Abstract: Apparatus and methods for collecting debris from a body of water onto a waterborne vessel include at least one wave dampener and/or gate configured to limit inflow from the body of water into at least a first cargo compartment on the vessel to water and debris disposed at or near the surface of the body of water.

Abstract: A method for assembly of a riser string onboard a vessel that is adapted to perform subsea wellbore related operations involving said riser string, said riser string being configured to extend between a subsea wellbore and the vessel in a wellbore related operation, wherein the vessel including a hull, a riser storage adapted to store therein, in horizontal orientation, multiple pre-assembled riser stands and/or multiple individual riser stand, a deck structure having an elongated transfer opening above said riser storage, a transfer elevator, wherein multiple pre-assembled riser stands, each being pre-assembled from multiple riser sections connected end-to-end and each having a length of at least 150 ft. (45.72 m), and/or multiple individual riser sections each having a length of at least 150 ft. (45.

Abstract: A stable fishing raft that is easily transportable to the water without a trailer and has a deck large enough to easily and securely carry fishing gear. The deck and bottom are flat, and the sides are perpendicular to the deck and bottom. The deck is connected to the bottom at the bow and stern with a circular arc. The core of the raft is a buoyant foam, preferably polyurethane, and covered in a water-resistant resin, preferably polyethylene. The raft is steerable and propelled by paddle or trolling motor that attaches to a removable motor mount. In a preferred embodiment the raft has a recessed accessory track and a series of recessed rings on the deck to receive the bottom edge of a bucket and hold it in place as a seat. Rafts can be joined together with couplers.

Abstract: A water sports board is provided to be attached to the chest of a rider and allow the rider to hold onto a tow line of a powered watercraft and be pulled across water thus riding on the board. The water sports board is strapped to the rider utilizing an integrated harness system consisting of shoulder straps that cross the back of the rider (over a flotation device such as a life vest) and attaches to the board near the waist of the rider. The bottom of the water sports board includes a fin, ribs and water directing channels for allowing the rider to maneuver the board, and a water deflector positioned at or near the front of the board for purpose of deflecting water from spraying onto the face of the rider.

Abstract: An acquisition unit acquires weather and marine data indicating a ship voyage schedule that serves as a reference, actual performance data, fuel consumption data, and weather and marine conditions the ship has encountered during a voyage. A time difference data generation unit calculates the difference between the time indicated by the reference data and the time indicated by the actual performance data for each of the journeys between ports. Projected fuel consumption calculation unit calculates projected fuel consumption for each of the journeys between ports based on the reference data, weather and marine data and fuel consumption data. Fuel consumption difference data generation unit calculates the difference between the projected fuel consumption and the actual fuel consumption amount indicated by the actual performance data for each of the journeys between ports.

Abstract: A height adjustable depth finder system is provided such that a user may easily raise and lower the height at which a depth finder display is located. Height adjustability may be provided by one or more supports, with at least one support actively driven. The one or more supports may telescope to provide height adjustability and are actively driven by an actuator that may include a wire feed motor or a rack and pinion. In the event of two supports, the two supports may be perpendicular (side-by-side) or parallel (front and back) with the longitudinal axis of the boat. The longitudinal axis of the boat generally forms a “V” line at the lowest part of the hull running from the bow to the stern of the boat.

Abstract: A boat fender system comprising a boat fender including a first portion that absorbs kinetic energy to prevent damaging a surface of a boat. The first portion having a first surface facing out away from the surface of the boat. The boat fender including a second portion arranged with the first portion. The second portion having a second surface facing toward the surface of the boat. The boat fender including an adhesive arranged on the second surface of the second portion of the boat fender. The adhesive arranged on the second surface of the second portion of the boat fender adherable to the surface of the boat to make the boat fender immobile on the surface of the boat.

Abstract: A tangential flow machine can be operated both as electric propulsion and as a generator, having a jacket housing which can have flow passing around it on an outer side, the profile of which is formed on a first front-side opening, and tapers to a second front side, on which a second front-side opening is formed. Between the two front-side openings, there extends a flow path along a main axis, and with an electrical machine, which on the jacket housing has a stator and a rotor that is supported so as to rotate within the stator. The rotor defines a free rotary axis and has a rotor ring and an arrangement of rotor blades which each extend from the rotor ring, radially to a free edge and the free edges of the rotor blades, in the projection direction parallel to the main axis.

