Abstract: The present disclosure discloses a diving mask, including a mask assembly and a breather assembly. The mask assembly is provided with an accommodating cavity and a first air outlet channel. The first air outlet channel is arranged along a circumferential direction of the accommodating cavity. A wall surface of the accommodating cavity is provided with a first air inlet and an air outlet. The first air outlet channel is communicated with the accommodating cavity through the air outlet. The breather assembly is provided with an air inlet channel and a second air outlet channel which are spaced from each other. The air outlet is communicated with the second air outlet channel. The air inlet channel is communicated with the first air inlet.

Abstract: A system for handling operations in a body of water has an unmanned floating vehicle configured to perform first activities from a surface of the body of water; at least one intervention/inspection device configured to perform second activities in/on the body of water; a first control module, configured to control the performance of the first activities according to first acquired data; a second control module, configured to control the performance of the second activities according to second acquired data; and a mission control unit in communication with the first and the second control module and configured to assign respective first activities to the first control module and respective second activities to the second control module according to a mission prediction model and to control the performance of the first and second activities assigned in combination.

Abstract: A propulsion system for a marine vessel is presented. The propulsion system comprising a propulsion unit that is rotatably attached to the marine vessel about an axis, a rotary drive arranged to rotate the propulsion unit about the axis by applying a torque about the axis, and a slip clutch assembly operationally arranged between the propulsion unit and the rotary drive to allow a rotational motion between the propulsion unit and the rotary drive about the axis in case the propulsion unit impacts an obstacle.

Abstract: A propulsion system for a marine vessel includes a drive unit, a transom bracket for attaching the drive unit to a transom of the marine vessel, and an actuator for moving the drive unit. The transom bracket comprises a wall structure that is arranged to shield the actuator from the water.

Abstract: A propulsion system for a marine vessel includes a drive unit and a transom bracket for movably attaching the drive unit to the marine vessel such that the drive unit may be moved between a lower position and a higher position. The drive unit is adapted to be connected to the swim platform such that at least a portion of the swim platform is manoeuvrable by the drive unit being moved between its lower and higher positions.

Abstract: A propulsion system for a marine vessel includes a transom bracket configured to be connected with a transom of the marine vessel, and a drive unit. The drive unit is arranged to be moved in relation to the transom bracket to move the drive unit in the water and out of the water. The drive unit is connected with the transom bracket via a connecting arm having a first pivot joint connected with the transom bracket and a second pivot joint connected with the drive unit. The drive unit is configured to be moved in the water and out of the water by the connecting arm pivots around the first pivot joint or the drive unit pivots around the second pivot joint or the connecting arm and the drive unit pivot around both pivot joints.

Abstract: A propulsion system for a marine vessel includes a transom bracket configured to be connected to a transom of the marine vessel, a drive unit being rotatably connected with the transom bracket so as to be pivotable by a tilt arrangement from a lowered position into a raised position, or vice versa, about a pivot joint, and a trim arrangement being arranged between the transom bracket and the drive unit to adjust a trim angle of the drive unit when in the lowered position. A trim arrangement lock is arranged to be connected with the trim arrangement for a range of trim angles of the drive unit in the lowered position so as to prevent pivoting of the drive unit by the tilt arrangement inside the range of trim angles, and the trim arrangement lock is configured to be disconnected from the trim arrangement outside the range of trim angles so as to allow pivoting of the drive unit by the tilt arrangement.

Abstract: A propulsion system for a marine vessel includes a transom bracket being configured to be connected with a transom of the marine vessel, a drive unit being rotatably connected with the transom bracket so as to be pivotable from a lowered position into a raised position, or vice versa, and a trim arrangement being arranged between the transom bracket and the drive unit to adjust a trim angle of the drive unit when in the lowered position, wherein a support face is arranged on the transom of the marine vessel or at the transom bracket, and the drive unit comprises a support member arranged opposite the support face in the lowered position whereby the support face is configured to support the support member.

