Abstract: An enhanced system for controlling boat fenders wherein, based on a tidal range chart, a motion function is calculated for one or more boat fenders, which is loaded into a fender controller so that fenders are lifted or lowered to protect a boat over a period of time as boat rises and falls with water levels when stationed at a dock.

Abstract: A drone equipped with a camera, a wireless communication module, an acoustic sensor, a GPS receiver, software and collapsible floatation device patrols above swimmers. The camera and acoustic sensor capture the video and audio of the swimmers. The information is either streamed to a command center or processed by the onboard software. With audio and video analysis capabilities, software is used to detect a swimmer in distress (SID). Alternatively the information is streamed to lifeguard or volunteers all over the world to spot SID. Another detection method is to let swimmer wear a wearable emergency notification device, which sends wireless signals comprising GPS location data. A SID presses a button to indicate rescue request and the drones fly over by GPS signal guidance. Solar power is used as the optional power source of the drones, which would allow the to sustain operation for a prolonged period of time.

Abstract: A survival craft comprises a hull (10) formed from inflatable members (12, 13) and mounting a powered propulsion system (18, 19) for the survival craft. A superstructure (11) is mounted on the hull and formed from inflatable members (25, 26, 29a-29i) and a flexible roof (28) supported by the inflatable members (25, 26, 29a-29i). The superstructure provides the hull (10) with increased longitudinal rigidity that reduces the tendency of the hull (10) to bow longitudinally when the propulsion system (18, 19) is operating. The survival craft forms part of a marine escape system with the survival craft deflated and packed in a container including an inflation system for the survival craft. The system has a deployment system for mounting on a marine structure and carrying the container with the deployment system transferring the container from the structure to the water where the inflation system inflates the survival craft for access by persons.

Abstract: A person-in-the-water rescue and retrieval system includes a net assembly having a pair of laterally spaced apart side ropes and a plurality of net portions, each net portion being constructed of a material that floats, extends laterally between the side ropes, and is spaced apart longitudinally from an adjacent net portion. The system includes a deployment capsule defining an interior space configured to selectively receive the net assembly therein. A launching device includes a framework configured to receive the deployment member. A first compressed air canister is in fluid communication with the launching device and the deployment member and configured to apply force to the deployment member when actuated that is sufficient to propel the deployment member from the launching device. The launching device may be boat mounted or configured as a handheld device such as in the form of a rifle.

Abstract: A propeller guard assembly for enclosing the propeller blades of a marine propeller to prevent them from striking marine animals. The propeller guard assembly comprises a front cage portion hingedly attached to a back cage portion. The front cage portion and back cage portion are each defined by a plurality of bars extending radially from a center area to a circumferential bar. The front cage portion and back cage portion are hingedly coupled by a hinge, thereby enabling them to swing between an open position and a closed position. When in the closed position, the front cage portion and back cage portion can be selectively fastened together by a fastening clip.

Abstract: The present invention is directed an adjustable foot rest system for a kayak comprising a bulkhead member adapted for synchable non-slip support of the feet and on the fly user positioning. A mounting sleeve in the bow wall and/or runners are provided with the bulkhead resting inside the sleeve and/or runners by friction alone. Flexible straps equipped with strap adjusters are connected to the bulkhead, through guide anchors and secured to anchors affixed to the inside hull of the kayak near the seat. A bungee cord is threaded through an anchor disposed near the end of the bow and connected on each side to the bulkhead cross member, whereby the bulkhead position as selected by the user remains in place until the user selects a new position.

Abstract: A human-powered underwater propulsor for user's moving in water mainly has a power generating module provided within a receiving space inside a waterproof airbag, and the power generating module is coupled to a propulsion unit. The receiving space is formed with an opening end provided with a waterproof ring to be worn by user in such a manner that the receiving space is hermetically sealed to prevent water from entering the receiving space during diving. When user pedals by stepping on two pedals of the power generating module, the power generating module is actuated to cause the flapping of the propulsion unit. Hence, the human-powered underwater propulsor allows user to exercise his feet in the air to reduce drag in diving so that user can moves more easily in the water.

Abstract: A marine propulsion device includes an engine, a cylinder cooling pathway through which a cooling water passes, a water pump, an electromagnetic valve, a water pressure sensor, a water temperature sensor, and a controller. The engine includes a cylinder. The cylinder cooling pathway is disposed in an area surrounding the cylinder. The water pump supplies the cooling water to the cylinder cooling pathway from outside. The electromagnetic valve restricts a flow of the cooling pathway in the cylinder cooling pathway. The water pressure sensor detects a water pressure of the cooling water in the cylinder cooling pathway. The water temperature sensor detects a water temperature of the cooling water in the cylinder cooling pathway. The controller is configured or programmed to control an opening degree of the electromagnetic valve based on a detection value of the water pressure sensor and a detection value of the water temperature sensor.

