Abstract: An energy storage battery basket, adapted for equipping with an electric bicycle having a crossbar frame, includes a basket body and an energy storage base. The basket body has a storage space and includes at least a handle. The energy storage base, configured with a bottom of the basket body, includes at least one rechargeable battery provided therein, at least one electric terminal socket provided at a center of one side of the energy storage base, and at least one USB charging port, at least one Type C power supply port, at least one DC2.1 charging port, and at least a power switch provided at two sides of the electrical terminal socket respectively.

Abstract: A child ride-on vehicle includes a front wheel, a rear wheel displaced in a rearward direction from the front wheel, a frame connected to the front and rear wheels, a steering mechanism configured to facilitate steering the front wheel relative to the frame, a steering interface configured to control the steering mechanism, a seat connected to the frame and configured to support a user in a driving position for interaction with the steering interface, and a rear camera. The rear camera is supported by the frame and has a viewing angle that is oriented in the rearward direction and away from a user in the driving position, and in an upward direction that is transverse to a longitudinal axis of the vehicle.

Abstract: A control device for controlling a transmission ratio between a traction means and a sprocket set rotatable about an axle may include at least two sprockets alternatively wrapped around by the traction means. At least one of the sprockets may include several independently adjustable rim segments. Adjustment of the rim segments in relation to a fixed plane may be effected by a control device in a direction substantially transverse to the plane. The control device includes at least one electrically actuatable control element, e.g., a servomotor. The at least one control element is configured to rotate with the sprockets.

Abstract: A water resistant storage assembly for a boat or other vehicle including a drawer assembly or a hinged-door assembly coupled to a cabinet, wall, or other compartment. The storage assembly may include a series of faces featuring or defining self-draining channels adapted to redirect inbound water or other fluids away from the interior storage area and towards an external wall or other external surface.

Abstract: A bimini top for a watercraft includes a bimini frame having at least one bow and at least one support leg rotatable relative to the at least one bow. The bimini frame is transformable between a retracted position and a stowed position. An actuator is operable to automatically transform the bimini frame between the retracted position and the stowed position. The actuator forms the at least one support leg.

Abstract: A mechanism positions a movable part relative to a support, between deployed and retracted configurations, with the movable part distant from the support and flush with the support, respectively. A base is attached to the support and has a central hole. A first positioning device has a first body in the central hole and a first off-centered hole relative to the central hole and a first notched wheel mechanically attached to the first body. A second positioning device has a second body in the first off-centered hole and a second off-centered hole and with a second notched wheel attached to the second body rotating when the second notched wheel is actuated. The two positioning devices are mounted fixed in translation relative to the base and position, along the two directions, an interface member of the movable part mounted in the second off-centered hole and attached to the positioning mechanism.

Abstract: A towing device for a rider on a body of water comprises a buoyant platform having at least one electric motor and a prop. A container fixed with the towing device contains a controller to power each electric motor. A wireless remote control sends wireless commands to the controller. A tow rope is fixed with the buoyant platform proximate the rear end. As such, with the rider holding the wireless remote control and engaged with a distal end of the two rope, commands from the wireless remote control are sent to the controller to control power to each electric motor. Preferably the towing device further includes a pivotable rudder that is disposed behind the prop, or a steering nozzle, and the wireless remote control has a steering control to send steering signals to the controller. Various modes of operation of the towing device are disclosed.

Abstract: A marine information integrated online monitoring buoy system comprises a buoy body. Specifically, a protection apparatus is disposed outside the buoy body. A bearing is disposed outside the buoy body, convex strips are arranged around a bearing outer ring, two floating rings are disposed outside the bearing outer ring with a certain spacing distance from the outer ring and arranged vertically, a protective cylinder is arranged between the upper and lower floating rings in a surrounding manner and is rotatable relative to the floating rings, and then a protective retaining ring is sleeved outside the protective cylinder and is rotatable relative to the protective cylinder. The longest end of a protective retainer is abutted against the bearing outer ring during rotation of the outer side of the protective retaining ring, and a friction block is disposed on the protective retainer.

Abstract: Disclosed is an autonomous vessel comprising a hydrodynamic pump that converts the energy of ocean waves into electrical power when the vessel is floating adjacent to an upper surface of an ocean, and utilizes a portion of the generated electrical power produced to charge an electrical energy storage device. The vessel may submerge itself, and then propel itself beneath the water's surface, after which it may return to the surface and resume its production of electrical energy and recharge its electrical energy storage device.