Abstract: An outboard motor includes a drive source, a propeller, and a transmission to transmit a drive power of the drive source to the propeller. The transmission includes a propeller shaft, an input shaft, a first output shaft, and a first winding transmission. The propeller shaft extends in a first direction and is rotatable together with the propeller. The input shaft is connected to the drive source and is rotatable by the drive power of the drive source. The first output shaft is connected to the propeller shaft, is spaced apart from the input shaft, and transmits power to the propeller shaft. The first winding transmission transmits rotation of the input shaft to the first output shaft.

Abstract: An outboard motor includes a drive source, a propeller, a propeller shaft extending in a first direction and rotatable together with the propeller, and a transmission shifter to transmit a drive power of the drive source to the propeller shaft. The transmission shifter includes a first assembly including an input shaft rotatable by the drive power of the drive source, a second assembly positioned around a second virtual axis, a gear transmission to transmit power between the first assembly and the second assembly and including a first gear rotatable around the first virtual axis and a second gear to mesh with the first gear and rotatable around the second virtual axis, a winding transmission to transmit power between the first assembly and the second assembly, and a switch to turn on and off the transmission of power between the gear transmission and the winding transmission.

Abstract: An outboard motor support device includes a transom connection mechanism, a pivot joint, and a motor support. The transom connection mechanism engages directly with a transom bracket to maximize stability and is configured to provide a consistently correct angular orientation of the motor support relative to the motor during use. In particular, the pivot joint adjustably aligns to the motor is a desired orientation during assembly to ensure a firm and “nested” engagement with the lower unit of the motor in the motor support. The motor support can be designed to fit specific motors, allowing for maximum stability and maximum surface area contact when properly aligned and engaged with the motor. The present outboard motor support device is formed as a single unit that provides vertical support as well as horizontal stabilization to the motor during transit, thereby also preserving the transom brackets and tilt/trim mechanism of the motor.

Abstract: A watersport propulsion system for a marine watersport vessel includes a drive unit arranged rotatable from a rearward-facing position to a forward-facing position, and vice versa, a control unit being operatively connected with the drive unit. The control unit is configurable in a nominal mode of operation and in a watersport mode of operation. The control unit is configured to operate the drive unit in the forward-facing position when in the watersport mode of operation and in the rearward-facing position otherwise.

Abstract: A propulsion system for a marine vessel includes a transom bracket being configured to be connected with a transom of the marine vessel, and a drive unit. The drive unit is rotatably connected with the transom bracket via a first pivot joint, wherein a harness is guided from the transom bracket via the first pivot joint to the drive unit.

Abstract: A propulsion system for a marine vessel includes a drive unit, a transom bracket for attaching the drive unit to the marine vessel, a linear actuator for moving the drive unit. The linear actuator includes a drive end that is connected to the drive unit and a transom end. The propulsion system further includes a movable attachment for movably connecting the transom end of the linear actuator to the transom bracket.

Abstract: In one embodiment, a modular door panel assembly for an aircraft comprises a door surround that interfaces with a door aperture of the aircraft to ensure aircraft pressurization, a first hole in an upper portion of the door surround configured to accommodate a modular upper panel assembly such that a portion of the door surround around the first hole is capable of interfacing with the modular upper panel assembly to ensure aircraft pressurization, a second hole in a lower portion of the door surround configured to accommodate a modular lower panel assembly such that a portion of the door surround around the second hole is capable of interfacing with the modular lower panel assembly to ensure aircraft pressurization, and a strut actuator aperture below the second hole that is configured to interface with an articulated strut to ensure pressurization.

Abstract: An aircraft part with a door for accessing inside an aircraft and a fuselage part includes a cavity between an upstream edge of the door in the closed position and a downstream edge of the fuselage part, the cavity opening to the outside of the aircraft part and having a bottom connected to the upstream edge of the door and to the downstream edge of the fuselage part. The aircraft part includes a chamfer on the outer face of an outer plate of the door at the upstream edge of the door, as well as possibly other technical features such as a sharp ridge and/or an add-on component, allowing for reducing noise generated by the cavity.

Abstract: A removable tinted window panel system for an aircraft cockpit may include unique tinted panels and panel brackets which are easily installed and removed allowing full compliance with FAA regulations. The tinted panels, when installed, block 99.9% of UV radiation, reduce glare by up to 70%, reduce heat from solar energy up to 47% and thereby improve overall cockpit environment and pilot comfort. The panels allow the pilot to selectively block the sun when needed to remove glare and to remove the discomfort of being exposed to direct sunlight coming from the side windows. The panels reduce pilot fatigue, reduce eye strain and increase pilot performance and comfort and most of all improve flying safety.