Abstract: Provided is a technology that facilitates a calibrating operation. A ship steering system for outdrive device includes an outdrive device, a control device that provides an instruction about a turning direction of the outdrive device, and a ship steering lever that instructs the control device about a traveling direction of a hull, and is provided with a monitor capable of displaying an image for matching an actual traveling direction with the traveling direction of the hull according to the instruction from the ship steering lever. The monitor shows the direction in which the ship steering lever is tipped, and indicates that the operation is proper if the direction in which the ship steering lever is tipped corresponds to a pre-set direction.

Abstract: The present invention includes: a ballast water treatment line (4) having a treatment target water suction pump (1), a filter (2) that filters treatment target water, and a ballast tank (3) that stores filtered treatment water; a treatment target water overboard discharge line (6) having a treatment target water overboard discharge unit (5) that discharges treatment target water overboard; and a treatment water overboard discharge line (10) having a treatment water suction pump (7) that sucks treatment water in the ballast tank (3), an ultraviolet reactor (8) that treats treatment water with ultraviolet radiation, and a treatment water overboard discharge unit (9) that discharges treatment water treated with ultraviolet radiation overboard. When treatment water is sucked, treatment water in the ballast tank (3) is sucked, passes through the ultraviolet reactor (8) to be treated with ultraviolet radiation, and is discharged overboard from the treatment water overboard discharge line (10).

Abstract: According to an example aspect of the present invention, there is provided an automated balloon launching system for launching at least one balloon such as a meteorological balloon or a radiosonde. The system comprises a container and a storage arranged in the container for storing at least one box at a defined storage position p=1, 2, . . . , n. The at least one box includes a balloon and a sonde. A release silo is arranged at least partially on top of or above and adjacent to the container for sheltering the balloon during inflation. A x-, y- and z-manipulator is arranged in the container for removing a specific box from one of the defined storage positions p=1, 2, . . . , n, and for subsequent feeding the release silo with the specific box. The present invention also concerns a method for launching at least one balloon such as a meteorological balloon or a radiosonde.

Abstract: A method for measuring the position of a mobile structure in a set of reference axes, the structure comprising a plurality of intrinsic recurrent structural elements, comprising the following steps undertaken by a processor. Acquiring simultaneous images of the structure from a plurality of optical devices, each recurrent element being in a field of view of at least three separate optical devices. Extracting the recurrent elements from each image and determining their position in the image. Computing at least one indicator for each recurrent element detected in each image. Identifying each recurrent element by associating a unique identifier with each element, the identifier being related to the position of each optical device in the set of reference axes, and to at least one indicator associated with each element in each image. Determining the position, by implementing a photogrammetric algorithm, of each recurrent element in the set of reference axes.

Abstract: A pressure bulkhead for an aircraft fuselage including a sandwich structure defining a central axis and extending between a circumferential border area, the sandwich structure including an inner face sheet and an outer face sheet extending transverse to the central axis, and a core assembly sandwiched between the inner face sheet and the outer face sheet. The pressure bulkhead can receive pressure loads and can be used as a structural bearing element for receiving loads introduced by other structural parts. The inner face sheet and/or the outer face sheet has a corrugated shape. The distance between the outer face sheet and the inner face sheet increases and subsequently decreases from the border area to a central area about the central axis, forming a thickened area where the distance between the outer face sheet and the inner face sheet has a peak.

Abstract: Described and illustrated is a pressure bulkhead for an aircraft fuselage, comprising a sandwich structure defining a central axis and extending between a circumferential border area which is configured for being mounted to a fuselage shell, wherein the sandwich structure comprises an inner face sheet extending perpendicularly with respect to the central axis, an outer face sheet opposite the inner face sheet, extending perpendicularly with respect to the central axis, and a core assembly sandwiched between the inner face sheet and the outer face sheet, wherein the inner face sheet, when viewed in a radial cross section along the central axis, has an even shape.

Abstract: The disclosed embodiments relate to an aircraft having an interior door with a compressible header. Accordingly to non-limiting embodiments, a slideable door panel includes an opening in a top portion thereof to receive a compressible header configured to reside in the opening of the slideable door panel. The compressible header includes a biasing mechanism configured to upwardly bias the compressible header against the headliner when closed. The compressible header is also configured to allow lateral movement of the compressible header within the opening. The compressibility of the compressible header and lateral movement resist the formation of gaps between the compressible header and the headliner during flight.

Abstract: An aircraft heated floor panel includes a first support layer, a second support layer, and a heating layer located between the first support layer and the second support layer. An aircraft floor panel includes a floor panel body and a removal feature that provides a mechanism for the aircraft floor panel to be removed from an attached aircraft structure.

Abstract: A foldable drone is provided to improve the portability of the drone, which includes a drone body and a rotary wing part connected to the drone body. The rotary wing part includes a first rotary wing module and a second rotary wing module with each having at least one rotary wing, and the first rotary wing module and the second rotary wing module are respectively articulated to two sides of the drone body, to allow the first rotary wing module and the second rotary wing module to rotate about their respective articulating shafts, so as to be folded or unfolded.