Abstract: The present invention relates to a method of manufacturing a board for sport equipment and the board for sport equipment thereof. The method comprises the steps of molding a substrate on a first mold; transferring the substrate to a second mold; and injecting a thermoplastic material into a cavity provided between at least a part of an edge side of the substrate and the second mold to form the board with a board bumper on the at least a part of the edge side of the substrate.

Abstract: A method and an unmanned surface vehicle for identifying and remediating a gas leak. The method includes detecting a first condition indicative of the gas leak with a first sensor and sensing environmental conditions near the gas leak with an environmental sensor. The method includes receiving, at a controller operatively coupled to the unmanned surface vehicle, signals representing the first condition indicative of the gas leak the environmental conditions near the gas leak. The method includes determining, by the controller and based on the first condition indicative of the gas leak and the environmental conditions near the gas leak, a navigation plan of the body of water including an ignition zone. The method includes positioning, based on the navigation plan, the unmanned surface vehicle relative to the ignition zone and discharging, by an ignition mechanism, an ignition source into the gas leak to ignite the gas leak.

Abstract: A barge-type wind turbine platform in combination with a heel tank damper includes a barge-type wind turbine platform having a keystone, two pairs of bottom beams, each including two bottom beams connected to opposite sides of the keystone, wherein the combined pairs of bottom beams define a foundation. A U-shaped ballast conduit is mounted or formed within each of the pairs of bottom beams. Each ballast conduit has ballast water therein, the ballast water extending from an outwardly extending portion of each bottom beam of each pair of bottom beams, such that a volume of air is defined between a surface of the ballast water in each outwardly extending portion and an outwardly facing wall of each outwardly extending portion, and an internal damping element is provided within each ballast conduit. A heel tank damper is defined by the ballast conduits and their respective internal damping elements.

Abstract: A launch and recovery vehicle can be towed by a water vehicle or ship. The launch and recover vehicle can ballast in order to retrieve an unmanned vehicle. The launch and recovery vehicle can deballast while holding the unmanned vehicle. The water vehicle or ship can retrieve or winch the launch and recovery vehicle onto a well deck. Additionally, the launch and recovery vehicle has wheels and can be pulled or towed onto land with a land-based vehicle, such as a truck.

Abstract: An adaptive tooling interface comprises a single motor, disposed at least partially within a housing, which is operatively in communication with a controller and where a first power output and a second power output are operatively in communication with the motor. A drive interface, comprising a external tool interface, is operatively in communication with the motor and configured to mate with and provide power to one or more external tools, which comprise a matching subsea external tool external tooling interface, via the first power output and the second power output. The adaptive tooling interface may be connected to or otherwise integrated into a subsea vehicle system comprising a subsea vehicle.

Abstract: Provided with a weight release device capable of being operated in deep sea same as the conventional weight release device without accompanying a mechanical operation at all to avoid troubles of mechanical operation occurred in the conventional weight release device. The weight release device includes a housing fixed to the underwater observation device; a thread made of thermoplastic resin; electric heater portions; a weight support plate; a locking member of the thread made of the thermoplastic resin; and a ring for hanging the weight. The thread made of the thermoplastic resin is arranged from a start point housed in the housing, arranged to pass through the first electric heater portion, locked to the locking member of the thread made of the thermoplastic resin, arranged to pass through the second electric heater portion housed in the housing, and returned to an end point housed in the housing. The ring for hanging the weight is fixed to a lower surface of the weight support plate.

Abstract: A modular hydrodynamic subsea vehicle comprises an upper section and a lower section, where the upper section comprises a first upper primary module, a second upper primary module operatively connected to the first upper primary module, and, optionally, one or more intermediate upper modules disposed in-between the first and second upper primary modules. The lower section is operatively connected to the upper section and comprises a first lower module, a second lower module operatively connected to the first lower primary module, and, optionally, one or more intermediate lower modules disposed in-between the first and second lower primary modules. The modules are capable of performing a desired set of functionality subsea.

Abstract: The invention relates to a rotor sail system (RSS) for a water vessel comprising one or more rotor sails rotatably and multiaxially tiltably coupled with the water vessel which can comprise defined propelling means. The RSS can comprise a drive flange, a defined joint, an end plate, a defined fin, a thermal management system, an array of solar cells and/or two or more superposed portions. The RSS can be configured to provide more sailing regimes, to be at least partially stowable. The RSS can comprise rotor sails of defined forms which can further be coupled with defined electrocomponents and/or mechanocomponents. The RSS can provide data transmissions. The RSS can be provided in a modular system. A rotor sail driving method and a rotor sail assembly method are proposed.

