Abstract: A chain guide is disclosed herein. The chain guide includes a backplate and a chain guide. The backplate has an elongated opening therein. The chain guide includes a guide to orient a chain with respect to the sprocket. The chain guide also includes a retaining assembly to removably and adjustably frictionally couple the guide at a given location along the elongated opening in the backplate, such that when the guide is rotated axially about the retaining assembly, the guide is retained at the given location.

Abstract: A recessed and retractable mooring line device includes a housing having a mooring head that is configured for projecting through an opening or recess of a mounting structure so that an upper surface of the mooring head does not project from an outer surface of the mounting structure. A reel assembly is coupled to the housing and positioned below the mooring head to take up a flexible mooring line. The reel assembly includes a rotatable spool for winding the line. A ratchet wheel and spool that is engaged by a pawl prevents rotation of the ratchet wheel and spool when engaged. A moor head assembly that includes a pawl actuator actuates the pawl. An actuator lock of the moor head assembly engages the pawl actuator to keep it engaged with the pawl. A line anchor is used for securing to an end of the mooring line.

Abstract: An accessory system for a pontoon boat includes a support comprising longitudinal members and at least one support crosspiece connected between the longitudinal members, where the support can be attached to a structural component of a pontoon boat and move between a stowed position and a deployed position. An accessory component includes one or more hangers with a hook constructed to engage the support. A support portion is connected to the accessory component and extends transversely away from the one or more hangers. In use, the support can be deployed along a side of a pontoon with the accessory component removably attached to the support. The accessory component can be used to support a platform, a grill, a cooler or other accessory alongside the pontoon boat.

Abstract: Boats can include a swim platform with an integrated system of steps that can be selectively deployed and retracted. Such platforms can be attached to a transom of a boat or can be fabricated as an extended portion of the boat's hull. In another embodiment, deployable steps can be integrated with a boat's hull as a side-entry door. In order to reconfigure the step system into a deployed configuration, a linkage is actuated that causes the step system to unfold, forming steps (or a seating configuration) at least partially below the water line. Since the steps can be deployed below the water line, a swimmer can more easily get on board the boat.

Abstract: A truss system may include a plurality of beams. Each beam of the plurality of beams may have various cross-sectional sizes in a same plane. Additionally, the plurality of beams may have a geometric arrangement such that a structural weight at required strength level may be reduced to achieve optimal design.

Abstract: A water flow deflection device configured to be attached to a side of a watercraft for wake enhancement, the water flow deflection device having a water flow deflector having a stationary portion operably connected to a foldable portion, the foldable portion capable of being configured between a fully extended position and a folded position with intermediate folding positions there between, whereby the foldable portion in the folded position is configured to facilitate storage of the device. The water flow deflection device also includes a frame connected to the stationary portion of the water flow deflector, the frame including a base, at least one extension arm, and two or more suction cups for attaching the water flow deflection device to the side of the boat.

Abstract: A floating oceanic debris collection device may include a circular base, a debris collection unit, and a debris storage unit. The debris collection unit may include a blade erected on an upper surface of the base and an arm extending in an outward direction to a rotation direction side. The debris storage unit may include an annular inner peripheral float installed on a lower surface of the base, an inlet penetrating a peripheral surface of the inner peripheral float, and an outlet penetrating the upper surface of the base. An entirety of the base may be configured to rotate via receiving wind on the sea with the blade. The arm may be configured to scrap debris floating on a sea surface inward. The inlet may be configured to introduce the debris to an inside. The outlet may be configured to facilitate removal of the debris from the debris storage unit.

Abstract: A system for transmission of power offshore comprises two or more power stations operably connected with a high voltage cable system. The high voltage cable system may comprise a dynamic, dry type high voltage submarine cable of varying length configured to transmit at least about 45 megawatts of power. In some cases the dynamic, dry type high voltage submarine cable comprises a first end connected to an offshore power station and second end connected to a static submarine cable system which is connected to an onshore power station. The systems may facilitate transmission of power for applications such as compressing and/or pumping subsea natural gas in deep water.

Abstract: Aspects of the invention may be related to a computer system and a computerized method of controlling a marine vessel. Embodiments may include: receiving, by a controller, a position of the marine vessel from a positioning system; receiving, by the controller, geographical data, from at least one database, the geographical data may include at least a map of seabed depths; receiving, by the controller, a heading direction and speed of the marine vessel; calculating, by the controller, a safety zone ahead of the marine vessel based on the position, the heading direction and the speed of the marine vessel; identifying a location of a critical seabed depth inside the safety zone based on the received, the geographical data; and changing, by the controller, a state of a propelling unit of the marine vessel when a critical seabed depth was identified inside the safety zone.

