by a second corner that includes at least one layer which runs continuously from the second rib foot flange into the rib foot web via the second corner.

Abstract: A modular structural assembly to form part of an aircraft wing that has an outer skin and a plurality of stringers is disclosed. The assembly includes a plurality of panels, each panel having a portion that forms part of the outer skin and at least one stringer integrally formed with said portion.

Abstract: A stiffener 100 comprises a first stiffener portion (102), having a first cross-sectional profile (104) that is constant along the first stiffener portion (102). The stiffener 100 also comprises a second stiffener portion (106), having a second cross-sectional profile (108) that is constant along the second stiffener portion (106). The second cross-sectional profile (108) of the second stiffener portion (106) is different from the first cross-sectional profile (104) of the first stiffener portion (102). The stiffener 100 additionally comprises a transition stiffener portion (110) tapering from the second stiffener portion (106) to the first stiffener portion (102).

Abstract: The invention provides an aerodynamic device configured for being mounted to an aerodynamic structure of an aircraft, the aerodynamic device having a spanwise length, a chordwise width, a leading edge section along a leading edge of the device, for being mounted to the aerodynamic structure of the aircraft, and a trailing edge section along a trailing edge of the device, for providing a required aerodynamic profile, wherein a first chordwise extending segment of the trailing edge section is moveable in a spanwise direction with respect to the leading edge section or with respect to a second chordwise extending segment of the trailing edge section.

Abstract: A computer-implemented method for protecting a vehicle from a directed energy attack is provided. The method includes receiving, at the vehicle, a beam of directed energy, determining a threat level of the beam of directed energy, and causing the vehicle to automatically execute at least one evasive maneuver when the threat level of the beam of directed energy is greater than a predetermined threshold.

Abstract: An airflow diverter system for an aircraft may include an external aircraft surface upstream from an engine inlet and a passage having an upstream opening adjacent the engine inlet. The passage may be configured to channel boundary airflow from the external aircraft surface away from the engine inlet. The diverter system may include an occlusion device configured to selectively open and close the opening to the passage.

Abstract: An aircraft landing gear assembly includes a fibre composite leaf spring arranged as a down lock spring to make the lock link.

Abstract: An undercarriage having a wheel mounted on an axle (3), a brake and a drive assembly. The brake comprises a torsion tube (9), friction members (11) mounted around the torsion tube, and at least one brake actuator (13) for selectively exerting a braking force on the friction members. The drive assembly is operative to drive rotation of the wheel and comprises an electric motor (14) that is connected to a rim (5) of the wheel (4) by a coupler member (15). The coupler member extends at least in part around the axle (3) between the axle and the torsion tube (9) of the brake.

Abstract: An antivibration suspension system of an aircraft, the antivibration suspension system comprising a lever and an oscillating mass. The antivibration suspension system comprises a mechanical motion amplifier device interposed between the lever and the oscillating mass, the motion amplifier device being provided both with a mechanical inlet constrained to move in rotation with the lever about a control axis and with a mechanical outlet driving rotary movement of the oscillating mass.

Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. By moving the rotor units, the aircraft can transition from a hover mode to a transition mode and then to a forward flight mode and back.

Abstract: The subject matter of the invention is a remote-controllable, disk-shaped aircraft platform, comprising a platform housing and at least one transport housing, the platform housing having a plurality of motor-driven, horizontally aligned rotors, each rotor being connected via a support arm to a support structure holding the support arms of the rotors, the support structure being centrally arranged in the platform housing, the support structure accommodating at least one transport housing in a vibrationally isolated manner.

Abstract: Certain embodiments herein relate to location verification for autonomous unmanned aerial vehicles (also referred to as “drones”). In some embodiments, an unmanned aerial vehicle engaged in autonomous flight may determine its location using a satellite-based navigation system. The location may be evaluated against location data obtained from one or more secondary factors, such as public broadcast beacons, cellular towers, wireless network identifiers, visual markers, or any combination thereof. If the location is determined to be invalid, the unmanned aerial vehicle may be instructed to take a mitigation action. Additionally, certain embodiments also include the verification of a flight plan for the unmanned aerial vehicle using secure no-fly logic to verify a flight plan does not violate no-fly zones. If the flight plan is verified, the flight plan may be signed using a cryptographic signature and provided to a navigation module that verifies the signature and executes the flight plan.