Abstract: An outboard motor includes a first housing, a second housing, and a steering mechanism. The steering mechanism is operable to steer the second housing around a steering axis. The steering mechanism includes a pinion gear, a first rack, and a second rack. The pinion gear is connected to the first housing or the second housing. The first rack includes first teeth and a first relief portion. The first teeth mesh with the pinion gear and are arranged side by side with each other in a first direction. The first relief portion does not mesh with the pinion gear and allows the pinion gear to idle. The first rack is movable in the first direction. The second rack includes second teeth. The second teeth mesh with the pinion gear and are arranged side by side with each other in a second direction. The second rack is movable in the second direction.

Abstract: An outboard motor includes a first housing, a second housing, a propeller shaft, and a steering mechanism. The steering mechanism includes a first pinion gear, a second pinion gear, a first rack, and a second rack. The first pinion gear is connected to the first housing or the second housing. The second pinion gear is connected to the first pinion gear. The first rack includes first teeth. The first teeth mesh with the first pinion gear and are arranged side by side with each other in a first direction. The first rack is movable in the first direction. The second rack includes second teeth. The second teeth mesh with the second pinion gear and are arranged side by side with each other in a second direction. The second teeth have a smaller module than the plurality of first teeth. The second rack is movable in the second direction.

Abstract: A watercraft propulsion device includes: a motor driving a propulsion unit; a battery supplying electric power to the motor; and a gas flow passage including one end communicating with the battery and another end communicating with a region that is outside a watercraft hull and is located lower than an upper end of a shell panel disposed at an edge of the watercraft hull, the gas flow passage exhausting a gas ejected from the battery from the other end to outside of the watercraft hull.

Abstract: A power supply and cooling system for a floating structure having a tank, includes a supply circuit having at least one compression device, the supply circuit being configured to supply gas to a gas-consuming device, and a cooling circuit having a heat exchanger configured to participate in managing the internal pressure of the tank, the cooling circuit being connected to the supply circuit on either side of the compression device. The compression device includes two compression stages, and the power supply and cooling system includes a control device configured to connect the compression stages in series or in parallel.

Abstract: A container for a flight craft such as a gas balloon is provided. Part of the walls of the container is constituted of three separated plates. The first plate has one or more holes that causes gas to flow in and out of two spaces so that the pressure difference between a first space and a second space separated by the first plate is resolved but does not cause gas convection between those two spaces. As the flight craft ascends, a relationship T1<T2<T3<T4 occurs among the temperatures inside the first to a fourth space. The temperature gradient between the inside and outside of the container becomes less pronounced. Condensation is unlikely to form on any of the three plates. The first plate with the holes buffers the force that the second plate is subjected to due to a pressure difference between the inside and outside of the container.

Abstract: A line assembly for installation in an aircraft fuselage includes a first line section having a first diameter, a second line section having a second diameter, a set of first line brackets, and a set of second line brackets. The first line brackets include a first receiving space configured to hold the first line section and a first support portion for attaching the first line brackets to a fuselage structural part. The second line brackets include a second receiving space configured to hold the second line section and a second support portion for attaching the second line brackets to the first line section. The second line section includes a higher flexibility than the first line section. The second line section is attached to the first line section through a plurality of second line brackets arranged at a distance to and independent from the first line brackets.

Abstract: An aircraft wing with an array of moveably flight control surfaces is disclosed. Each flight control surface includes a trailing edge with a moveable tab attached to the flight control surface trailing edge. A flight control system coupled to a flight control surface drive system which moves the flight control surfaces; a tab drive system which moves the moveable tabs and one or more aircraft angle of attack sensors. The flight control system stores a set of angular deflections to deflect the tabs upwardly when the angle of attack reaches a threshold.

Abstract: A wing lock and deployment apparatus for an air launched vehicle includes a ball screw and driver acted on by a single actuation event. The disclosed wing lock and deployment apparatus is capable of unlocking deployable wings of an air launched vehicle, deploying deployable wings of the air launched vehicle from a stored position, and locking deployable wings of the air launched vehicle in a deployed position in sequential order with the one single actuation event.