Abstract: A device for the cleaning of a submerged section of the hull of a vessel that is treated with a non-toxic layer of paint based on a surface-treated coating. The device comprises a platform with a first cleaning module and with a device to place and move the cleaning module against the side of the hull of the vessel and that the device is further provided with a launch platform with a second cleaning module which can place the second cleaning module against the bottom of the hull. The second cleaning module is connected via a first cable to the launch platform for the movement and control thereof.

Abstract: The invention relates to a structure (2) for supporting a wind turbine tower (1) provided with a housing (7) for fitting therein the foot of the tower (1), a main axis (?) being defined on the platform (2) which coincides with a main axis of the tower (1), and which comprises a body with a constant cross-section and internal walls (8) and intermediate walls (10) joined by internal radial ribs (11) perpendicular to the internal wall (8) whose plane passes through the main axis (?), such that at the intermediate wall (10) first joining nodes (12) are defined between the intermediate wall (10) and radial ribs (11), the intermediate wall (10) and an external wall (9) being joined by reticular ribs (14 and 15). This structure provides an optimal transmission of forces. The invention likewise relates to methods for manufacturing, assembling and installing the structure.

Abstract: The invention relates to an underwater device for capturing images of a seabed, comprising at least one sensor for detecting a sensor value, at least one electrical consumer and an electrical energy source for supplying electrical energy to the electrical consumer. The underwater device is characterised in that, based on the sensor value, it is determined whether a hazardous condition exists for the electrical consumer and an energy distribution unit is provided which disconnects the electrical consumer from the electrical energy source if a hazardous condition exists.

Abstract: A limit switch device for a boat lift includes a lower gear connected to and rotated by a drive shaft of the boat lift, and an interengaged upper gear operatively connected to an electronics module of the limit switch. The interengaged gears are enclosed within a gear housing that is sufficiently narrow to restrict the gears from laterally disengaging one another. The limit switch electronics module is mounted above the drive shaft and disposed interiorly of the gear mechanism. The module does not protrude beyond the frame bearing blocks that rotatably support the drive shaft and winder of the boat lift.

Abstract: A modular underwater vehicle includes a hull having a series of modular sections, defining an interior housing, a propulsor coupled to a stern of the hull, a series of control surfaces coupled to the propulsor or the stern of the hull, and a power supply, a processor, and a nonvolatile memory device in the interior housing. The nonvolatile memory device has instructions stored therein which, when executed by the processor, cause the processor to supply power from the power supply to drive the propulsor and to actuate the plurality of control surfaces. At least one modular section of the series of modular sections is detachable.

Abstract: A propeller (20) for a marine vessel (10), the propeller (20) comprising a plurality of propeller blades (24, 26). The propeller blades comprise a leading edge (30), a trailing edge (32) and an outer edge (34) located between the leading edge and the trailing edge. A transition from the leading edge to the outer edge occurs at a first transition point (36) and a transition from the outer edge to the trailing edge occurs at a second transition point (38). A straight line from the first transition point to the second transition point coincides with the outer edge (34) or is located at least partially outside the propeller blade. A smallest distance (D2) from the second transition point to the axis of rotation (A) is smaller than a smallest distance (D\) from the first transition point to the axis of rotation.

Abstract: A device includes a hub and a blade. The hub has a cylindrical geometry. The blade extends radially from the hub. The blade has a helical structure. The blade includes a leading edge, a winglet, a trailing edge, and a trough. The leading edge is formed on the blade and has an arcuate geometry. The winglet of the blade is distal relative to the hub. The winglet angles away from a surface of the blade. The trailing edge is formed on the blade to be opposite the leading edge. At least a portion of the trailing edge forms a pitch-line cup that is angled with respect to the surface of the blade. The trough is formed in a transition between the pitch-line cup of the trailing edge and the winglet. The trough forms a recess that is relatively closer to the surface of the blade.