Abstract: A preferred embodiment of a method and apparatus for detection and disablement of an unidentified aerial vehicle (UAV) includes arrays of antenna elements receiving in two modalities (for instance radio frequency (RF) and acoustic modalities, or RF and optical modalities). Signal processing of outputs from multiple antenna arrays locates a potential UAV at specific coordinates within a volume of space under surveillance, and automatically aims video surveillance and a short-range projectile launcher at the UAV, and may automatically fire the projectile launcher to down the UAV.

Abstract: A toilet module for a vehicle is provided. The toilet module comprises a housing having a front wall, a first functional wall and at least one second functional wall, which enclose a floor surface on the underside of the housing, and a toilet unit. The front wall comprises an access opening. The first functional wall is arranged opposite the front wall and accommodates the toilet unit. The at least one second functional wall extends between the first functional wall and the front wall and is perpendicular to the front wall. The toilet unit has a longitudinal extension axis which forms an angle which is greater than 0° with the at least one second functional wall. In this way, a particularly narrow and compact toilet module can be provided.

Abstract: An optimized, multi-configuration cabin and lavatory arrangement for a single aisle aircraft that adds either another row of seating or increases cabin space without sacrificing performance or function of the existing components. The invention includes a space efficient lavatory that may incorporate various design configurations to meet the needs of airlines seeking to generate additional revenue. The configuration of the present invention uses a reduction in the lavatory floor plan with the option for a modular flex wall area to provide a customizable combination that gains extra cabin space for carriers that can be utilized for additional revenue streams.

Abstract: An upholstered panel assembly includes an upholstery component having a foam layer provided on a substrate layer. The upholstery component covers the face of a base structure and is retained releasably by clips. The clips extend along the edges of the panel assembly. The panel assembly may be particularly suitable for aircraft cabins.

Abstract: A cabin air compressor assembly that include a cabin air compressor disposed at a compressor inlet and a cabin air compressor motor operably connected to the cabin air compressor. At least one cooling flow inlet is configured to direct a cooling flow through various pathways in the cabin air compressor assembly, including across the cabin air compressor motor. A blower is configured to boost the cooling flow across the cabin air compressor motor, thereby increasing cooling flow provided to the air compressor motor. A static seal plate is downstream of the blower and guides the boosted cooling flow toward a cooling flow exit. In addition, the static seal plate isolates boosted cooling flow from a moving rotor of the cabin air compressor, and also forms part of a containment structure that contains fragments and breakage that may come from the cabin air compressor rotor.

Abstract: A tap off for use in a mixer comprises a pair of cylindrical portions, with a first cylindrical portion extending in a direction that will be inward toward a mixer when the tap off is mounted on a mixer. The first cylindrical portion defines a first port inlet and communicates into a second cylindrical portion. The second cylindrical portion defines a second inlet port and an outlet port for combining air from both the first inlet and the second inlet port. The first and second cylindrical portions are fixed together. A pair of diverter plates have a face for deflecting air from the second inlet port in the inward direction, and further have a leg extending from the face into the first cylindrical portion. Tabs on the face and legs of both diverter plates extend into slots in the second cylindrical portion. The tabs extends into slots in the first cylindrical portion. A mixer, and an ECS pack are also disclosed.

Abstract: An aircraft system includes a fan, a differential pressure sensor, a temperature sensor, and a system controller. The fan provides airflow for at least one heat exchanger. The differential pressure sensor senses a pressure difference between an inlet of the fan and a diffuser exit of the fan. The temperature sensor senses a temperature at the inlet of the fan. The system controller is configured to receive the sensed pressure difference, the sensed temperature, and a speed of the fan, and determines an operating point of the fan based upon the sensed pressure difference, the speed of the fan, and the sensed temperature. The operating point is indicative of contamination of the at least one heat exchanger.

Abstract: An aircraft galley chiller is disclosed characterized by a cassette that inserts into the galley compartment above the beverage cart and houses an air return duct, a heat exchanger, a fan, and an air supply outlet. The chiller further includes a control valve for controlling the amount of air passing through the heat exchanger, and an electronic control box for control over the chiller, where the cassette is disposed between the beverage cart and a galley work deck.

Abstract: In order to decrease the overall mass of an assembly for an aircraft, including an engine attachment pylon and an engine attachment, the pylon according to the disclosure herein has a primary structure forming a box section equipped with internal transverse stiffening ribs, one of which is produced in one piece with at least a part of the body of the engine attachment.