Abstract: What is provided is a propeller guard apparatus that may be readily configured to a variety of different boat motors. Described embodiments of the propeller guard apparatus comprise a cylindrical housing configured to circumferentially enclose a propeller from all sides in order to protect humans, pets, and aquatic wildlife from being entangled or cut by the propeller. Described embodiments of the propeller guard apparatus also comprise a protective structure, such as a skid plate comprising of at least two pieces of metal attached from the cylindrical housing to an end of the outer casing to form a folded T-shaped configuration. This type of configuration serves to protect the propeller from damage caused by submerged objects and aquatic wildlife found in shallow water. Also, the folded T-shaped configuration may push vegetation, weeds, manatees, and other aquatic wildlife away from the path of the moving boat and its propeller.

Abstract: A shipping container includes a container configured to be secured onto a vessel or a vehicle. The shipping container further includes at least one wingsail stored in the container and configured to be unfolded to deploy from the container and folded to be stowed in the container.

Abstract: A transom component having an upper arcuate slot threaded bolt hole there through and a lower arcuate slot pin hole there through. There is an associated lower arcuate slot pin. There is a transom cross brace. There is a motor component having an upper arcuate slot there through and a lower arcuate slot there through. There is a motor cross brace. There is a rotation pin and a slot pin.

Abstract: A variable multiple engine jack plate, comprising, in combination, a motor plate, a pair of center plate connectors, a pair of outer slides and a pair of inner slides. There is at least one hydraulic cylinder coupling the motor plate and the slides. There is a hydraulic pump system having a pump and a hydraulic fluid flow control valve and a hydraulic fluid reservoir holding a volume of hydraulic fluid.

Abstract: An outboard motor includes an engine including a crankshaft that extends in a horizontal or substantially horizontal direction and perpendicular or substantially perpendicular to a direction of a thrust force, a cylinder, a first gear provided on a balance shaft disposed in a direction that intersects with a direction in which the cylinder extends, a second gear, a drive shaft, and a propeller.

Abstract: An outboard motor performs assist control of assisting rotation of a crankshaft and performs power running rotation speed range expansion control of expanding a power running rotation speed range of a rotary electric machine in a state in which the crankshaft is rotated at a rotation speed within a cranking rotation speed range due to rotation of a rope reel.

Abstract: An outboard motor includes a shift rod including a first rod, a second rod, and a joint. The first rod extends in a vertical direction. The second rod extends in the vertical direction and is located below the first rod. The second rod is disposed eccentrically with respect to the first rod. When viewed in a plan view, the second rod overlaps with at least a portion of the first rod or is in contact with the first rod. The joint connects the first rod to the second rod.

Abstract: A cooling system is for a marine engine. The cooling system has a cooling fluid conduit that is configured to convey cooling fluid for cooling at least one component of the marine engine; a strainer disposed in the cooling fluid conduit and configured to strain the cooling fluid; and a quick connector that is manually operable to connect and disconnect the strainer from the cooling fluid conduit.

Abstract: An outboard motor includes an engine, a cooling water passage, a pump that is driven in conjunction with the engine, an inlet water passage that branches from the cooling water passage, an oil cooler, an outlet water passage, a first thermostat located in the cooling water passage, and a second thermostat. The pump takes outside water into the cooling water passage. The oil cooler includes a water-storing space into which water in the inlet water passage is taken. The outlet water passage is connected to an outlet of the oil cooler. The first thermostat increases and decreases the flow rate of water flowing through the engine. The second thermostat is located at the outlet or at the outlet water passage, and increases and decreases the flow rate of water flowing through the outlet water passage.

Abstract: A valve for a marine propulsion unit comprises a valve body (11) having an end face (13) and a wall (14) extending from the end face. An aperture (15) is defined in the end face. A valve stem (12) is moveable within and with respect to the valve body, such that, in the closed state of the valve, the valve stem closes the aperture. A maximum width (d1) of the valve stem is greater than the width (d2) of the aperture in the end face of the valve—so that, if the valve stem should fracture, the detached portion(s) of the valve stem will be retained in the valve body. The valve may for example be used as a cylinder drain valve in a marine propulsion unit.