Abstract: A propeller having a plurality of blades extending radially outward from a hub, the blades forming a loop. Each loop having an intake portion, an exhaust portion and a tip portion extending radially outward from the hub and a gap between the intake root and the exhaust root. The tip portion of each of the blades is 30%-75% of the blade, the tip portion beginning at a first deviation from zero of the roll value and extending to 90 degrees, wherein roll value is zero in a plane parallel to the hub axis, and wherein the blades have a vertical angle between ?45 degrees and 45 degrees throughout.

Abstract: A method of operating a steering system on a marine vessel includes changing a maximum drive angle defining a permitted drive angle range for at least one marine drive and then, based on a steering map correlating wheel positions of a manually rotatable steering wheel to drive angles of the marine drive, adjusting at least one end stop wheel position to an adjusted end stop wheel position based on the changed maximum drive angle. Once it is determined that a current wheel position of the steering wheel is approaching the adjusted end stop wheel position, a resistance device is controlled to apply a resistance force against rotation of the steering wheel in a first rotational direction past the end stop position. The steering actuator associated with the marine drive is then controlled based on the steering map such that a drive angle of the marine drive stays within the permitted drive angle range.

Abstract: A method of controlling an electric marine propulsion system configured to propel a marine vessel including measuring at least one parameter of an electric motor in the electric marine propulsion system and determining that the parameter measurement indicates an abnormality in the electric marine propulsion system. A reduced operation limit is then determined based on the at least one parameter measurement, wherein the reduced operation limit includes at least one of a torque limit, an RPM limit, a current limit, and a power limit. The electric motor is then controlled such that the reduced operation limit is not exceeded.

Abstract: A vessel speed control system includes a lever operator on which an operation is performed to increase or decrease a propulsion speed of the vessel, a transition operator on which a transition operation is performed to transition a normal operation mode to a speed control mode, and a controller configured or programmed to perform a control to prevent transition to the speed control mode even when the transition operation is performed on the transition operator during a restriction period of time including at least an acceleration/deceleration period of time during which a rotation speed of an engine or the propulsion speed of the vessel is changed by the lever operator in the normal operation mode.

Abstract: A swivel gyro-mount system for a self-contained air conditioning system, disclosing a unit having a main body with an evaporator having an evaporator cover with an aperture bordered on a side opposite of the evaporator by a plurality of frustum-spherical wall sections, thereby creating a boundary. A frustum-spherical gyro-swivel ring is positioned within the boundary of the frustum-spherical wall sections. A fitment ring is removably affixed to a protruding lip of the frustum-spherical gyro-swivel ring. The frustum-spherical wall sections movably contain the frustum-spherical gyro-swivel ring in a tight periphery, thereby allowing the frustum-spherical gyro-swivel ring to adjust in orientation, whereby the adjustment in orientation influences a direction of airflow in a conical range of orientations to a blower, whereby said blower may expel air in a plurality of selectable directions in a range of angulation resembling a dual conical shape.

Abstract: A lighter-than-air craft including an envelope. A mixture of helium and hydrogen disposed within the envelope. The mixture having a ratio of helium to hydrogen such that the mixture is nonflammable during operating conditions for the lighter-than-air craft. The mixture provides buoyancy for the lighter-than-air craft. A hydrogen fuel cell fluidically coupled with the mixture and configured to utilize the mixture to generate electricity. A propulsion system is coupled to the envelope, and the propulsion system is configured to provide propulsion for the lighter-than-air craft. The propulsion system is electrically coupled with the hydrogen fuel cell and receives electricity generated by the hydrogen fuel cell. The propulsion system is configured to utilize the electricity in providing the propulsion to the lighter-than-air craft.

Abstract: An aircraft includes an airfoil and a hinge member to rotatably couple the airfoil to a structure of an aircraft. The hinge member defines at least a portion of a rotational axis. The aircraft also includes an indexing mechanism coupled to the airfoil and configured to, in a first state, inhibit rotation of the airfoil about the rotational axis, and in a second state, to permit rotation of the airfoil about the rotational axis between a first position and a second position that is angularly indexed relative to the first position. The aircraft further includes an actuator to selectively change a state of the indexing mechanism from the first state to the second state, from the second state to the first state, or both.

Abstract: Embodiments of the present invention discloses a wing detachment assembly and an aerial vehicle. The wing detachment assembly includes a first connecting portion and a second connecting portion, one of the first connecting portion and the second connecting portion being fixed on a wing and the other being fixed on a vehicle body. The second connecting portion includes a thumb wheel, the thumb wheel being provided with a threaded hole and being rotatably mounted on the vehicle body or the wing. The first connecting portion is threadedly connected to a threaded hole of the thumb wheel, the first connecting portion and the thumb wheel being fastened or detached when the thumb wheel is rotated. The aerial vehicle includes the foregoing wing detachment assembly. The wing detachment assembly and the aerial vehicle have the advantage of being convenient to detach and mount the wing.