Abstract: A wing component for an aircraft, comprising a leading edge part and a trailing edge part pivotably mounted to the leading edge part so as to pivot about a pivot axis, an actuator unit configured for moving the trailing edge part relative to the leading edge part, and a damper device configured for damping uncontrolled movement between the leading edge part and the trailing edge part. The trailing edge part comprises a first part portion and a second part portion arranged next to each other in a span direction and configured to pivot about the pivot axis individually, the damper device comprises a damping element coupled between the first part portion and the second part portion to damp relative movement of the first part portion and the second part portion.

Abstract: An aircraft wing with a moveable leading edge device mounted towards the leading edge of the wing. The leading edge device is moveable between a first configuration, a second configuration and a third configuration. In the first configuration, the leading edge device is retracted fully within the wing profile. In the second configuration, a portion of a surface of the leading edge device is extended away from the wing profile and into the oncoming airflow on the lower surface of the wing as the wing moves through the airflow to increase lift produced by the wing. In the third configuration, a portion of the surface of the leading edge device is extended away from the wing profile into the oncoming airflow over the upper surface of the wing to impair lift produced by the wing.

Abstract: An aircraft wing with a moveable leading edge device mounted towards the leading edge of the wing is disclosed. The leading edge device is moveable between a first configuration and a second configuration. In the first configuration, the leading edge device is substantially flush with the low pressure surface. In the second configuration, the surface of the leading edge device is retracted into the wing profile. The second configuration creates a void in the lower surface of the wing which modifies the airflow over the surfaces. The oncoming airflow can enter the void. In the second configuration, the leading edge device reduces the lift on the wing, acting to reduce the lift induced strain on the wing during high speed flight or to help manoeuvre the wing. The leading edge device may also be configured to move into a third configuration.

Abstract: An uplock for selectively retaining a capture pin of a movable element including a hook, a locking member, and a detector. The hook is movable between a release position and a retaining position. The locking member is movable between a locked position that immobilizes the hook and an unlocked position in which the hook is free. The detector detects whether the hook is in the retaining position and the capture pin is present in the hook. The detector includes a sensor associated with a single target which is movable between two positions The sensor emits a signal which is modified when the target passes from one of the positions to the other. The target is independently in kinematic interaction with the hook and the capture pin.

Abstract: An aircraft comprises a fuselage, a plurality of support structures coupled to the fuselage, and a first propeller and a second propeller connected to a motor and symmetrically distributed along the plurality of support structures, the first propeller configured to create a first thrust having a first horizontal force vector and the second propeller configured to create a second thrust having a second horizontal force vector. A summation of the first and second horizontal force vectors is substantially zero when the first thrust is substantially equal to the second thrust, and a first rotational axis of the first propeller and a second rotational axis of the second propeller are substantially coplanar with a vertical axis disposed between the first and second propeller. A movement of the aircraft is controlled by selectively increasing or decreasing a thrust of either the first propeller or the second propeller.

Abstract: A hybrid foldable system of wings and rotors of a flying vehicle, and a flying vehicle. The flying vehicle includes a vehicle body, two wings, wing rotating mechanisms, rotor supports, rotor support rotating mechanisms, and rotor assemblies. The wings are movably connected to the vehicle body and the wing rotating mechanisms drive the wings to rotate to expand or retract. The rotor assemblies expand to two sides of each wing, or reversely rotate to retract to inner sides of each wing. Vertical taking-off and landing and stable flight in the air of the flying vehicle can be realized. In addition, when running on the ground, the wing and the rotor assemblies can be rotationally folded and placed on the inner sides of the vehicle body, so that space is reduced, and the limit requirements of urban roads regarding the size of the vehicle are satisfied.

Abstract: A vertical take-off and landing aircraft and method which uses fixed rotors for both VTOL and forward flight operations. The rotors are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the wing. The wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight, or may have a single center wing. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.

Abstract: The present disclosure relates generally to electric aircraft, and more specifically to electric power distribution for electric aircraft. In one embodiment, an electric aircraft is disclosed, comprising: a fuselage; two wings mounted on opposite sides of the fuselage; a plurality of first electric propulsion units, arranged on both sides of the fuselage, aft of the wings during forward flight; a plurality of second electric propulsion units arranged on both sides of the fuselage, forward of the wings during forward flight; and a plurality of battery packs, each battery pack configured to power at least: a portion of one of the first electric propulsion units on one side of the fuselage, and a portion of one of the second electric propulsion units on the other side of the fuselage.