Abstract: The present disclosure provides an apparatus for use on a balloon having a balloon envelope. The apparatus includes a frame body comprising first and second members, an adjustable arm attached to the first member and a circular heating element disposed on a surface of the second member. The adjustable arm may be configured to cause the first member to move in a direction with respect to the surface the second member. The surface of the second member may be arranged to receive a termination plate and a portion of a balloon envelope. By moving the adjustable arm between first and second positions with respect to the surface of the second member, the termination plate and the portion of a balloon envelope are pressed together. In this regard, the circular heating element, when activated, is configured to cause the termination plate to heat bond with the portion of the balloon envelope.

Abstract: An aerofoil for an aircraft includes an engine, a first lift body, and a second lift body which is arranged behind the first lift body in the direction of flow of the aerofoil. The second lift body is pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil.

Abstract: A window assembly for an aircraft is provided that includes a windshield, a side window, a post, and an airflow surface. The windshield is oriented toward a front of the aircraft. The side window is oriented toward a side of the aircraft. The post is interposed between the windshield and the side window. The airflow surface is disposed on the post and on an exterior of the aircraft. The airflow surface extends along a length from a leading edge proximate the windshield to a trailing edge proximate the side window, and extends along a height between a top and a bottom. The airflow surface has a first radius of curvature proximate the leading edge and a second radius of curvature proximate the trailing edge, wherein the first radius of curvature is less than the second radius of curvature.

Abstract: An aircraft is disclosed, the aircraft having a fuselage having a centerline, and a wing extending from the fuselage and having a leading edge and a trailing edge. Additionally, the aircraft includes an engine mounted to the wing and having a rotating output shaft, and a propeller operably coupled to the output shaft and generating a rotating flow field to define a propeller wake when the propeller is rotated by the rotating output shaft. The propeller is located forward of the leading edge of the wing, so the propeller wake flows over the wing forming localized areas of effectively increased angle of attack generating a corresponding increased wing loading, with the wing having corresponding localized areas of reduced chord length to neutralize the otherwise increased wing loading. A method of countering the aerodynamic effects of propeller wake acting on a wing is also disclosed.

Abstract: Methods, apparatus, and articles of manufacture to control and monitor a folding wingtip actuation system are disclosed. An example apparatus includes a collection module to obtain flight stage information of an aircraft. The example apparatus further includes a sequence and control module to calculate a first position of a folding wingtip assembly operatively coupled to a wing of the aircraft, determine actions during a first stage and a second stage to complete in sequence to move the folding wingtip assembly, determine a status of a component of the folding wingtip assembly based on a measurement of a sensor, and control a movement of the folding wingtip assembly in accordance with the actions and based on the status.

Abstract: The invention relates to a device (12) for a non-streamlined propeller (6, 7) with blades (10) having variable pitch of a turbomachine (1), the device comprising a support (15) intended to support a blade (10) and including a cylindrical foot (17), a bearing comprising a radially internal annular section (20) and a radially external annular section (21) capable of pivoting with respect to each other, the foot (17) being mounted in said internal section (20) of the bearing. The device comprises a hub (27) mounted in the foot (17), said hub (27) including a rim (29) comprising a face (30) coming to bear on the radially internal annular section (20) of the bearing, the hub (27) and the foot (17) of the support (15) comprising complementary engagement elements (18, 28) interacting with a locking component (23).

