Abstract: A fishing trap handling system for handling fishing traps on a deck of a fishing vessel is provided. The fishing trap handling system comprises a gantry crane type lifting apparatus for being mounted to the fishing vessel. The lifting apparatus is adapted for operation while the fishing vessel is exposed to rough seas. An end effector is mounted to a hoist of the lifting apparatus. The end effector is adapted for easily engaging one of the fishing traps and for holding the fishing trap in a substantially horizontal orientation.

Abstract: A passenger bridge including a least one passenger bridge end segment; a bridge head, arranged at a distal end of said bridge end segment; a cabin, arranged to move about an outer periphery of the bridge head and comprising a door for passengers; and a cabin suspension, arranged to allow the cabin to rotate in relation to the bridge head about a vertical axis (A1). The application further relates to a cabin suspension including a pivot arm in journaled engagement with an upper part of the bridge head so that the cabin can swing in a first horizontal plane (P1), and in that a cabin holding part of the pivot arm is fastened to an upper part of the cabin, whereby the cabin hangs from the said cabin holding part.

Abstract: This invention provides a method and apparatus for transporting marine fuel by rail car directly to a fueling vessel, by loading rail cars loaded with marine fuel onto a specially equipped roll-on/roll-off rail barge and transporting the barge by towboat to a mooring, where it is moored/secured in position, after mooring the barge will have the capability for offloading marine fuel from its rail cars via a barge-included distribution system to fuel a vessel. The barge may operate and be regulated as a fuel terminal when secured to the mooring.

Abstract: A drag-inducing mat includes a main body configured to accommodate a rider. The main body includes a rider surface configured to face the rider and an opposing surface configured to face a slide surface. The drag-inducing mat also includes a sipe array defined within the opposing surface. The sipe array includes a plurality of sipes that extends from a first lateral edge of the main body to a second lateral edge of the main body to selectively induce friction between the main body and the slide surface based on force applied to the sipe array by the rider.

Abstract: A flotation device includes a main body portion having a leg rest, seat, back rest, and headrest. Arms are adjustably attached to the back rest via hinge mechanisms which allow the arms to be pivoted towards and away from the main body portion, and which allow the length of the arms' extension from the main body portion to be adjusted. In alternative embodiments, cupholders are secured in apertures in the arms, with headrest extensions providing additional buoyance to the head rest portion.

Abstract: A system for improving the static and dynamic stability of an offshore floating structure in which outriggers having a unit with an inertial mass are supported from the structure to hold each unit at a radial distance from a centre of rotation of the offshore floating structure and be entirely submerged. Water may enter and exit a tank in a unit to statically adjust and dynamically control stability and dampen roll and pitch of the structure. The outriggers can be raised for tow. The outriggers ballast can be adjusted during tow, installation and in operation. The units can transport mooring lines. An embodiment of a hydrocarbon production or support facility is described with the dynamic flexible risers connected to a support structure of the system.

Abstract: A diving mask includes a metal frame, a soft rubber mask, and a lens. The diving mask consists of the metal frame, the soft rubber mask and the lens. The frame of the diving mask is a metal frame. The metal frame includes an outer frame and an inner frame. The lens is sandwiched between the inner frame and the outer frame and is fixed through a fixing structure, which improves the structural stability of the diving mask.

Abstract: Disclosed is a mast intended to equip a marine or submarine vessel. The mast includes a metal structure extending along an axis and a fairing arranged externally to the structure in a direction normal to the axis. The fairing is removably assembled to the structure.

Abstract: An accelerating ducted propeller system for propelling boats offers enhanced performance, having the front end of the nozzle disposed at a radial distance (H) between 0.045D and 0.082D from the inner radius of the nozzle, where D is the inner diameter of the nozzle. The front end of the chord of the axial profile of the nozzle has a larger radius than the rear end of the chord with respect to the axis of rotation of the propeller. The inner surface of the nozzle at the axial distance (J) of 0.025D from the rear end of the output edge of the nozzle is at a radial distance from the inner radius of the nozzle of more than 0.0040D and less than 0.0300D. The radial difference between the inner radius of the nozzle and the outer radius of the profile of the nozzle is less than 0.092D.