Abstract: A high-speed propulsion system for a high-speed vehicle includes an air intake duct, a compression section, a combustion section, and an expansion section. A gas dynamic laser generator is disposed proximate the expansion section and generates a source of laser light. A laser transmission mechanism receives the laser light and transmits the laser light from the gas dynamic laser generator to the combustion section and to presents the laser light into the air/fuel mixture of the flowpath which promotes mixing, combustion, and flame stability.

Abstract: A human machine interface linked to the throttle lever of an aircraft used to control the energy of an aircraft is disclosed. The HMI has upper part, which corresponds to the forward stroke of the lever, and a lower part, which corresponds to the rearward stroke of the lever. An upper shutter is positioned over the upper part, and a lower shutter is positioned over the lower part. A “cursor” acts as a visual representation in the HMI of the lever and its handle. The cursor moves forward or backward as the pilot acts on the lever/handle. The cursor indicates an ordered release of more or less aircraft energy, depending on its position on the display. The upper and lower shutters also indicate the ordered release of more or less aircraft energy, depending on the respective lengths of the two shutters.

Abstract: A method of determining the longitudinal air speed VairX and the longitudinal ground speed VsolX of a rotary wing aircraft depending on the exposure of the aircraft to the wind, the aircraft flying at a speed of advance Va. The method making it possible to determine characteristic speed curves for the aircraft depending on the longitudinal speed of the relative wind to which the aircraft is subjected, and then during a flight and depending on the actions of the pilot of the aircraft, to deduce the longitudinal ground speed VsolX and the longitudinal air speed VairX to be applied to the aircraft depending on variations in the longitudinal speed of the relative wind to which the aircraft is subjected.

Abstract: A computer-implemented method for providing a real-time global view of airline operations situational awareness is provided. The method is implemented using a situational awareness server system in communication with client systems and data sources. The method includes gathering a plurality of situational awareness data from a plurality of data sources including real-time data, updating the situational awareness data based on one or more business rules, augmenting the updated situational awareness data based on historical data, and determining whether to generate one or more alerts based on the augmented situational awareness data.

Abstract: As a component of an aerial vehicle, a power management system having an active power control device is provided. The system includes a solar cell converting solar energy into electric energy; a fuel cell provided in the aerial vehicle and converting fuel energy into electric energy by electrochemical reaction; a battery compensating for a lack of electric power supplied from the solar cell and the fuel cell to the aerial vehicle and storing surplus electric power; and an active power control device connecting with all the solar cell, the fuel cell and the battery and combining and distributing electric power generated in the solar cell, the fuel cell and the battery to loads. The system efficiently distributes the power from the respective power sources through the controllable output of the fuel cell in accordance with power required by the aerial vehicle and the solar cell's performance depending on weather.

Abstract: A retrieval device for an unmanned aircraft. The retrieval device may include a frame that supports a flexible material. The flexible material may form a receptacle portion shaped to receive the unmanned aircraft. The flexible material may absorb at least a portion of the energy exerted by the aircraft landing within the receptacle portion. Wheels may be connected to the frame to further control and absorb energy from the landing.

Abstract: The present invention extends to methods, systems, devices, apparatus, and computer program products for aligning a target with and/or over and/or into a specific position and orientation. Embodiments include one or more capture components, such as, engagement lines, spars, or struts, that can be actuated together or independently to position a vehicle in a capture area defined by a ring or other geometry. A vehicle can include a sloped surface feature configured to engage with the capture components. When actuated, the capture components draw the sloped surface feature towards and down into the center of the defined capture area. Variations allow a vehicle to be rotated in place, repositioned in place, or clamped securely in place. Positioning and rotation allows alignment with replenishment devices for resupplying and refueling. In this way, a vehicle is relieved from having to have precision terminal guidance for landing and recharging.

Abstract: A technique is directed to launching an unmanned aerial vehicle (UAV). The technique involves positioning a UAV launcher over a ground location. The technique further involves installing, after the UAV launcher is positioned over the ground location and prior to launching the UAV, an anchor into the ground location to anchor the UAV launcher to the ground location. The technique further involves operating, after the UAV launcher is anchored to the ground location, the UAV launcher to impart launching force onto the UAV to launch the UAV, the anchor holding the UAV launcher substantially in place at the ground location to minimize energy loss as the UAV launcher imparts launching force onto the UAV. In some arrangements, the UAV launcher is capable of pivoting while remaining anchored between launches to accommodate changes in wind direction while maintaining substantial connection to the ground location for enhanced consistency and performance.