Abstract: The invention concerns a flight control device (1) for an aircraft, comprising: —a housing (2), —a handle (4) mounted rotating relative to the housing (2) about a center of rotation (O), —a first drive shaft (31), a second drive shaft (32) and a third drive shaft (33), the drive shafts (31-33) being mounted rotating relative to the housing (2) about a same axis of rotation (X), —a first connecting part (34) mounted pivoting on the first shaft (31) about a first axis of rotation (A1), and on the handle (4) about a fourth axis of rotation (B1), —a second connecting part (35) mounted pivoting on the second shaft (32) about a second axis of rotation (A2), and on the handle (4) about a fifth axis of rotation (B2), —a third connecting part (36) mounted pivoting on the third shaft (33) about a third axis of rotation (A3), and on the handle (4) about a sixth axis of rotation (B3), the first axis of rotation (A1), the second axis of rotation (A2) and the third axis of rotation (A3) intersecting at the center of rotati

Abstract: A landing gear lock assembly includes a first lock link, and a second lock link, a first end of the second lock link being rotatably coupled to the second end of the first lock link so that the first and second lock links unfold relative to each other in a first rotation direction. A toggle lock mechanism has a crank link and a toggle link rotatably coupled to each other, the toggle link being rotatably coupled to the second lock link, and the crank link being rotatably coupled to the first lock link so that the toggle link rotates relative to the second lock link, in a direction opposite the first rotation direction, to rotate the second lock link to a fully extended position relative to the first lock link. Rotation of the toggle link mechanically locks the second lock link in the fully extended position.

Abstract: Systems and methods for uplock systems are provided. An uplock system may comprise a body, a hook having an opening defining at least a first surface and a second surface, the hook being rotationally engaged with the body, a first biasing member configured to bias the hook in a first rotational direction relative to the body, and a cam in operable communication with the hook and the body such that the hook has at least a first stable position and a second stable position relative to the body when biased in the first rotational direction.

Abstract: A cockpit control system and method for efficiently controlling ground travel in an aircraft equipped with an engine-free electric taxi system are provided. The cockpit control system is configured with a display that provides a maximum amount of information during aircraft ground movement with a minimal amount of input from and distraction to pilots or cockpit crew to facilitate essentially hands free operation and control of aircraft ground travel. System test and drive procedures ensure safe aircraft ground travel with the engine-free electric taxi system. Constant pilot hand or other input is not required to achieve safe and maximally efficient aircraft ground travel powered by the aircraft's engine-free electric taxi system or, under selected defined conditions, by the aircraft's engines to achieve this maximum efficiency. The system may further be designed to be uninterruptible by unauthorized persons.

Abstract: A system for determining a deceleration rate of an aircraft, in various embodiments, includes at least one component capable of transmitting a first deceleration rate. The system also includes a brake control unit coupled to the at least one component and having a brake controller that is configured to receive the first deceleration rate from the at least one component and to determine a likely accurate deceleration rate based on the first deceleration rate, a second deceleration rate and a hierarchy of sources of deceleration rates.

Abstract: The runway state determined on the ground by an aircraft and provided to the aircraft on approach does not make it possible to account for possible degradation of the runway occurring since the previous determination of that runway state. Updating of this runway state on the basis of a simple comparison between a desired deceleration and an observed deceleration resulting from a degraded runway is not satisfactory either. The disclosure herein thus provides for obtaining a local stopping distance according to a local runway state characterizing a runway zone on which the aircraft is in movement at the time of the landing, this local stopping distance being estimated based on local measurements made in the aircraft; obtaining a reference stopping distance according to a reference runway state; then comparing these two distances with each other to determine whether the local runway state is more degraded than the reference runway state.

Abstract: Systems, methods, and computer program products for directional force weighting of an active vibration control system involve arranging a plurality of force generators in an array, identifying individual component forces corresponding to force outputs of each of the plurality of force generators, determining a combination of the individual component forces that will produce a desired total force vector, and adjusting the outputs of each of the plurality of force generators such that the combination of the individual component forces are at least substantially similar to the desired force vector.

Abstract: A propulsion system for a vehicle includes a supporting structure and a plurality of propellers carried by the supporting structure. Each propeller is associated to an electric motor with a toroid geometry, having an annular rotor rotatable within an annular stator and defining therewithin a central aperture. The blades of the propeller, which are carried by the rotor, extend to the central aperture.

Abstract: While an aircraft is mid-flight, a braking start point associated with a stoppable rotor is calculated where the stoppable rotor includes a first and second blade and the stoppable rotor is configured to rotate about a substantially vertical axis. A process to stop the stoppable rotor is started, while the aircraft is mid-flight, when the stoppable rotor reaches the braking start point, where the stoppable rotor is stopped with the first blade pointing forward and the second blade pointing backward.