Abstract: Embodiments are described for detecting optical discrepancies associated with image capture analyzing pixels in multiple images corresponding to common points of reference in a physical environment. In an embodiment, photometric error values are averaged over time to compute the mean error at each pixel. Once the estimate of the mean error has a sufficient number of updates above a specified value, the estimate is thresholded to provide a mask of any optical discrepancies occurring in the stereo pair of images. Applications include detecting optical discrepancies in images captured for use by a visual navigation system in guiding an autonomous vehicle (e.g., an unmanned aerial vehicle).

Abstract: In some examples, a first device includes multiple fixed first cameras and a movable second camera. A processor is configured to receive, from at least one of the fixed first cameras, a plurality of first images of an airspace corresponding to an area of operation of an unmanned aerial vehicle, and detect, based at least on the first images, a candidate object approaching or within the airspace. Based on detecting the candidate object, the processor controls a movable second camera to direct a field of view of the movable second camera toward the candidate object. Based on one or more second images from the movable second camera captured at a first location and one or more third images from a third camera captured at a second location, the processor may determine that the candidate object is an object of interest and perform at least one action.

Abstract: A lavatory system includes a toilet having a front end, a back end, a top end, and a bottom end, and a tube having a first end coupled to the toilet toward the top end and a second end extending above the top end. The toilet includes a toilet bowl defined by the front end, the back end, the top end, and the bottom end, and a toilet seat coupled to the toilet bowl on the top end.

Abstract: A locking assembly of a lavatory door in an aircraft, comprising: a locking mechanism; and an occupancy indicator. The occupancy indicator is configured with a display that enables viewing of a status of the lavatory of availability or is occupancy. The position of the locking mechanism and occupancy indicator has been changed from a higher location on the lavatory door that approximates a line-of-sight from a standing position at the lavatory door to a lower location that approximates the line-of-sight from a seated position at the lavatory door. The display of the occupancy indicator is configured with a plurality of display angles to display the status comprising at least a first display angle to allow viewing from the line-of-sight in the standing position and at a second display angle to allow viewing from the line-of-sight in a seated lower position at the lavatory door.

Abstract: Examples provide a door assembly including a dual operation slide device for a sliding privacy door associated with a seat unit. The door assembly includes a sliding door movably mounted to a door support member of a seat unit. The door slides laterally between a retracted position and a deployed or partially deployed position. The dual operation slide device includes a trigger and release mechanism for switching the door assembly from a primary track system used during a normal operation mode to a secondary track system used during a backup operation mode if the primary track becomes jammed or otherwise malfunctions based on manual activation of a release lever or force applied activation. The dual operation slide device enables a user to return the sliding door to a retracted position after a failure of the primary slide units to operate in the normal operational mode.

Abstract: Described are armrests for positioning between passenger seats having a base component with a divider extending upward from an upper surface of the base component and at least one adjustable component movably coupled to the base component. In a retracted position, the adjustable component and divider are arranged to form a non-intrusive barrier between passengers' arms. In an extended position, the divider is arranged to form the non-intrusive barrier between passengers' arms, while the adjustable component is arranged to extend a width of the armrest.

Abstract: A device and method for detecting a phase transition between a liquid phase and a solid phase of a substance include a pair of electrodes, a sensing layer arranged in an electrical path between the pair of electrodes, and means for measuring a first electrical characteristic of the electrical path. The sensing layer includes a mixed ion and electron conducting composite material. The composite material has an electrical property, in particular electrical resistance, which shows a peak variation as a function of time at the phase transition, such as an onset of ice formation. Computing means process the first electrical characteristic to indicate an occurrence of the phase transition.

Abstract: In accordance with one embodiment of the present invention, an aircraft comprises a battery pack mounted external to the aircraft structure. The batteries are configured to vent directly to the environment during battery thermal runaway. In one embodiment, an aerodynamic fairing provides an aerodynamically efficient surface and weather protection during nominal flight conditions. During battery thermal runaway however, the aerodynamic fairing is configured to expose the battery to the environment.

Abstract: A propulsion assembly for an aircraft, having a turbomachine, a pylon, and a device for reacting thrust forces having a main fitting, a spreader pivoting on the main fitting and having an opening, two rods articulated to the turbomachine and to the spreader, a secondary fitting fastened beneath the pylon and having a secondary female clevis constituted of two secondary arms passed through by holes of oblong shape and aligned along a secondary axis (R2), wherein the spreader is housed in the secondary female clevis of the secondary fitting, wherein the opening is coaxial with the secondary axis (R2), and a backup connection pin inserted with a tight fit into the opening and with clearance into the holes. Also an aircraft with such a propulsion assembly.

