Abstract: An autonomous underwater system for environmental monitoring including a multidisciplinary underwater station including onboard instrumentation, at least one autonomous modular underwater vehicle movable inside an area to be monitored along an assigned route, and at least one external instrumental modulus which can be connected to the vehicle, wherein the multidisciplinary underwater station includes a docking area, an interface system, an equipping system for supplying the vehicle with instrumental moduli, and a management system.

Abstract: A marine engine for propelling a watercraft has a drive unit adapted to be pivotally connected about a steering axis to the watercraft, and a steering position sensing system. The steering position sensing system has a magnet housing operatively connected to the drive unit and having an arcuate portion, a magnet disposed in the magnet housing, a sensor housing adapted to be operatively connected to the watercraft and a sensor disposed in the sensor housing. The magnet housing and the magnet are pivotable about the steering axis with the drive unit and relative to the sensor housing. The arcuate portion of the magnet housing is spaced from the sensor housing. The sensor senses a magnetic field of the magnet to determine an angular position of the drive unit relative to the watercraft. A bracket assembly for mounting an outboard engine to a watercraft is also disclosed.

Abstract: The invention relates to a boat with an electric drive that comprises electric components, especially an electric motor and an electric storage unit. The components are interconnected via an electric grid. At least one of the components is connected to the grid by means of a first connection means, the first connection means comprising first connection means main contacts for connecting the at least one component to the grid, and a second connection means being provided for connecting the electric storage unit to or disconnecting it from the grid. According to the invention, the first connection means comprises at least one pair of auxiliary contacts for connecting the at least one component to a monitoring line and said monitoring line is operatively connected to the second connection means.

Abstract: An acceleration control system for a marine vessel includes an actual propulsion power detector, a setting controller configured or programmed to set final target propulsion power of the marine vessel, and a controller. The controller is configured or programmed to set target propulsion power of the marine vessel at an initial time to an initial target propulsion power, to change the target propulsion power of the marine vessel based on an actual propulsion power of the marine vessel and the initial target propulsion power, and to control a propulsion device such that the actual propulsion power of the marine vessel gets closer to the final target propulsion power.

Abstract: A personal watercraft body comprises a recess configured to receive similarly shaped cassettes. A first cassette may be motorized to propel the body relative to a body of water. A second cassette may be non-motorized and may include a storage space therein for storing personal items. An insert may be disposed between the cassettes and the recess to orient and fit the cassettes within the body.

Abstract: A marine transmission located within drive housing includes a torque transmitting gear set and a clutch mechanism. The torque transmitting gear set includes top and bottom bevel gears and opposing side idler bevel gears mounted to a pinion shaft. The pinion shaft is mounted on a carrier and the clutch mechanism engages the carrier to rotate with the input shaft to drive the output shaft in the forward direction and engages the carrier to a reaction plate fixed to the drive housing to drive the output shaft in the reverse direction.

Abstract: A marine vessel electronic display system includes a first display station that can include a mode selector for permitting selection of a first mode of operation and a processing system causing displays in the first display station to present information related to the selected first mode of operation. The marine vessel electronic display system may include a second display station that can include a mode selector for permitting a user to select a second mode of operation different from the first mode of operation and a processing system causing a display in the second display station to present information related to the selected second mode of operation.

Abstract: A drain for expelling fluids from an interior of an aircraft to an exterior of the aircraft, the drain including a drain tube disposed at the interior of the aircraft having a first end disposed in fluid communication with an aircraft equipment to be drained and an opposite second end, wherein the drain tube terminates at the second end at a location within the interior of the aircraft, a seal which extends between the second end of the drain tube and an outer skin of the aircraft, delimiting a drainage cavity, and a drainage pathway extending from the cavity through the outer skin to the exterior of the aircraft.