Abstract: The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

Abstract: Thermal control louvers for CubeSats or small spacecraft may include a plurality of springs attached to a back panel of the thermal control louvers. The thermal control louvers may also include a front panel, which includes at least two end panels interlocked with one or more middle panels. The front panel may secure the springs, shafts, and flaps to the back panel.

Abstract: A packaging and filling device, a paper container, and a blank is disclosed. The blank comprises a sixth panel in a readily foldable state prior to a step for forming a bottom part, and provides sufficient length in a folded portion to protect the end surface of a packaging material. The blank for the paper container is formed by the packaging and filling device and comprises a top part, a bottom part, and a cylindrical body having four side walls and a square cross-section. The packaging and filling device comprises a loading unit for retrieving the blank and loading a cylindrical blank, a bottom-part-molding unit for molding the bottom part of the cylindrical blank to obtain a container, a filling unit for filling the container with liquid food from an upper opening, and an upper-part-sealing unit for heat-sealing the upper opening.

Abstract: A boxing apparatus erects packages that can be erected along a limited section of a conveyor, without having to erect them all at once, even with individual packages that are long in the feed direction. The boxing apparatus has a fourth conveyor belt that blocks the front of a line of incoming packages and exerts an upward force on the front package. The front package is raised up by this upward force, so the following package rides up onto the package in front, and the packages are erected successively. Consequently, even individual packages that are long in the feed direction can be erected at a limited section of a third conveyor belt.

Abstract: A machine is described for covering book covers and sealing envelopes or articles of various kind. The machine comprises a fixed lower base suitable for resting a sheet of flexible plastic material for an article to be covered, an upper part movable towards said base and a heatable blade accommodated in the upper part to execute soldering of the overlapped ends of the plastic material sheet along the article edges when the upper part is approached to the lower base. The machine comprises an electric motor, a control member accessible from the outside of the machine for operating the electric motor and movement transmission means acting on the sides of the upper part to induce, at every activation of the electric motor, movement of the upper part towards the lower base for executing the soldering of the ends of the plastic material sheet.

Abstract: A processing method for automatically opening a slide-open package of tobacco articles with a hinged lid; the processing method including the steps of: mechanically clamping an outer container of the package; exerting pull on the lid to rotate the lid into an open position by means of a first actuator, which contacts a top wall of the lid, and has a suction head which engages the top wall by suction; and, simultaneously and in coordination with the step of exerting pull on the lid, exerting thrust on an inner container of the package, to slide the inner container axially with respect to the outer container, by means of a second actuator, which contacts a wall of the inner container through a window formed through a corresponding wall of the outer container.

Abstract: A method for sealing a food storage bag includes providing a bag with walls formed of two facing sheets, at least one of the facing sheets is a multilayer sheet having an inner layer of polymer enabling the facing sheets to be joined by melt sea ng at less than 95° C.; providing a sealing device comprising an elongated bar with thermal conductivity greater than 5 W/(m K) and an insulating component affixed to the bar having a thermal conductivity less than 1 W/(m K); placing the sealing device into water; warming the bar to between 50° C. and 100° C.; removing the warmed bar from water; handling the sealing device by the insulating component; and pressing the warmed bar against a wall of the storage bag to join facing sheets. In one embodiment, a machine-readable image on the bag points to a video on the Internet that illustrates the sealing process.

Abstract: The sonotrode and anvil of copending application Ser. No. 12/925,652, for advanced ultrasonic welding of work pieces, are readily incorporated into new form-fill-seal machines, but existing machines with heat-seal stations pose difficult problems for swapping of the sealing packages. Kits enabling heat station replacement, with the further improved sonotrode and anvil disclosed herein, comprise: a housing; a linear rail fixed thereto; anvil and sonotrode support members; and a parallel gripper. Each of the anvil and sonotrode support members is slidably attached to the rail(s) and are also connected to a respective piston of the gripper, permitting actuation of each through cycling of the gripper pistons.

Abstract: Disclosed is a method for processing cut edges of a blank member, so called “package sleeve”, made from packaging material, in particular paper/plastics composite material, the cut edges of which are open from above and/or below, by applying a processing medium. In order to develop a simple and cost-effective method, in which the risk of contamination of the packaging and the aseptic region of a filling installation when the package sleeves are filled and closed is reduced, the processing medium contains at least one sterilizing medium and the sterilizing medium remains after being applied to the cut edges and is introduced into the packaging material.