Abstract: An assembly for an aircraft propulsion system includes an upstream cowl and a downstream cowl. The upstream cowl extends axially from a first upstream end to a first downstream end. The upstream cowl includes an inner barrel panel, an outer barrel panel, and a bulkhead. The bulkhead extends radially between and connects the inner barrel panel and the outer barrel panel at the first downstream end. The downstream cowl extends axially from a second upstream end to a second downstream end. The downstream cowl includes a cowl panel and a seal assembly. The seal assembly includes a seal frame and a seal member. The seal frame is mounted to the bulkhead. The seal member is mounted to the cowl panel. The seal member includes a first radial portion projecting away from the cowl panel. The first radial portion is located at the second upstream end.

Abstract: An acoustic treatment panel including acoustic absorption cells each comprising a bottom wall, a porous inlet wall, an enclosure extending in an axial direction between the bottom wall and the inlet wall, and a first acoustic horn extending inside the enclosure between a first opening and a second opening that is smaller than said first opening, the first opening facing said inlet wall. Each cell comprises a second horn extending inside the enclosure in the first axial direction between a first opening of the second horn and a second opening of the second horn that is smaller than said first opening.

Abstract: A flexible diaphragm coupler includes a flange having a central support and a flange element extending radially outwardly from the central support. The flange element includes a rim portion having an axially facing surface. The axially facing surface includes a plurality of interlock elements. A diaphragm member is disposed between the first flange and the second flange. The diaphragm member includes a diaphragm element. The diaphragm element includes a central support element and a disc member extending radially outwardly from the central support element. The disc member includes a rim element having an axially facing surface portion including a plurality of interlock members that connect with the plurality of interlock elements.

Abstract: A drive mechanism for use with an electric motor and a clutch mechanism includes a rotor shaft, a disconnect shaft, a disconnect mechanism, at least one damper element, and a part of a clutch. The rotor shaft and disconnect shaft have a longitudinal axis A. The disconnect shaft transmits torque between the rotor shaft and the clutch mechanism. The disconnect shaft comprises the part of the clutch and a shaft element. The disconnect mechanism is configured to move the disconnect shaft between an engaged position in which the part of the clutch is engaged with the clutch mechanism and a disengaged position in which the part of the clutch is not engaged with the clutch mechanism. The at least one damper element is configured to absorb at least part of any kinetic energy introduced into the disconnect shaft due to movement of the disconnect shaft.

Abstract: A drive mechanism for use with an electric motor and a clutch mechanism The drive mechanism comprises a rotor shaft, a disconnect shaft, a disconnect mechanism, at least one damper element, a part of the clutch, and a lubrication system. The rotor shaft and disconnect shaft have a longitudinal axis A. The disconnect shaft transmits torque between the rotor shaft and the clutch mechanism. The disconnect shaft comprises the part of the clutch and a shaft element. The disconnect mechanism is configured to move the disconnect shaft between an engaged position in which the part of the clutch is engaged with the clutch mechanism and a disengaged position in which the part of the clutch is not engaged with the clutch mechanism. The at least one damper element is configured to absorb at least part of any kinetic energy introduced into the disconnect shaft.

Abstract: A method of controlling an inerting system of an aircraft is disclosed. The inerting system feeds inert gas into a fuel tank of the aircraft, the method includes: a) obtaining a location of the aircraft, the location comprising a current location or an expected future location; b) assessing an environmental impact of releasing of fuel vapour at the location obtained in step a); and c) controlling the inerting system based on the assessment of step b).

Abstract: A method for providing inert gas to a protected space. The method includes: providing air having a pressure greater than or equal to 2 atmospheres absolute pressure to a chemical inert gas generator; producing an inert gas in the chemical inert gas generator; providing the inert gas to a condenser at an elevated pressure; reducing the water content of the inert gas in the condenser; and providing the dried inert gas to a protected space.

Abstract: A wireless flight recordation system is disclosed for collecting black-box data of an aerial platform. The wireless flight recordation system includes one or more black-box data collectors for collecting black-box data that is recorded by one or more flight recorders of the aerial platform. The wireless flight recordation system also includes at least one data transmission interface connectable to the black-box data collectors for receiving the black-box data and establishing a wireless communication link with a wireless data communication network which is capable of providing data communication services to the aerial platform during flight. The data transmission interface transmits the black-box data or at least a parts thereof, via the wireless data communication network, to a receiver remote from the aerial platform. In some implementations the black-box data collectors are adapted to interface (e.g.