Abstract: The present disclosure relates to a wing. More specifically, aspects of the invention relate to a variable shaped wing movable incrementally between a neutral configuration and a deformed configuration, wherein the wing takes a reflexed camber aerofoil section shape in the deformed configuration. The wing includes a first aerofoil segment and a second aerofoil segment having ends connected or fixed to one another at opposing neutral leading and trailing edges and spaced apart from one another along their lengths across a neutral mean camber line extending between the neutral leading and trailing edges to form a neutral aerofoil section of the wing. One or more actuators deform the wing between the neutral aerofoil section and a reflexed camber aerofoil section, with the first and second aerofoil segments being resilient to bias the wing towards an initial at rest aerofoil section.

Abstract: Aircraft fuel tank access door systems and methods incorporating one or more of an outer fuel tank access door completely encapsulated by a dielectric material and an inner fuel tank access door comprising at least one drainage feature are disclosed. These systems and methods reduce or prevent (i) fuel pooling on the inner fuel tank access door, (ii) moisture pooling between the inner and outer fuel tank access doors, and (iii) p-static build up and lightning attachment to the outer fuel tank access door to increase safety, reduce the likelihood of corrosion and ease installation of the fuel tank access door system.

Abstract: An aircraft lifting surface attached to the rear or frontal end of the aircraft fuselage with a variable sweep angle ? in an inboard part and with a constant sweep angle ?1 in an outboard part. The aircraft lifting surface can be for example a horizontal tail plane or a vertical tail plane attached to the rear end fuselage or a canard attached to the frontal end fuselage.

Abstract: The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

Abstract: A method of controlling a Counter-Rotating Open-Rotor (CROR) includes mechanically linking a pitch change system of a first rotor with a pitch change system of a second rotor and commanding a Blade Angle (Beta1 commanded) of the first rotor such that a Blade Angle (Beta2 Actual) of the second rotor is a function of the commanded Blade Angle (Beta1 commanded) to provide a linear relationship between an actual Blade angle (Beta1 Actual) and Beta1 commanded of the first rotor and a non-linear relationship between Beta2 Actual and Beta1 commanded.

Abstract: A piloting system having a control stick configured to control the aircraft with respect to its three piloting axes, namely the pitch axis, the roll axis and the yaw axis, and an auxiliary control device configured to automatically control the aircraft during one of the following phases: a landing phase and a takeoff phase. The auxiliary control device automatically controls the aircraft with respect to at least one of the piloting axes, and the other piloting axes, which are not controlled automatically by the auxiliary control device, then being controlled manually by a pilot with the aid of the control stick.

Abstract: A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators.

Abstract: An aircraft landing gear comprising an axle (3) intended to receive a wheel (4) comprising a rim (6) mounted to rotate on the axle (3) by means of at least one rolling bearing (8). The rolling bearing (8) comprises an inner ring (11) mounted around the axle (3) and an outer ring (12) rotationally secured to the rim (6) of the wheel (4). The landing gear further comprising a measurement device (21) intended to perform measurements of at least one operating parameter of the landing gear. The measurement device (21) is incorporated in the rolling bearing (8) by being secured to one of the inner or outer rings of the rolling bearing (8).

Abstract: An aircraft landing gear arrangement comprises a nose landing gear assembly and at least one main landing gear assembly. The nose landing gear assembly has a nose landing gear wheel with a high energy brake apparatus therein. The main landing gear assembly has a main landing gear wheel with a high energy brake apparatus therein and a main landing gear wheel with a motor therein. The motor is used for driving the main landing wheel during taxiing of the aircraft.

Abstract: A swashplate apparatus is provided and includes a first swashplate including outer and inner bodies and an intermediate portion defining a major groove between the outer and inner bodies, a second swashplate disposable in the major groove to be rotatable relative to the first swashplate, the second swashplate including an interior facing surface radially separated from the inner body to define a minor groove and defining a recess in which the rod end is disposable, a connector disposable in the recess to pivotably couple the rod end to the second swashplate and a plate element disposable in the minor groove and affixable to the interior facing surface of the second swashplate and the connector.