Abstract: A hybrid VTOL/high speed aircraft may comprise systems and functions for in flight configuration changes from high lift helicopter or VTOL mode to fixed or swing-wing high speed aircraft mode to accommodate a variety of functions or missions.

Abstract: The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

Abstract: A rotor blade spar for use in a rotor blade is provided comprising a housing defining an interior and having an open end. An end cap is affixed to and sealed on the open end to seal the interior from an exterior outside of the housing. The end cap includes a first port and a second port fluidly coupling the interior to the exterior. A port sealing system closes the first and second ports. The first port is connectable to an external device configured to generate a pressure differential between the interior and the exterior sufficient to create an airflow through the first and second ports which removes a liquid disposed in the housing through one of the first and second ports.

Abstract: A tri-wing aircraft includes a fuselage having a longitudinally extending fuselage axis. Three wings extend generally radially outwardly from the fuselage axis and are circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals. The wings have airfoil cross-sections including first and second surfaces having chordwise channels therebetween. A distributed propulsion system includes a plurality of propulsion assemblies. Each propulsion assembly includes a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings. At least two variable thrust cross-flow fans are disposed within the chordwise channels of each of the wings. A flight control system is operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.

Abstract: A multi-mode unmanned aerial vehicle includes an elongated fuselage, a right and left fixed wing extending from a respective right and left side of the elongated fuselage, a right and left tilt wing attached at a first side to a free end of the respective right and left fixed wing, a right and left duct attached to a second side of the respective right and left tilt wing, a right and left winglet attached to the respective right and left duct opposite to the right and left tilt wing, a tilt tail located within a curved guide slot at a rear end of the elongated fuselage, a rear duct attached to the tilt tail, a tilting mechanism, and an integrated autonomous flight control system.

Abstract: A tailsitter aircraft includes one or more rotatable wings. The tailsitter aircraft optionally includes a fuselage from which wing supports extend. Each rotatable wing optionally includes a rotatable wing section having an inboard portion proximate to the fuselage, and an outboard portion distal from the fuselage. The rotatable wing section may be rotatably attached to the wing support and configured to rotate between a vertical flight configuration in which the inboard portion is positioned on an opposing side of the wing support relative to the outboard portion, and a horizontal flight configuration different from the vertical flight configuration. The wings may be rotated during flight to transition between horizontal and vertical flight configurations, and they may be rotated about multiple axes.

Abstract: One example includes a dual-aircraft system. The system includes a glider aircraft configured to perform at least one mission objective in a gliding-flight mode during a mission objective stage. The system also includes an unmanned singlecopter configured to couple to the glider aircraft via a mechanical linkage to provide propulsion for the glider aircraft during a takeoff and delivery stage. The unmanned singlecopter can be further configured to decouple from the glider aircraft during a detach stage in response to achieving at least one of a predetermined altitude and a predetermined geographic location to provide the gliding-flight mode associated with the glider aircraft, such that the glider aircraft subsequently enters the mission objective stage.

Abstract: A truss for a flying vehicle supports a pair of wings in a manner which facilitates pivoting of the wings between a deployed configuration and a retracted configuration. The truss includes parallel top and bottom plates with the gap therebetween. The wings have wing brackets affixed thereto with the wing brackets pivotably supported by hinge assemblies to the top plate and bottom plate of the truss. Latch assemblies can be selectively actuated to secure the wing brackets and associated wings to the truss in either the deployed configuration or the retracted configuration, so that loads between the wings and the truss are primarily carried through the latch assemblies rather than through the hinge assemblies. A hinge position on the truss and on the wing brackets is selected to maximize wing length tip to tip while minimizing an outline required for the vehicle when the wings are fully retracted.

Abstract: The disclosure herein includes a drone assembly, including: a drone; a screen; and a strut that may have a first portion and a second portion, and a strut having a first portion coupled to the drone and a second portion coupled to the screen.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that includes a frame that provides both structural support for the UAV and protection for foreign objects that may come into contact with the UAV. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV may also include one or more pushing motor and propeller assemblies that are oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, the pushing motor(s) may be engaged and the pushing propeller(s) will aid in the horizontal propulsion of the UAV.