Abstract: A fairing arrangement for a high-lift mechanism for an aircraft is disclosed including a flap to be arranged at a trailing edge of an aircraft wing, and a mounting and guiding mechanism for the flap. The fairing arrangement includes a flap side fairing unit and a wing side fairing unit. The flap side fairing unit includes a flap side fairing for covering an aft part of the mounting and guiding mechanism and a flap side fairing mount for mounting the flap side fairing to the flap. The wing side fairing unit includes a wing side fairing for covering a forward part of the mounting and guiding mechanism, and a wing side fairing mount for mounting the wing side fairing to the wing. The wing side fairing mount is configured for movably connecting the wing side fairing to the wing such that the wing side fairing is rotatable around an axis directed at least partially in a vertical direction.

Abstract: An aircraft system includes a support structure, an aerodynamic component, a first coupling unit and a second coupling unit. The first coupling unit includes a first coupling mechanism movably coupling the aerodynamic component to a first coupling point at the support structure, and a second coupling mechanism coupling the aerodynamic component to a second coupling point at the support structure. The first and second coupling points are spatially separated from each other, wherein the first coupling mechanism and the second coupling mechanism interact with each other to enable a rotational movement of the aerodynamic component with respect to the support structure such that, during the rotational movement of the aerodynamic component, a center of rotation of the aerodynamic component is translated from a neutral position to an adjusted position. The second coupling unit pivotably moves the aerodynamic component about a pivot axis at the support structure.

Abstract: An aerodynamic system for an aircraft. The aerodynamic system includes a first aerodynamic component configured to be movably coupled to a primary structure of the aircraft, a second aerodynamic component which is movably coupled to the first aerodynamic component and a first panel element coupled to the first aerodynamic component. The first panel element at least partially covers a gap between the first aerodynamic component and the second aerodynamic component. The aerodynamic system further includes a sealing element arranged between the first aerodynamic component and the second aerodynamic component. The sealing element is configured to at least partially block an airflow between the first aerodynamic component and the second aerodynamic component.

Abstract: The illustrative examples provide a slat movement system for use in an aircraft. An aircraft comprises a wing having a fixed edge and a wing front spar, and a moveable slat connected to the wing by a four bar linkage and a slat arm, the slat arm movable along a track comprising a slot terminating prior to the wing front spar.

Abstract: A landing gear system for an aircraft includes a drag brace, a lateral brace, and a support assembly, the support assembly coupled to: a lateral side of the fuselage via the lateral brace, an upper portion of the fuselage via a hinge, and a forward portion of the fuselage via the drag brace. The support assembly can rotate about the hinge connection about a forward-aft axis, with the lateral brace resisting rotation of the support assembly about the forward-aft axis, and the drag brace resisting rotation of the support assembly about a vertical axis. The system includes inboard and outboard landing gear separately coupled to the support assembly to support weight of the aircraft. The hinge transfers vertical forces to the fuselage, moments about the hinge are reacted by forces on the lateral brace, and drag forces are transferred to the fuselage by the drag brace.

Abstract: A landing gear assembly is provided. The landing gear assembly includes a shock strut. The shock strut includes a shock strut cylinder and a shock strut piston slidably disposed within the shock strut cylinder. The landing gear assembly further includes a temperature control unit assembly disposed within the shock strut cylinder. The temperature control unit assembly is configured to, responsive to a temperature within the shock strut cylinder falling below a predetermined temperature, heat gas within the shock strut cylinder.

Abstract: A drive system has a gearbox, comprising a passage therethrough, a coupling shaft disposed at least partially within the passage and a first coupling carried by a first end of the coupling shaft. The first coupling is configured to accommodate misalignment. The drive system also has a second coupling carried by a second end of the coupling shaft. The second coupling is also configured to accommodate misalignment.