Abstract: A blade attachment (1, 20) for a bearingless main rotor of a helicopter with an airfoil blade (2), a flexbeam (3, 21) including a flexbeam body (16, 17) and a flexbeam head (13) at an end of the flexbeam body (16, 17). A control cuff (4, 22) encloses and extends along at least a predominant portion of the flexbeam (3, 21). A separable junction arrangement between the flexbeam head (13), the control cuff (4, 22) and the root end of the airfoil blade (2) is mechanical with removable fasteners. The removable fasteners comprise a main bolt (7) and at least one supporting bolt (8).

Abstract: Systems and methods provide for a guided lift system utilized for maneuvering payloads. According to aspects of the disclosure, a guided lift system may include a lift unit attached to a payload, at least two control tethers attached to the lift unit, and at least two control units fixed in positions and capable of adjusting the lengths of the control tethers. Coordinated length adjustments of the control tethers pulls the lift unit and payload in a desired direction to a desired delivery location.

Abstract: Embodiments described herein may relate to systems and methods for navigating to a supply request. An alert device may be controlled to issue alerts to draw the attention of bystanders to associated supplies for a situation. An illustrative method involves (a) receiving, by a computing system, a transmission indicating a situation at a designated location; (b) the computing system determining an approximate target area associated with the designated location; (c) the computing system making a determination that an alert device is located within the approximate target area; and (d) in response to the determination that the alert device is located within the approximate target area, the computing system executing instructions to activate at least one alert on the alert device indicating the situation and the designated location of the situation.

Abstract: A system for deploying loads out of an aircraft comprises an aerial delivery parachute with an aerial-delivery parachute line and an activation means for placing the aerial delivery parachute in an enveloping flow past the aircraft. Within the aircraft a receiving device can be positioned that receives a tractive force acting on the aerial-delivery parachute line, which tractive force has been determined by a force measuring device and has been transmitted by way of a transmitting device. With the knowledge of the tractive force it is possible both to implement emergency release and to assess whether an aerial delivery parachute has correctly deployed in the flow enveloping the aircraft.

Abstract: A system and method for determining length of load sling assembly in an aircraft, includes receiving, with a processor, information via one or more sensors regarding a load length during a delivery and descent state, the load length comprising length of a load sling assembly and a load height; controlling, with the processor, a minimum altitude of operation of the aircraft that ensures that the load does not touch the ground or obstacles during one or more of a flight plan, during decent, or during delivery; determining, with the processor, when a load has touched a ground in response to the receiving of the load length information; and releasing, with the processor, the load from the load sling assembly when the processor determines that the load has touched the ground.

Abstract: A payload mount adapter assembly for use with an aircraft is disclosed. The payload mount adapter assembly includes, but is not limited to an upper section that is configured for mounting to the aircraft and a lower section that is configured to receive a payload. The lower section is releasably engaged with the upper section such that the lower section is substantially unadjustable with respect to the upper section when the lower section is in a fixed state and the lower section is substantially adjustable with respect to the upper section when the lower section is in a released state.

Abstract: Embodiments of the present disclosure generally provide a grey water interface valve liquid level sensor system. The liquid level sensor system may deliver information about the water level and the water movement that occurs in a water reservoir. A control unit may then activate a valve to open so that the water can be removed via vacuum.

Abstract: A seat arrangement of a passenger cabin includes at least two seat groups. The at least two seat groups are arranged consecutively between two passenger aisles running parallel to a longitudinal direction of the passenger cabin and each have two outer seat units and just one central seat unit. The seat units are set in a seating configuration. A central seat unit of at least one of the at least two seat groups is arranged offset with respect to at least one of the outer seat units of the same seat group in the longitudinal direction of the passenger cabin, as a result of which each seat unit has obstacle-free access to at least one cabin aisle.

Abstract: A storage assembly includes a housing with an opening manifold on an outer surface of the housing. The opening manifold is capable of receiving a cord. A first end of the cord is connected to an electrical outlet disposed within the housing. The opening manifold includes a first aperture and a second aperture. The first aperture extends across a first plane. The second aperture extends across a second plane positioned substantially orthogonal to the first plane.