Abstract: An accessory sleeve that fits over an oar combination is disclosed herein. The sleeve is configured with a ruler or a tape measure printed on a surface thereof. Further, the sleeve comprises neoprene that yields proper feel and grip while stretching slightly so that the sleeve can be easily applied and removed, if necessary. The ruler is supported underneath by a nylon strip that prevents shrinking initially and any stretching during the useful life of the sleeve.

Abstract: In an example, a composite stringer is described. The composite stringer includes a skin flange having a first gage, a top flange having a second gage, and a web having a third gage and extending between the skin flange and the top flange. The skin flange is configured to be coupled to a support structure. The support structure includes at least one of a skin of a vehicle or a base charge. The second gage of the top flange is greater than the first gage of the skin flange and the third gage of the web. The skin flange, the top flange, and the web include a plurality of plies of composite material.

Abstract: In an example, a composite stringer assembly includes a composite stringer, a radius filler, and an overwrap layer. The composite stringer includes: (i) a skin flange configured to be coupled to a support structure, (ii) a web, (iii) a lower corner portion of the composite stringer extending from the skin flange to the web, and (iv) an inner surface of the composite stringer extending along the skin flange, the lower corner portion, and the web. The radius filler includes a first surface coupled to the inner surface at the lower corner portion, a second surface configured to couple to the support structure, and a third surface extending between the first surface and the second surface. The overwrap layer is coupled to the inner surface at the web, the third surface of the radius filler, and the support structure.

Abstract: A drain mast is provided that includes a unitary structure having a first housing, a second housing, and a plurality of tubes extending between the first housing and the second housing. The unitary structure is configured to provide a plurality of fluid paths through the drain mast, each fluid path extending through the first housing, one of the plurality of tubes, and the second housing.

Abstract: A process of joining a wing to an aircraft fuselage comprising the steps of: mapping the wing root of the wing, mapping the center-wing-box (CWB) of the aircraft fuselage, determining the position to provide the hole pattern on the CWB, providing the holes on the CWB, and attaching the wing root to the CWB. Primary and secondary templates with corresponding hole patterns may be used in combination with targets and laser trackers to implement the process. The hole pattern of the wing root can therefore be duplicated on the CWB at a position such that when the wings are joined to the fuselage, the aircraft will have optimum flight performance and dynamic symmetry. A predictive fit is thus provided, based on virtual representation and analysis, and advantageously permits the hole pattern to be provided without requiring the CWB and wing root to be brought together.

Abstract: Vortex reduction apparatus for use with airfoils are disclosed. An example vortex reduction apparatus includes a housing to couple to a tip of an airfoil. The housing defines a volute fluid flow passageway between an inlet and an outlet. The volute fluid flow passageway is structured to induce a rotational fluid flow in a first rotational direction opposite a second rotational direction of a shed vortex induced at the tip of the airfoil during flight.

Abstract: Systems and methods for bipedal nose landing gear of an aircraft. One embodiment is a nose landing gear of an aircraft. The nose landing gear includes a shock strut coupled to an axle with a nose wheel, and a folding side brace extending from the shock strut inboard toward a belly of the aircraft and configured to stabilize the shock strut. The nose landing gear also includes a trunnion configured to pivot the shock strut forward toward a nose and inboard toward the belly of the aircraft to retract the nose wheel.

Abstract: Systems and methods for wide set retracting landing gear of a cargo aircraft. One embodiment is an aircraft that includes a fuselage including a nose, and a pair of main landing gears comprising a pair of main posts disposed across the fuselage, each main post having a main wheel and configured to pivot forward toward the nose to retract the main wheel. The aircraft also includes a pair of nose landing gears comprising a pair of nose posts disposed across the fuselage, each nose post having a nose wheel and configured to pivot inboard to retract the nose wheel.