Abstract: A spinner is described that can provide aerodynamic advantages for vertical takeoff and landing (VTOL) aircraft. The spinner can be shaped with multiple faces divided by chines. The chines can run down the edge of the spinner to fairings that can cover rotor blades and/or couplings between rotor blades and the rotor hubs of the aircraft. During forward flight the rotor blades can be folded down into recesses on the spinner. The spinner and fairings can provide aerodynamic advantages in addition to protection for sensitive components within the rotor and blades apparatus. This improves efficiency and allows the aircraft to fly faster.

Abstract: A method for driving a tilt rotor between vertical and horizontal using a variable displacement motor controlled in response to a swash angle of the motor measured in a feedback loop. The loop includes an algorithm configured to monitor change in swash angle as the motor speed reduces and the actual tilt position of the rotor pylon approaches the second position and, based on the change and actual tilt position, to limit change in swash angle to be within a predetermined range as a percentage of the operating load.

Abstract: A coaxial rotor system includes a plurality of upper rotor blades and a plurality of lower rotor blades disposed at a mast assembly. The upper rotor blades rotate about an axis of rotation in a first direction and the lower rotor blades rotate about the axis of rotation in a second direction opposite the first direction. A control system disposed at the mast assembly between the upper and lower rotor blades includes an upper swashplate connected to the upper rotor blades and a lower swashplate connected to the lower rotor blades. The control system adjusts the upper swashplate and the lower swashplate relative to the mast assembly to adjust respective pitches of the upper and lower rotor blades relative to the axis of rotation. The control system is operable to adjust the upper swashplate and the lower swashplate relative to the mast assembly independently of one another.

Abstract: An emergency oxygen system for an internal cabin of a vehicle includes a housing including one or more compartments. One or more oxygen assemblies include a mask and a fluid conduit. The mask is configured to be stowed within and deployed from the one or more compartments. A door is moveably secured to the housing. The door is configured to pivot in an outboard direction from a closed position to an open position during a deployment event. One or more pouches can be secured to an interior surface of the door. Coiled tubing of the fluid conduit is retained by the one or more pouches when the mask is stowed within the one or more compartments. An alert device can be operatively coupled to the one or more oxygen assemblies. The alert device is configured to emit a response indicating that oxygen is flowing to the mask.

Abstract: An aircraft seat may include an integrated controller feedback system. The controller feedback system may include a user interface device at least partially embedded within an armrest console of the aircraft seat. The user interface device may include a control panel, one or more buttons, one or more sensors, and/or a controller. The one or more buttons may indicate a controllable feature of the feedback system. The one or more sensors may be aligned with the one or more buttons and may be able to distinguishably detect a user touch from a user press. The controller may be in communication with the one or more sensors. The controller may generate one or more feedback signals in response to a user touch, and/or generate one or more activation signals in response to a user press.

Abstract: The present disclosure provides a seat layout for business class in an aircraft. The layout includes a first row of seats that are angled toward a centerline, and a second row positioned directly behind the first row of seats, the second row including seats that are laterally adjacent and parallel to the centerline. Each seat includes a console positioned to one side of the respective seat, wherein the consoles of the first row form footwells for the seats of the second row. The seats in the second row are grouped to form a sharable space for passengers traveling together. The disclosure further provides a seat layout for a widebody aircraft including a sharable space positioned at the aft end of the center column.

Abstract: A seating arrangement for a passenger-carrying vehicle including a first seat and a third seat arranged in a first row and facing in a forward direction, and a second seat located rearwardly of the first and third seats. The third seat is offset forwardly with respect to the first seat, the second seat is offset with respect to each of the first and third seats in a transverse direction that is perpendicular to the forward direction such that it is located between the first and third seats in the transverse direction. The combined effect of the transverse offset of the seats in adjacent rows, together with the forward offset of the seats in any given row provides seated passengers with a larger passenger accommodation region than is provided by conventional seating arrangements.

Abstract: A controller using image sensors and eye tracking software tracks the position of the eyes of the pilot. The controller causes an actuator of a pilot seat to automatically adjust the seat position to the Design Eye Point (DEP). The automatic adjustment of the seat position to the design eye point reduces the workload of the pilot and ensures accurate position of the eyes within the design eye point. The reduced workload may be particularly advantageous during an emergency event.