Abstract: A coupling system and method are configured to secure one or more spars of a wing of an aircraft to one or more struts. The coupling system and method include a plurality of interface joints that secure the one or more spars to the one or more struts. At least a portion of a front surface of the one or more spars is linearly aligned with at least a portion of a rear surface of the one more struts.

Abstract: A system for controlling the pitch of a propeller blade for an aircraft turbine engine is provided. The system generally includes a cup having an annular wall extending about a pitch setting axis of the blade, the annular wall having a lower axial end enclosed by a bottom wall, and an upper axial end that is open and configured so as to enable a root of the blade to be mounted in the cup; and a locking ring that extends around the pitch setting axis and is configured to be mounted around the root, the locking ring being a double dog ring that comprises two annular rows of outer dogs constituting active and safety dogs, respectively.

Abstract: The invention relates to a composite blade (5) for a turbine engine rotor, for example, an unducted propeller, comprising a skin (6) made of woven fibres forming the outer profile of the blade and an attachment (11) with cylindrical geometry in the direction of the span emerging from the blade root (9), which attachment is intended to retain the blade (5) on a hub of the rotor, characterised in that it further comprises a spar (16) having a hollow tube structure made of braided carbon fibres, fixed to the attachment (11) and extending inside the skin (6) over at least part of the span of the blade (5). The invention also relates to a propeller comprising said blade and to a method for manufacturing said blade.

Abstract: Systems, methods, and apparatus for controlling aircraft roll operations are disclosed. An example system includes an aileron actuator including a mode selector valve to control fluid flow through the aileron actuator, and a valve spring coupled to the mode selector valve, the valve spring to adjust the mode selector valve from the active position to a block position, the block position to prevent fluid flow through the aileron actuator, a wing cable system coupled to the aileron actuator, a wing actuator coupled to the wing cable system, the wing actuator to control displacement of the aileron of the aircraft in response to the mode selector valve being in the block position, and a differential linkage coupled to the wing actuator and the aileron, the differential linkage to translate the displacement of the wing actuator into rotational movement to adjust the aileron from a first position to a second position.

Abstract: A hinge assembly 8a for an aircraft component comprises first and second hinge plates 9, 10, each hinge plate including a plurality of fingers 13 to 17. The fingers of the first and second hinge plates are interleaved. A seal assembly 28 to 32 is provided between at least some of the fingers. The provision of a hinge including interposed fingers allows for a hinge assembly having a complex aerodynamic profile to be made, while the sealing function is performed by the seals filling the gaps between the fingers.

Abstract: An uplock for the selective retention of a capture pin of a movable element includes a hook, a locking member, and a detector. The hook is movable between a release position and a retaining position for retaining the capture pin. The locking member moves between a locked position, and an unlocked position. The detector detects whether the hook is in the retaining position and the capture pin is in the hook. The detector includes a sensor movable relative to a target. The target or the sensor is carried by the locking member and the other by an indicator lever which is movable between a first position indicating absence of the capture pin in the hook and a second position indicating presence. The target and the sensor are only in the proximate position if the locking member is in the locked position and the indicator lever is in the second position.

Abstract: A landing gear for a flight vehicle is used during landing. The landing gear for a flight vehicle includes a first cylinder structure configured to have an upper end which is coupled to be able to roll with respect to the flight vehicle; and a second cylinder structure configured to have a lower end which is able to come into contact with the ground, configured to be able to relatively move in an axial direction along a reference axis with respect to the first cylinder structure, and configured to be able to relatively rotate about the reference axis with respect to the first cylinder structure. The first cylinder structure and the second cylinder structure switch the landing gear between a stowed state and a released state by means of the relative movement and the relative rotation.

Abstract: A shock absorber system for a vehicle includes a first shock absorber with a first cavity and a second shock absorber with a second cavity, wherein the first and second shock absorbers are located on a same side of the vehicle. The shock absorber system further includes a conduit in fluid communication with the first and second shock absorbers so that the second cavity maintains fluid communication with the first cavity through the conduit. The first and second cavities are at least partially filled with a gas.