Abstract: Systems and methods for folding landing gear of a cargo aircraft. One embodiment is a main landing gear of an aircraft that includes a shock strut coupled to a truck with one or more wheels, and a yoke pivotally coupled with the shock strut via a lower trunnion, and pivotally coupled with an aircraft structure via an upper trunnion. The yoke is configured to pivot about the upper trunnion in a direction back toward a tail of the aircraft and up toward a fuselage of the aircraft, and the shock strut is configured to pivot about the lower trunnion in a direction forward toward a nose of the aircraft and up toward the fuselage of the aircraft to retract the one or more wheels.

Abstract: Systems and methods for pivoting main landing gear of a cargo aircraft. One embodiment is a main landing gear of an aircraft that includes a shock strut coupled to a truck with one or more wheels, and a trunnion coupled to a bulkhead and configured to pivotally couple the shock strut with the bulkhead. The main landing gear also includes a folding brace extending from the shock strut in a forward direction toward a nose of the aircraft and configured to stabilize the shock strut. The main landing gear further includes a retraction actuator configured to pivot the shock strut about the trunnion to retract the one or more wheels in the forward direction toward the nose and up toward a fuselage of the aircraft.

Abstract: A torque link assembly may comprise an upper torque link, a lower torque link, and a torque link pin. The upper torque link may define an upper hydraulic fluid channel. The lower torque link may define a lower hydraulic fluid channel. The torque link pin may fluidly couple the upper hydraulic fluid channel to the lower hydraulic fluid channel.

Abstract: An aircraft having a differential rotor speed resonance avoidance system. The aircraft includes an airframe having structural elements subject to resonant vibration at critical frequencies. A thrust array is coupled to the airframe. The thrust array includes at least four rotor systems distributed about the airframe, each rotor system operable over a range of rotor speeds. A flight control system is operably associated with the thrust array and is configured to independently control the rotor speed of each rotor system. While preserving flight dynamics during flight operations, the flight control system selectively increases the rotor speed of some of the rotor systems by a speed delta and decreases the rotor speed of others of the rotor systems by the speed delta to avoid generating excitation frequencies by the rotor systems at the critical frequencies.

Abstract: To provide a rotorcraft capable of improving flight efficiency. The rotorcraft according to the present invention is capable of moving forward along at least a first direction and comprises an arm part, a plurality of motors mounted on the arm part, and a rotary blade mounted on each of the motors. The rotorcraft is configured to have one or more motors one or more front motors located at a front side and one or more rear motors located at a rear side, wherein the output characteristics of a motor included in the front motor and the output characteristics of a motor included in the rear motor are different.

Abstract: Vertical takeoff and landing (VTOL) aircraft, especially electric VTOL (e-VTOL) aircraft include a fuselage (which may include a pair of ground-engaging skids) defining a longitudinal axis of the aircraft, forward and aft pairs of port and starboard aerodynamic wings extending laterally outwardly from the fuselage and forward and aft pairs of port and starboard rotor pods each being in substantial alignment with the longitudinal axis of the fuselage. In specific embodiments, each of the forward and aft pairs of port and starboard rotor pods comprises a forward and aft pair of rotor assemblies.

Abstract: Methods, apparatus, systems and a vertical take-off and landing (VTOL) vehicle are provided. The VTOL vehicle includes: a fuselage having longitudinally a front section, a central section and a rear section; a first lifting surface comprising two wings respectively secured to opposite sides of the rear section of the fuselage; a second lifting surface comprising two wings respectively secured to opposite sides of the front section of the fuselage; where each wing comprises at least one engine module, each of the engine modules being pivotally coupled to the wing and each engine module being independently controlled for transitioning between a vertical mode of flight and a horizontal mode of flight.