Abstract: A carousel for processing containers includes a base structure that can rotate about the rotation axis of the carousel and supports a plurality of supporting elements. A detection device is provided having at least one sensor that can move about the rotation axis of the carousel. The carousel further includes a plurality of kinematic connection elements arranged between the base structure and the sensor or sensors, which are adapted to couple integrally in rotation the sensor or sensors and the base structure during the movement of the sensor or sensors. The kinematic connection elements are associated with motor elements adapted to return on command the sensor or sensors from a final angular position to the initial angular position by way of an angular movement of the sensor or sensors in the opposite direction with respect to the rotation of the base structure.

Abstract: An apparatus for the application of hotmelt onto labels, includes a vacuum cylinder, a gluing unit with a glue roller unit, and a glue reservoir. The gluing unit is pivotally mounted such that it can be slewed away from the vacuum cylinder and the glue reservoir is designed as a self-contained unit that is structurally separate from the pivotable gluing unit. A glue reservoir for hotmelt includes an inner body with heating fins, a thermally insulating jacket enclosing the inner body, and an outer casing made of plastic.

Abstract: A blow molded container including (A) a layer containing an ethylene-vinyl alcohol copolymer as a principal component, in which the layer (A) contains an unsaturated aldehyde, and the content of the unsaturated aldehyde in the layer (A) is 0.01 ppm or more and 100 ppm or less. The unsaturated aldehyde (II) is preferably an unsaturated aliphatic aldehyde. The unsaturated aldehyde (II) is preferably at least one selected from the group consisting of crotonaldehyde, 2,4-hexadienal and 2,4,6-octatrienal. The layer (A) preferably contains a conjugated polyene compound, and the content of the conjugated polyene compound in the layer (A) is preferably 0.01 ppm or more and 1,000 ppm or less.

Abstract: A plastic container that is adapted for adjustment to internal volumetric changes such as those that occur during the hot-fill process includes a container body defining an internal space and having a sidewall. The container body has a maximum lateral dimension and a plurality of flexible panels and posts defined in the sidewall. The posts are respectively interposed between the flexible panels around the outer circumference of the sidewall. Each of the plurality of posts has a minimum width and a maximum width, and a ratio of the minimum width to maximum width is preferably within a range of about 0.3 to about 0.7. A ratio of the minimum width to the maximum lateral dimension is preferably within a range of about 0.05 to about 0.30. In addition, a ratio of the maximum width to the maximum lateral dimension is preferably within a range of about 0.15 to about 0.45.

Abstract: A supporting structure for concurrently supporting a plurality of containers having a predetermined length for medical, pharmaceutical or cosmetic applications comprises a carrier having a plurality of supporting means for supporting the containers on the carrier, optionally, at least in a first orientation (e.g. upright) or in a second orientation (upside-down or also upright). According to the invention the carrier is matched to the lengths of the containers such that the upper ends of the containers are arranged in the first position at the same distance to the carrier as the lower ends of the containers in the second position and that the upper ends and/or lower ends of the containers are accessible for a further processing of the containers while they are supported on the carrier.

Abstract: A package for a prolate spheroidal ball having a longitudinal axis. A back plate is disposed between a first end and a second end of the package. A first cradle extends from the back plate adjacent the first end, and is operative to receive a first portion of the prolate spheroidal ball along the longitudinal axis. A wing portion extends from the back plate adjacent the second end, and at least partially circumscribes the longitudinal axis of the prolate spheroidal ball. A flap portion extends from the wing portion and defines an end surface of the package. The longitudinal axis intersects the flap portion.

Abstract: Dual handle box designs, blanks for forming boxes by folding, collapsible and non-collapsible boxes formed thereby, and manufacturing methods therefor are disclosed. Preferably each handle is located on an opposite end of the box; is two-ply; defines an elongate hand opening for receiving fingers of a hand; defines an elongate tab opening for receiving a tab of a center handle, and that intersects the hand opening; and defines a recess for receiving and retaining a lid panel of the box. Furthermore, the boxes preferably have a waterproof or water-resistant coating applied and are used as ice coolers for beverages and food items.

Abstract: Embodiments of this disclosure include a rigid tray container and methods and equipment for using the rigid tray container in batched process operations. In one embodiment, a mass container is sized and dimensioned to receive one or several rigid tray containers. In other embodiments, equipment is configured to lid/unlid, secure, stack, load/unload, and buffer rigid tray containers. In other embodiments, equipment is configured to stack and stage mass containers. In some embodiments, methods are provided for batch processing items.