Abstract: An aircraft provided with a rotary wing driven by a mechanical kinematic linkage, the aircraft having a power plant provided with at least one engine, the mechanical kinematic linkage comprising a free-wheel associated with the engine, the free-wheel comprising a driving part and a driven part, the driving part being connected by a mechanical connection to a working shaft of the associated engine and the driven part being connected kinematically to the rotary wing. A disengageable connection is arranged in parallel with the free-wheel in order to transmit mechanical power between the rotary wing and the engine on request, the power plant having a braking system comprising an engine brake of the engine.

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: An electrical conductor assembly for a rotor blade includes a substrate and at least one electrical conductor. The substrate includes an inboard end portion and an outboard end portion. The at least one electrical conductor is attached to the substrate and extends between the inboard end portion and the outboard end portion. The at least one electrical conductor is configured to transmit electricity along a length of the rotor blade. The inboard end portion and the outboard end portion are structured such that when the electrical conductor assembly is installed within the rotor blade, the inboard end portion is securable relative to the rotor blade and the outboard end portion is movable relative to the rotor blade.

Abstract: The aircraft includes a fuselage, a front wing and a rear wing provided to extend laterally from the fuselage for generating lift during cruise, a boom 18 supported by the front wing and the rear wing to be spaced apart from the fuselage, and at least one VTOL rotor that is supported on the boom, and having one or more blades for generating thrust in a vertical direction during take-off and landing, wherein the boom has a shape in a top view in which a barrel forms a curvature in a direction away from the fuselage with respect to a front end and a rear end while extending in a front-back direction, and has a cross section in a front view in which an upper side forms a round curvature, the boom being tapered from an upper side from a lower side, and the lower side is substantially flat.

Abstract: A vertical take-off and landing (VTOL) aircraft (100) having: a wing structure having right and left side forward wings (20, 22); and right and left side rearward wings (30, 32), each of the right side wings (20, 30) being connected, and each of the left side wings (22, 32) being connected in a box wing configuration; wherein each wing (20, 22, 30, 32) has a fixed leading edge (100) and at least one moveable trailing control surface (110), further wherein each wing (20, 22, 30, 32) has at least one motor pod (195), the motor pod (195) being pivotally mounted to an underside of the fixed leading edge (100), and fixedly secured to the trailing control surface (110).

Abstract: A deformable aerospace structure includes a first layer and a second layer spaced from the first layer and defining a space therebetween. The space includes one or more reinforcement elements extending between the first layer and the second layer. The ends or portions of the reinforcement element(s) proximate to the first layer are connected thereto and ends or portions of the reinforcement element(s) proximate to the second layer are moveable with respect to ends or portions of adjacent reinforcement element(s) proximate to the second layer.

Abstract: A crash detection device for mounting on a flying object having a parachute or paraglider deployment device. The crash detection device includes a sensor for measuring a parameter related to a flying state of the flying object. The sensor is configured for acquiring data of the parameter in a normal mode in which the data is acquired at a sampling frequency of less than 1 kHz, and in an abnormal mode in which the data is acquired at the sampling frequency of 1 kHz or more. The crash detection device further includes a detector coupled to the sensor and configured for verifying proper operation of the sensor; and a controller configured for receiving from the sensor values of the parameter and for determining flying state of the flying object.

Abstract: The present invention relates to systems and methods for powering and controlling flight of an unmanned aerial vehicle. The unmanned aerial vehicles can be used in a networked cellular communication system. A tether management system can be used to facilitate both mobile and static tethered operation to provide power and/or voice and data communication.

Abstract: A method for coordinating initiation of a power plant of a telecommunications site is disclosed herein. The method includes receiving construction plans and other project details for the power plant. The method also includes receiving data responsive to an initial site visit with the data representing field conditions of the telecommunications site, the data capture including one or more of photos and videos of existing infrastructure of the telecommunications site selected to receive and interface with the power plant. The method further includes generating one of a 360 degree view and a model of the existing infrastructure selected to receive and interface with the power plant. The method yet further includes ensuring the construction plans match the field conditions including the conditions of the existing infrastructure selected to receive and interface with the power plant and identifying any obstacles to the installation of the power plant.