Abstract: A seat leg assembly for a passenger seat includes a brace member to extend from a front end of a base frame of the passenger seat to a rear floor fitting; a front leg to extend from a front floor fitting to the brace member and connected to the brace member; a rear leg portion extending from a rear end of the base frame to the brace member; and a first joint structure connecting the rear leg portion to the brace member.

Abstract: A cooling system for an aircraft includes a first cooling circuit having a first evaporator and a second evaporator, and a second cooling circuit having a third evaporator and a fourth evaporator. One of the first and second cooling circuits includes a first set of valves arranged to direct refrigerant through a first cooling sub-circuit, a second cooling sub-circuit, or both the first and second cooling sub-circuits based on ambient conditions. Two of the evaporators are installed on a first side of the aircraft, and the other two of the four evaporators are installed on a second side of the aircraft opposite the first side, and the first and second cooling circuits reject heat, via a heat exchanger, from their respective cooling circuit to air passing into an engine of the aircraft.

Abstract: An inflatable life raft system for an aircraft includes a window coupled to a fuselage portion of the aircraft. A mechanism is used to selectively detach the window from the fuselage. An inflatable life raft is deployable to the exterior of the aircraft upon detachment of the window from the aircraft.

Abstract: A fuel tank or bladder-free fuel tank having a reservoir on its inside area, limited to an outside area by a double-walled structure. The double-walled structure has an outer wall and an inner wall. A rib structure includes at least one rib extending inwardly into the inside area of the bladder-free fuel tank from the double-walled structure.

Abstract: A cooling system for a fuel tank of an aircraft includes a temperature sensor, a cooling system, and a control module. The temperature sensor detects a fuel temperature within the fuel tank. The cooling system maintains the fuel temperature below a control temperature. The phase change cooling system includes a heat exchanger. A cooling fluid flows through the heat exchanger and is in thermal communication with a surface of the fuel tank. The control module is in signal communication with the temperature sensor and the cooling system. The control module includes control logic for monitoring the temperature sensor, determining if the fuel temperature is above the control temperature, and generating an activation signal.

Abstract: When flights meet disaster in the mid-air, the cause of the mishap is unknown immediately. Teams are dispatched in difficult conditions to retrieve the flight data recorder (FDR) also known as black box. Until the black box is found, the exact cause of the crash cannot be determined. Sometimes it may take years to find the black box. For example, Air France flight 447 crashed into the Atlantic Ocean on Jun. 1, 2009. The cause of the accident remained unknown mainly because the black box was missing. It was found after almost two years in May 2011. The delay in finding the flight data creates risks for future flights if the crash occurred due to a manufacturing defect in the model of the plane. The ability to reach the data without the burden and need for a physical black box has obvious benefits.

Abstract: A system and method are provided for decluttering an aircraft display. Chart data, flight data and user input data are obtained. User input data reflects pilot preferences. A modified combination of chart data and flight data is generated in response to user input data. Symbology that is graphically representative of the modified combination is displayed.

Abstract: A device is provided for assisting in the piloting of a vehicle, in particular an aircraft. The device includes a surface displaying images and a display management unit for images designed to be displayed on the display surface superimposed on a view of the outside landscape. The management unit is capable of commanding the display of piloting information images on the display surface. The management unit is capable of commanding the display, for at least one of the piloting information images, of an animation intended to attract a user's attention to that piloting information image, the animation comprising the display of an alert image and the shrinkage of the alert image.

Abstract: An exterior aircraft light unit for emitting light of a first wavelength and light of a second wavelength, different from the first wavelength is disclosed. The exterior aircraft light unit has an integrated optical structure, which in turn has a first light source configured to emit the light of the first wavelength, a second light source configured to emit the light of the second wavelength, the second light source being positioned adjacent to the first light source, and an optical element for shaping a light emission distribution of the integrated optical structure. The optical element is arranged with respect to the first light source and the second light source in such a way that it affects both the light of the first wavelength and the light of the second wavelength.