Abstract: The invention relates to the field of aviation, and more particularly to designs for vertical take-off and landing aircraft. A convertiplane comprising a fuselage, a pair of wings: fore and aft, propulsion systems comprising engines and propellers, a keel, a landing gear, and pylons designed so as to be rotatable. Two lift propulsion systems are arranged on the pylons with one degree of freedom with respect to the yaw angle along the sides of the fuselage so as to be fixable in position and retractable during horizontal flight forward or back in fuselage niches. A basic propulsion system is mounted on a pylon with two degrees of freedom with respect to the angle of bank and pitch so as to be fixable in position, and is arranged either in the nose section of the fuselage or in the keel, on the leading edge or the trailing edge thereof. This provides improved reliability and safety, increased flight range and reduced cost of the convertiplane.

Abstract: A propulsion system for an aircraft, comprising at least one rotor and a nacelle fairing extending around the at least one rotor with respect to an axis of rotation of the rotor, the nacelle fairing comprising: an upstream section forming an inlet section of the nacelle fairing; a downstream section, a downstream end of which forms an outlet section of the nacelle fairing; and an intermediate section connecting the upstream and downstream sections, wherein the downstream section comprises a radially inner wall and a radially outer wall made of a deformable shape memory material, and wherein the downstream end forming the outlet section has a pneumatic or hydraulic annular actuator extending around the axis of rotation and configured to deform radially under a predetermined control pressure so as to vary an outer diameter of the outlet section between a minimum diameter and a maximum diameter.

Abstract: An aircraft includes a wing that is extended through by a ducted fan having movable louvers.

Abstract: Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45? diameter) footprint.

Abstract: A vertical take-off and landing (VTOL) flying machine. The machine includes a ducted fan having an intake side and an outlet side, at least two co-axial rotors configured to contra-rotate about a fan axis X when driven in rotation; a primary drive source arranged substantially co-axially with the ducted fan and to the outlet side of the ducted fan; and first and second thrust air ducts configured to split thrust from the ducted fan into a pair of thrust streams and to guide the two respective thrust streams to opposite respective sides of the primary drive source, the ducts being rotatable to direct motion of the machine. A number of configurations of secondary drive sources and alternative thrust sources are provided for improved safety.

Abstract: A method is provided. An airship is maneuvered to a desired location and oriented with the thruster such that ambient wind is traveling in a direction that is substantially parallel to the longitudinal axis of the fuselage. The airflow from the ambient wind is straightened with the flow straightener to generate a substantially laminar flow. The turbine is engaged with the airflow generated by the ambient wind to generate electricity, and the electricity generated by the turbine is rectified with the rectifier and stored in the storage array.

Abstract: An autonomous drone is programed with the geo-location of one or more remote sensors, and the autonomous drone then flies to each of the remote sensors to acquire a most recent sensing data record, and then return to a base where the most recent data record for each remote sensor can be transferred to a computing system. Upon arriving at the location of each remote sensor, the drone causes the remote sensor to activate a local area radio transceiver so that a communication link can be established between the drone and the remote sensor.

Abstract: Cargo aerial delivery systems for delivering one or more delivery items and related methods. A cargo aerial delivery system may include a cargo container configured to carry the delivery item(s) and an unmanned aerial vehicle (UAV) configured to carry the cargo container to delivery destinations of the delivery items. The cargo container may include a programmable device that stores manifest information regarding the delivery item(s) and a local communication mode configured to convey delivery information from the cargo container to the UAV. A method of utilizing a cargo aerial delivery system may include loading delivery item(s) into a container body of a cargo container, entering manifest information into a programmable device, operatively engaging the cargo container with a UAV, generating a delivery itinerary, transporting the cargo container with the UAV according to the delivery itinerary, and unloading each delivery item at the respective delivery destination.

Abstract: A method for selecting an operation mode of a mobile platform includes detecting a height grade of the mobile platform and selecting an operation mode of the mobile platform according to a result of the detecting.