Abstract: An unmanned aerial vehicle (UAV) has a wing assembly that is coupled to a cargo carrying pod. The pod has a pallet storage volume and an aerodynamic outer surface. The wing assembly has wings that are coupled to rotor booms that include motors and rotors. A tail assembly is coupled to tail booms that extend back from the wings. Rudders are coupled to the rear portions of the tail booms and an elevator is coupled to top portions of the rudders. The elevator is at least 84 inches high and the rudders are at least 48 apart so that a forklift can drive under the elevator and between the rudders to a rear door of the pod to place cargo on a pallet into the storage area of the pod.

Abstract: A flying machine storage container is provided that comprises multiple charging stations and a clamping mechanism. The clamping mechanism is configured to secure flying machines in the charging stations and securely close charging circuits between the storage container and the flying machines. A system for launching flying machines is also provided. The system comprises two regions and a transition region between the two regions. The two regions each constrain the positioning of a flying machine and the transition region enables a flying machine to move from the first region to the second region to reach an exit. A flying machine having sufficient performance capabilities will be able to successfully launch. Centralized and decentralized communication architectures are also provided for communicating data between a central control system, multiple storage containers, and multiple stored flying machines stored at each of the storage containers.

Abstract: Various arrangements for managing network channels are presented. A backend system can receive data from one or more data sources. Based at least in part on the data received from the one or more data sources, a triggering event and a location related to the triggering event can be determined. Location data associated with the location related to the triggering event can be transmitted to a UAV and the UAV deployed. While the UAV is deployed at the location, the UAV can relay data between wireless devices, such as cellular phones, and a network access point, such as a cellular base station.

Abstract: The technology relates to payload separation during descent of an aerial vehicle. A flight termination system (FTS) for a lighter than air (LTA) vehicle can include a first, a second, and a third mechanical actuation system. The first mechanical actuation system can be triggered in a first stage, causing an envelope and a payload of the LTA vehicle to separate. The second mechanical actuation system can be triggered in a second stage, causing a parachute to deploy from a component coupled to the payload. The third mechanical actuation system can be triggered in a third stage, causing a parachute to deploy from the envelope. In some cases, one or more of the mechanical actuation systems includes a squib.

Abstract: A component (6) for a passenger cabin (2) of a passenger aircraft (4) contains a base body (8) with a surface (10), and a layer structure (12), which is applied to the surface (10) and contains at least two layers in the form of at least one active layer (14) and an adhesive layer (16) arranged between the active layer (14) and the surface (10), wherein the active layer (14) contains at least one surface section (18a-c) which is formed from an electrically controllable colour-changing film (20), wherein at least a part of the colour-changing film (20) forms a visible surface (22) for the intended purpose in the passenger cabin (2).

Abstract: The current document is directed to an enclosure for electronic equipment that secures the electronic equipment within a storage space, provides ventilation for the electronic equipment, which generates heat during operation, and protects the electronic equipment from mechanical insults while, at the same time, providing access to control features and display features on the front panel of the electronic equipment. The currently disclosed enclosure includes cooling ports that allow for exchange of air between the external environment and the interior of the enclosure. One implementation of the currently disclosed enclosure can be partly disassembled in order to quickly secure the electronic equipment within the enclosure and can then be quickly reassembled for storage.

Abstract: A system configured to transfer an individual between an area and a toilet within a lavatory includes a base, one or more rollers coupled to the base, and a seating assembly coupled to the base. The seating assembly includes a backrest, a toilet overlay seat configured to be disposed over the toilet, and a seat cover that is movable between a covering position over the toilet overlay seat, and a lavatory use position in which the toilet overlay seat is exposed. A counterbalance is coupled to one or both of the base or the seating assembly. The counterbalance is moveable between a stowed position and a deployed position in relation to the toilet.

Abstract: An on-board toilet cubicle for an aircraft, including a front long side and a rear long side; a front short side and a rear short side, which are each connected at one end to the front long side and at their other end to the rear long side, the long sides and the short sides enclosing an interior of the toilet cubicle, and the front and the rear long sides each being wider than the front and the rear short sides; a toilet unit with a toilet opening; and an L-shaped door for accessing the on-board toilet cubicle, the L-shaped door having one door leg in the front long side and one door leg in the front short side, the toilet unit arranged adjacent to the rear long side, and the door leg in the front long side being wider than the door leg in the front short side.

Abstract: A data transfer system is disclosed for a galley insert used in an aircraft, which includes an electronic interface having an integrated antenna configured to utilize a wireless communication protocol to add data relating to insert status into a message reported to a maintenance engineer by way of a wireless reader.