Abstract: An economy aircraft seat includes a telescopically extensible seat pan frame. Multiple telescoping sections extend forward with stops to prevent overextension. A forward edge of the extensible seat pan frame includes clips to affix the extensible seat pan frame to a neighboring passenger seat frame. The extensible seat pan frame includes supports that transversely span the extensible seat pan frame.

Abstract: A seat system for an aircraft including a pilot seat configured to operate in a piloting mode and in a rest mode. The pilot seat includes a dual function component configured to function as a flight controller when the pilot seat is operating in the piloting mode and a rest surface when the pilot seat is operating in the rest mode. The piloting mode and the rest mode are mutually exclusive operating modes. The seat system further includes a control system in electronic communication with the pilot seat and configured to activate the flight controller when the pilot seat is operating in the piloting mode, deactivate the flight controller when the pilot seat is operating in the rest mode. The pilots seats may be utilized in a two-pilot aircraft to provide provisions for pilot rest in an aircraft cockpit.

Abstract: An air processing system for an aircraft comprising a hydrogen fuel cell. The air processing system includes an input airflow; a first and a second compressor, wherein each compressor is configured to compress the airflow in a compression stage; a first and a second turbine, wherein each turbine is configured to decompress the airflow in a decompression stage; and a first and a second shaft each configured to independently rotate. Each shaft mechanically couples one of the compressors and one of the turbines, such that torque can be transferred between the compressor-turbine pair.

Abstract: A system including an apparatus for determining the presence of ice on an external surface of a structure is provided. The apparatus includes a sensor that includes first and second parallel ink or paint conductive traces separated by a gap. The apparatus also includes a circuit configured to measure the impedance or change in impedance between the first and second parallel ink or paint conductive traces.

Abstract: A hybrid electric propulsion (HEP) system of an aircraft includes a gas turbine engine configured to generate rotational power, and an electric propulsion system configured to generate at least one of thrust or lift for operation of the aircraft. The propulsion system includes a propulsor and an electric motor configured to drive the propulsor. A controller is in signal communication with the gas turbine engine and the electric propulsion system. The controller operates the gas turbine engine based on an on-board engine model (OEM), monitors electrical parameters of the electric propulsion system, and updates the OEM in response to changes to the electrical parameters.

Abstract: A power generation system for an aircraft includes: a storage tank for storing hydrogen; a fuel cell configured to generate power from the hydrogen; a fuel supply line configured to supply the hydrogen from storage tank to the fuel cell; a fresh air supply line configured to supply air to a cabin air supply system; and a fuel-air heat exchange system, wherein the fuel supply line and the air supply line pass through the fuel-air heat exchange system such that the hydrogen cools the air in use.

Abstract: An aircraft includes a chamber (1), a processor, a memory, and a compressor system (12b) in fluid communication with the chamber. The compressor system (12b) configured to selectively pressurize the chamber (1). The chamber supports a fuel cell (26), a motor, and/or electrical components that electrically communicate with the fuel cell (26) and the motor to power the aircraft. The memory includes instructions stored thereon, which when executed by the processor, cause the aircraft to receive an altitude value of the aircraft, and selectively pressurize the chamber using the compressor system based on the received altitude value to reduce corona discharge in the chamber.

Abstract: A sight-viewing structure for an engine nacelle, including a sight glass that is translucent or semi-translucent, a mounting frame, and a flame shield. The sight glass allows checking of oil levels of an aircraft engine accessory gearbox within the nacelle without doors and springs that can be more susceptible to fail fire testing. The mounting frame has an outer side, an inner side opposite the outer side, and a frame opening formed through the mounting frame. The frame opening is covered by the sight glass, and the mounting frame is configured for attachment to an inner surface of the engine nacelle at a location with a hole through the engine nacelle, such that the sight glass can be viewed through the hole. A flame shield may be made of composite materials and covers the inner side of the mounting frame and peripheral edge regions of the sight glass.

Abstract: The present disclosure relates to a flight system and a failure responding method therefor. A flight system includes: a plurality of fuse boxes configured to control application of a voltage to at least one propulsion device; and an interlock control apparatus configured to control interlock lines between fuse boxes connected using the interlock lines among the fuse boxes to synchronize and control opening of the fuse boxes connected using the interlock lines.