Abstract: A gimbal mechanism for a turret includes a support member and a pair of opposing yoke arms extending from the support member. The pair of opposing yoke arms define a first axis. A sphere is rotatably mounted between the opposing yoke arms for rotation about the first axis. A disk is rotatably mounted within the sphere for rotation about a second axis perpendicular to the first axis. The disk is sized for rotation within the sphere. The second axis may be offset from the first axis. An aperture is provided in the disk. The sphere includes a slot within which the aperture is moveable in response to rotation of the disk about the second axis. The aperture is movable to define a field of coverage in response to rotation of the sphere about the first axis and the disk about the second axis.

Abstract: A system and method including a processor coupled to the non-volatile memory and a non-transitory medium connected to the processor wherein the processor is configured to select one of a flight path between two points or a point of departure and frequency of departure in the flight path from the point for an aircraft, wherein the flight path has at least two phases and a flight along the flight path or a departure constitutes one cycle.

Abstract: A requirement capture device for a centralized maintenance system for aircraft is composed of a means for capturing and parametrizing the various characteristics of the centralized maintenance system. It allows the various parties to the fine tuning of the CMS system to define the data set specific to their domain in a common framework. User profiles are defined for each of the users affording them configuration possibilities specific to their domain. After validation of the parameters input, a configuration file is generated.

Abstract: Intermodal vehicles may be loaded with items and an aerial vehicle, and directed to travel to areas where demand for the items is known or anticipated. The intermodal vehicles may be coupled to locomotives, container ships, road tractors or other vehicles, and equipped with systems for loading one or more items onto the aerial vehicle, and for launching or retrieving the aerial vehicle while the intermodal vehicles are in motion. The areas where the demand is known or anticipated may be identified on any basis, including but not limited to past histories of purchases or deliveries to such areas, or events that are scheduled to occur in such areas. Additionally, intermodal vehicles may be loaded with replacement parts and/or inspection equipment, and configured to conduct repairs, servicing operations or inspections on aerial vehicles within the intermodal vehicles, while the intermodal vehicles are in motion.

Abstract: A configurable-mass rideshare dispenser for a launch vehicle (LV). In one embodiment, the rideshare dispenser includes: (1) a modular chassis having an LV mount configured to mount the modular chassis to the LV and an LV interface configured to receive a separation signal from the LV and (2) multiple internal mounts associated with the chassis and operable to mount at multiple candidate locations therein a rideshare payload, signal processing circuitry operable to provide deployment sequencing and commodities for the rideshare payload, and at least one additional mass object.

Abstract: A stackable satellite includes a satellite frame and at least one vertical pillar attached to the frame. The vertical pillar has an upper end and a lower end. The upper end is coupled to the lower end of the vertical pillar of the satellite above and the lower end is coupled to the upper end of the vertical pillar of the satellite below. The vertical pillar receives substantially all of the vertical load of the stackable satellite and any other satellites stacked above. Use of such vertical pillars removes the need for a dispenser or substantially lightens the dispenser mass to allow substantially more satellites to be carried in a payload.

Abstract: Method for producing tilled containers from parisons made from a thermoplastic material, wherein the respective parison is at least conditioned thermally and is subsequently shaped during a shaping and filling phase in a mold by the action of the pressure of the supplied filling substance into the respective container at a shaping and filling pressure, wherein, during the shaping and filling phase, the parison is guided at least temporarily through a stretching rod and/or is stretched in the axial direction, and wherein, at least at the end of the shaping and tilling phase, the respective container has an internal pressure which corresponds to the shaping and filling pressure (p2).