Abstract: An unmanned aerial vehicle includes a body, a propulsion system connected to the body. The propulsion system generates a lift force in a vertical direction opposite of a gravitational force when activated. In some cases, the unmanned aerial vehicle includes an applicator connected to the body. The applicator includes a channel, a chamber in fluid communication with the channel, and a nozzle in fluid communication with the channel.

Abstract: A slim aircraft monument is disclosed. In embodiments, the monument is installable in an aircraft passenger cabin adjacent to a cabin space (e.g., in front of an otherwise unused exit door). The slim monument has an overall width of not more than four inches. The slim monument includes a side door with an external handle, the door deployable into the cabin space to reveal a group of nested interconnected panels within. The nested panels are similarly deployable into the cabin space to form a substantially horizontal work surface and, underneath the work surface, vertically stacked bays providing temporary storage for storage drawers and a cart space adjacent to the storage drawers, the cart space capable of accommodating a half-size galley cart.

Abstract: Provided is a toilet exterior structure of an aircraft lavatory unit. A shroud mount in an upper end outer peripheral plate portion is provided in a lower surface of a main body plate portion. The shroud mount includes space portions extending in the width direction of the main body plate portion between partition walls provided in the main body plate portion. Where the body plate portion is placed in the upper end outer peripheral plate portion, a plurality of air communication passages communicating a space inside of the upper end outer peripheral plate portion in the width direction and a space outside of the upper end outer peripheral plate portion in the width direction are formed by the space portions. Where the main body plate portion is stepped on by a foot, the plurality of partition walls are positioned inside of a contour of the foot.

Abstract: An adjustable table assembly for use in a passenger cabin environment such as an aircraft passenger suite including a passenger seat. The table assembly includes a fixed rail assembly attached to a monument, a support column rotatably mounted on the rail assembly, and a table mounted on the support column, the table having a stowed position and deployed positions in a first direction generally toward the passenger seat from the stowed position. The table has a predetermined stowage orientation at which the support column and table are movable along the rail assembly in a second direction opposite the first direction to the stowed position, and the rail assembly prevents the table from moving into the stowed position when the table is rotated out of the predetermined stowage orientation.

Abstract: A holder assembly, movable between stowed and deployed configurations, includes a holder including a flap configured to support a personal electronic device. The holder is configured to rotate between stowed and deployed positions. A latch assembly is configured to engage the holder in the stowed position, and a movement assembly is configured to automatically move the holder from the stowed position to the deployed position upon disengagement of the holder and latch assembly.

Abstract: Vertical take-off and landing (VTOL) aircraft can provide opportunities to incorporate aerial transportation into transportation networks for cities and metropolitan areas. However, VTOL aircraft can be sensitive to uneven weight distributions, e.g., the payload of an aircraft is primarily loaded in the front, back, left, or right. When the aircraft is loaded unevenly, the center of mass of the aircraft may shift substantially enough to negatively impact performance of the aircraft. Thus, in turn, there is an opportunity that the VTOL may be loaded unevenly if seating and/or luggage placement is not coordinated. Among other advantages, dynamically assigning the VTOL aircraft payloads can increase VTOL safety by ensuring the VTOL aircraft is loaded evenly and meets all weight requirements; can increase transportation efficiency by increasing rider throughput; and can increase the availability of the VTOL services to all potential riders.

Abstract: Provided are seat track fittings and methods for installing passenger seats in aircraft cabins using these seat track fittings such that the same seat can be installed on different types of seat tracks. A seat track fitting comprises a leg support, a pin, and a base interconnecting the leg support and pin. During installation of the seat track fitting, the pin is inserted into an attachment opening of the seat track. The attachment opening is selected based on the desired position of a seat. A removable fastener then protrudes through the base of the seat track fitting and is inserted into another attachment opening of the seat track. The seat is then attached to the seat track fitting by inserting the stud end of the seat into the leg support of the seat track fitting and fixing the stud end within the leg support.