Abstract: A method for controlling an aircraft having at least two engines burning fuel and a transmission system connected to a rotary wing, each engine having a power shaft connected to the transmission system. An energy-saving phase comprises at least one energy-saving period comprising controlling, at an active rating, with a control system, one active engine from the at least two engines, and using the control system to stop or control, at an inactive rating, each inactive engine from the at least two engines that is not the active engine.

Abstract: A component for an aircraft engine. The component is mountable externally to a core of the aircraft engine. The component includes an enclosure having a wall circumscribing a sealed inner chamber. The wall has an inner surface and an outer surface. The wall has a first wall portion welded to a second wall portion along a weld line extending about a perimeter of the enclosure. A mounting bracket is disposed on the outer surface for mounting the component to the core. A protrusion protrudes from one or more of the outer surface and the inner surface and extends along one or more of the outer surface and the inner surface concentrically with the weld line. Sn additional protrusion protrudes from one or more of the outer surface and the inner surface. The additional protrusion extends from the protrusion to the mounting bracket.

Abstract: An aircraft section comprising a fuel storage tank, a first strap, a second strap, at least one anchoring structure and at least one coupling portion; wherein: the first strap comprises two attachment portions anchored to the at least one anchoring structure; the second strap comprises two attachment portions anchored to the at least one anchoring structure; and the first strap and the second strap are arranged under tension such that the tank is maintained pressed against the at least one coupling portion by the first strap and the second strap. Also an aircraft with such a section.

Abstract: Example systems and methods for using multi-directional baffles in cryogenic fuel tanks are provided. An example cryogenic fuel tank comprises an inner surface defining an interior of the cryogenic fuel tank to hold a fuel and a plurality of baffles including a first baffle, the first baffle including a first member extending along a first plane and a second member extending along a second plane, the first plane different from the second plane, the second member connected to the first member, the plurality of baffles connected to the inner surface.

Abstract: A cryogenic fuel system for an aircraft, the cryogenic fuel system includes a fuel tank assembly that is configured to store a cryogenic fuel in a liquid phase during aircraft operation, and a cooling system that is associated with the fuel tank assembly. The cooling system is configured to maintain the fuel tank assembly within a predefined temperature range during non-flight operation.

Abstract: An aircraft having a wing, a dihydrogen-powered engine, a supply pipe for the dihydrogen, in which each wing has a front spar, a first rear spar extending behind the front spar and a second rear spar extending behind the first rear spar, in which the two rear spars together define a corridor, and in which each supply pipe extends backwards from the related engine then into the corridor of the wing carrying the related engine.

Abstract: A method and system for emergency landing routing and prioritization for an vertical takeoff and landing (VTOL) aircraft has been developed. First, an emergency condition onboard the VTOL aircraft is detected that requires a landing. The emergency condition onboard the aircraft is then categorized based on severity. All potential landing zones (LZs) for the VTOL aircraft are identified and categorized based on suitability for landing. The LZs for the VTOL aircraft are prioritized based on the severity of the emergency condition onboard the aircraft in view of the suitability of the LZs. Finally, a priority listing of the LZs displayed to an aircrew member of the VTOL aircraft.

Abstract: Provided is a thermocouple wire harness including a first branch, a second branch extending about ninety degrees from the first branch in a first direction and having a first pair of thermocouple terminal breakouts extending therefrom for coupling to a first thermocouple, and a third branch extending about ninety degrees from the first branch in a second direction opposite the first direction, the third branch having a second pair of thermocouple terminal breakouts extending therefrom for coupling to a second thermocouple, a third pair of thermocouple terminal breakouts extending therefrom for coupling to a third thermocouple, and a fourth pair of thermocouple terminal breakouts extending therefrom for coupling to a fourth thermocouple.

Abstract: A catapult is disclosed. The catapult according to an embodiment of the present invention, comprises: a take-off assisting member contacting an aircraft to push the aircraft; a power source coupled to the take-off assisting member to drive the take-off assisting member; and a winch coupled to the take-off assisting member.