Abstract: One variation of a system for packaging a foodstuff includes: a ramp; a bag dispenser adjacent the ramp and dispensing a bag into a load position; a paddle pivotable about a hinge arranged above the ramp, comprising a leading edge opposite the hinge and engaging the ramp, and extensible between a retracted setting and an extended setting, the leading edge of the paddle in contact with the ramp in the retracted setting and inserted into the mouth of the bag in the extended setting; an actuator coupled to the paddle and extending the paddle between the retracted setting and the extended setting; and a conveyor advancing the a foodstuff toward the bag dispenser, foodstuff contacting a bottom surface of the paddle and pivoting the paddle about the hinge to separate an upper layer of the bag from a lower layer.

Abstract: A modified atmosphere flow-wrap system and method and components thereof are provided for packaging a food product in a reduced oxygen atmosphere in a continuous or partially-continuous process. In one aspect, the flow-wrap system includes a saturation tunnel for saturating the food products with modified gas to reduce an amount of residual oxygen therein. In another aspect, the flow-wrap system includes a flow-wrapping station with a modified gas lance that extends into film webbing used to form the food product packages to insert modified gas into the film webbing and restrict oxygen from entering the food packages.

Abstract: A robotic carton erector and method of use is provided by the present invention. The robotic apparatus has a pair of movable jaws with grippers mounted thereto. The apparatus has a rail and a pair of platforms, the platforms positioned downstream of the rail. The robotic apparatus grips and opens a carton and the carton is moved into contact with the rail to close the bottom minor flaps. The carton is moved in a first direction onto a first platform to close a first bottom major flap and in a second direction onto a second platform to close a second bottom major flap. The carton bottom is then sealed.

Abstract: A yard waste collection and carrying device is in the form of a large flat-bottomed tray open at one end, sized to receive leaves, sticks and other materials raked into the open end. Formed of a semi-rigid rubbery plastic material, the device stores a large volume of material, has a pair of opposed side handles for carrying, and is easily deformed to curve the forward end into a pouring configuration, so that the collected materials can easily be transferred into a narrower waste can. The shape of the device is such as to be compactly stackable for storing or shipping a number of the devices together.

Abstract: A receptacle, particularly a closed plastic ampoule produced in a blow molding method and filled in the mold, has a sleeve-type neck part (1) connected to a receptacle body (3) as an axial extension. The neck part forms a seat (11) for a pre-shaped insert (5) and is integrally molded in the mold onto a circumferential surface (9) of the insert (5). The circumferential surface (9) is equipped with at least one surface irregularity (21) having an enclosed base surface such that, due to the integral molding of the neck part (1) onto the circumferential surface (9) of the insert (5), a positive fit is present between the insert and the neck part (1). The fit forms a fixing element. The axial extension of the base surface of the surface irregularity (21) is only a small fraction of the axial extension of the circumferential surface (9).

Abstract: A convertible container assembly comprising a convertible container body. The container body includes angular series of conversion demarcations, defining an angular conversion section, and, optionally, at least one storage conversion demarcation, defining a storage conversion section. The angular conversion section includes a portion of a sidewall of the container body and a bottom portion of the container body. The angular conversion section toggles between an expanded configuration having a common horizontal upper rim and a compressed configuration creating a new container body support surface, angling the upper rim. The depth conversion section toggles between an expanded configuration as a container and a compressed configuration collapsing the container for storage. The conversion section can employ a single section or a series of sections, wherein the series of sections enable an accordion styled formation when collapsed.

Abstract: The invention relates to a method for manufacturing a covering structure for a cardboard package comprising a tubular body made up a cardboard material. The covering structure comprises a flat assembly of three materials: (1) a cellulosic material covered with a reactivatable barrier material over the face thereof oriented towards a safety membrane, making up a lid cardboard, (2) a laminating part arranged between said lid cardboard and the safety membrane, with a shape conjugated to the shape of the opening of the tubular body, made from paper, or paper whereof the face oriented towards said lid cardboard is coated with a material having barrier and sealing properties, and (3) a safety membrane, made up of a paper coated with at least one reactivatable barrier material on the surface thereof not oriented towards the laminating part.