Abstract: The present disclosure provides a parachute comprising a fabric-based canopy and a crown area air inlet formed in the fabric-based canopy. The crown area air inlet may be aligned with areas of highest external pressure acting on an external surface of the canopy as the parachute inflates in order to increase a rate of inflation of the parachute.

Abstract: An orientation valve, in accordance with various embodiments, is disclosed herein. The orientation valve may comprise a first coupling portion, an insert portion, a second coupling portion, an internal cavity, and a piston. The insert portion may have a first inlet aperture and a second inlet aperture. The second coupling portion may be disposed between the first coupling portion and the insert portion. The internal cavity may be coupled to the first inlet aperture and the second inlet aperture. The piston may be disposed within the internal cavity. The orientation valve may be configured to block fluid flow from a compressed fluid source when an evacuation system is in a stored position. The orientation valve may be configured to fluidly couple the compressed fluid source and the evacuation device when the evacuation system is in a deployed position.

Abstract: A hybrid aircraft propulsion system. The system comprises a gas turbine engine having a turbine system comprising first and second turbine sections. The gas turbine engine further comprises a first combustor provided upstream in core flow from the turbine system, and a second combustor provided between the first and second turbine sections. The hybrid aircraft propulsion system further comprises an energy storage system and an electric propulsion system electrically coupled to the energy storage system.

Abstract: An integrated controller for controlling a movable object includes a connector, a movement control subsystem communicatively coupled to the connector and configured to control movement of the movable object, a vision subsystem communicatively coupled to the connector and configured to provide visualization of an operating environment surrounding the movable object, and a platform subsystem communicatively coupled to the connector and configured to provide timing and power management to the movement control subsystem and the vision subsystem.

Abstract: A power module includes a turbo-generator with a propellant selector valve, a stored energy module connected to the propellant selector valve, and bleed air conduit. The bleed air conduit is connected to the propellant selector valve, wherein the propellant selector valve has a first position, wherein the stored energy tank is in fluid communication with the turbo-generator, and a second position, wherein the bleed air conduit is in fluid communication with the turbo-generator. Vehicles and methods of generating electrical power are also described.

Abstract: A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

Abstract: A cooling duct configured to introduce air flow to a cooling target device provided in a helicopter body of a helicopter includes a duct body, a front opening, an upper opening, a hinge, and a movable blade. The duct body is mountable below a main rotor of the helicopter to be adjacent to the cooling target device. The front opening is formed on a forward side of the helicopter body in the duct body. The upper opening is formed on an upper side of the helicopter body in the duct body. The hinge is disposed in an upper portion of the duct body and includes a pivot shaft extending in a lateral direction of the helicopter body. The movable blade with an end that is pivotally supported by the hinge is provided to be pivotable about the pivot shaft between a first position and a second position.

Abstract: An aircraft power plant comprising multiple electric drivetrains combined through a single output shaft, wherein each drivetrain is completely separate from the other, containing individual power sources, motor controllers, and motors, wherein the motors could be selected to provide efficient direct drive to the propulsor at the target propulsor RPM, to facilitate combining multiple motors on the same shaft without requiring mechanical gearboxes. During normal operation, each drivetrain will be operating below their maximum output levels, extending the durability of the motor controllers and motors.

Abstract: A system ensures the correct type of fuel is dispensed in an aircraft while removing the introduction of human error in the refueling process. The system includes an RFID tag disposed at one or more aircraft that electronically stores data such as engine type, engine hours, fuel type, tail number, and pilot/subscriber data for the aircraft on which the RFID tag is disposed. An RFID reader is disposed at or near a fuel dispensing mechanism, such as a fuel truck or tank. A signal indicative of fuel type is emitted from the RFID tag to the RFID reader. RFID tags on aircraft that are enrolled in the system's subscription service enable aircraft to be recognized by a module operating the fuel dispensing mechanism. Based on a comparison performed by the module, authorization to begin fueling is either permitted or declined.

Abstract: An aircraft is disclosed, including a fuselage having a compartment configured to house refueling apparatus. An auxiliary power unit is mounted in the compartment.