Abstract: In some embodiments, systems and methods are provided to enable package delivery and interaction with customers. Some embodiments comprise unmanned aircraft system (UAS), comprising: a crane system comprising a first spool system and a crane motor, the first spool system comprises a first cord that is extended and retracted; a retractable interface system cooperated with the first cord; a package holder configured to hold a first package to be delivered by the UAS at a delivery location; a control circuit coupled with the crane motor to control the crane motor, and to activate the crane motor to extend the first cord and lower the retractable interface system while the UAS is maintained in flight at least at a threshold height; wherein the retractable interface system comprises an input interface to receive input from a customer at the delivery location.

Abstract: An anti-rattling restraint device and system for pallets in the cargo hold of an aircraft comprising a frame body with an upper side, lateral sides, a first and a second slot sets positioned on said lateral sides, a first and a second shaft, configured to slide along the first and second slot sets respectively, a threaded stud, a lever, comprising a first end, a second end and a lever slot substantially positioned on the second end of the lever, and lock positioned on the upper side of the frame body, wherein the threaded stud is connected to the second shaft, and further connected to the frame body by the lock, and the lever is connected to the frame body by the first and second shafts, and further connected to the threaded stud by the second shaft.

Abstract: A lift apparatus for transporting objects between compartments of an aircraft through an aperture in a floor structure separating the compartments and an aircraft in which such lift apparatus is mounted. The lift apparatus includes a conveyor with a retaining portion to selectively retain and release objects to be transported, a guide to which the conveyor is mounted to be linearly movable along a predetermined path of motion defined by the guide, and a moving mechanism for driving the conveyor to linearly move along the predetermined path of motion. The retaining portion and a closing portion of the conveyor are along the path of motion, and the lift apparatus mounts in an aircraft with the path of motion extending through the aperture. The conveyor is selectively movable along the predetermined path of motion between positions.

Abstract: A galley system includes a galley compartment defining a cavity. The galley compartment has a door that allows access to the cavity. A galley cart is positionable in the cavity of the galley compartment that has a first opening and a second opening. An air supply and return system is coupled in flow communication with the first opening of the galley cart and the second opening of the galley compartment. A space is defined about the galley cart when the galley cart is positioned in the cavity. The space provides flow communication between the second opening of the galley cart and the second opening of the galley compartment.

Abstract: An aircraft interior configuration includes a first passageway extending along a longitudinal axis of a fuselage of the aircraft and a second passageway extending along the longitudinal axis. A transitional region is disposed between the first passageway and the second passageway. The transitional region extends perpendicularly to the longitudinal axis, between starboard and port sides of the aircraft. The transitional region is configurable from at least a first configuration to at least a second configuration.

Abstract: In an illustrative embodiment, an aircraft seatback pocket spring provides a pre-loaded spring force for holding the pocket closed. The pocket spring may include a length of a wire extending between inner surfaces of frame members on either side of the seat and forming an upper edge of the pocket. Second lengths of wire may extend from ends of the first length of wire in a vertical direction to form side edges of the seatback pocket. Coils may be formed at each end of the second lengths of wire and may be mounted to receiving elements provided on inner surfaces of the frame members. Extension members extending from the coils may contact a contact point on the same or proximate frame members to maintain the pre-loaded spring force on the coils.

Abstract: A crew attendant seat (CAS) positioned within a wall of an aircraft cabin includes a frame defining a periphery of the CAS. A seat portion is positioned within the frame that includes a seat bottom connected to a seatback by a hinge mechanism in which the seat bottom rotates between stowed and deployed positions. A spring member is mounted at one end to the frame and at another end to an aperture on the hinge mechanism, which causes the seat bottom to move to the stowed or deployed position based on relative positioning between the aperture and pivot points for the spring member and hinge mechanism. A harness includes at least one shoulder strap and lap belt coupled together by a buckle. A storage area retains the lap belt and the buckle within the frame when the seat bottom is in the stowed position.