Abstract: The present disclosure refers to a multi-spar torsion box structure comprising a plurality of spars of composite material arranged to form a multi-cell structure with two or more cells extending span-wise at the torsion box, and upper and lower skin covers of composite material respectively joined to upper and lower surfaces of the multi-cell structure. The structure further comprises at least one belt-like reinforcing element extending on the outer perimeter of the torsion box, and fixed to the upper and lower surfaces of the multi-cell structure, and transversely arranged with respect to the span-wise direction of the torsion box. The belt-like reinforcing element is made of a metallic or a composite material. The present disclosure can advantageously be used in the manufacture of aircrafts lifting surfaces, such as horizontal tail planes (HTP) or wings.

Abstract: Flap track fairing systems are split into a forward immovably fixed portion and an aft movable portion. The fixed forward portion is immovably attached to the main wing structure of an aircraft while the movable aft portion is attached either to the movable components of the flap deployment mechanism or to the lower surface of the flap. A separation line between the forward movable portion and the aft fixed portion is provided such that the movable portion does not interfere structurally with the flap fairing structure during a flap extension/retraction cycle. An airflow deflector is positioned near a forward separation edge of the aft fairing portion so as to be positioned within a gap defined between the forward edge of the aft fairing portion and a rearward edge of the forward fairing portion when the flap is in the deployed configuration thereof to thereby deflect airflow away from the interior space of the fairing.

Abstract: A nacelle having a longitudinal axis and comprising a chassis, two articulated fan cowl doors and a sliding fan cowl door. Each articulated fan cowl door is rotatably mounted in an upper portion of the chassis, each about their own opening axis. The opening axes are parallel to the longitudinal axis. The articulated doors pivot between a closed position and an open position. The sliding fan cowl door, in its closed position, is placed between free edges of the articulated fan cowl doors. A sliding arrangement for the sliding door is configured such that, in the open position of either articulated door, the sliding fan cowl door can rotate about the longitudinal axis. The nacelle has fan cowl doors which take up less space when in the open position and which are more compact, in comparison to articulated fan cowl doors without a sliding fan cowl door.

Abstract: An aircraft hybrid flight control system comprising a manual control element, a mechanical transmission interposed between the manual control element and a control surface, an electromechanical actuator and a coupling unit configured to connect selectively the control surface to the mechanical transmission in a manual control mode and to the electromechanical actuator in a fly-by-wire control mode; the coupling unit is configured to maintain the mechanical transmission in a condition of substantial continuity with said control surface even in fly-by-wire mode, but for a freedom of relative motion of pre-set amplitude.

Abstract: The invention relates to an actuator (4) for controlling a horizontal stabiliser (3) of an aircraft, including: a primary channel including a screw (6) and a primary nut (7), the primary nut (7) being suitable for engaging with the screw (6), such that a rotation of the screw (6) relative to the primary nut (7) about a rotation axis (X) causes the primary nut (7) to translate relative to the screw (6) along the axis (X), such as to move the horizontal stabiliser (3); a secondary channel including a secondary part (25, 28), and a housing (23, 26), the secondary part (25, 28) being mounted in the housing (23, 26) with play between the secondary part and the housing, in which the secondary channel also includes a play take-up device (27), configured to, in the event of a breakdown of the primary channel causing the secondary part (25, 28) to move relative to the housing, eliminate the play between the secondary part (25, 28) and the housing (23, 26) such as to keep the secondary part (25, 28) in contact with the

Abstract: An actuator drive disconnection system comprises a housing and a drive coupling mounted in the housing, the drive coupling coupling a drive motor to an actuator drive train. A manually operable drive disconnection mechanism selectively moves the drive coupling from a first position in which the motor and actuator drive train are coupled and a second position in which the motor and actuator drive train are disconnected. The drive disconnection mechanism comprises an operating element which is manually extended from the housing to move the drive coupling from the first position to the second position.

Abstract: An aircraft (40a) is provided that includes a plurality of arms (41, 42, 43, 44) with selected arms having the ability to either adjust their length, have arm segments operative to move about an articulated joint in two or three dimensions, or have one arm operative to adjust an angle between the one arm and another arm, or any combination of the foregoing. Thrust generators are repositionably mounted on selected arms, and a control system enables automated, on-board, or remote control of the thrust generators, repositioning of the thrust generators on the arms, adjustment in the length of the selected arms, the movement of selected arms about the articulated joints, and adjustment of the angle between two or more arms, all while maintaining directional control of the aircraft in flight or on the ground. The aircraft has operational capabilities that exceed existing designs and facilitates manned and unmanned delivery of cargo and transportation of passengers.

Abstract: A winglet 3 has an inner end 5 and an outer 7. The winglet 3 has a varying radius of curvature (R) which: (i) decreases along the winglet over a first distance d1; (ii) remains constant over a second distance d2; and (iii) increases along the winglet 3 over a third distance d3. The sum of the first and third distances (d1+d3) is greater than the second distance (d2). The radius of curvature may vary according to the equation R=k1/dn. The parameter n may be equal to 1, such that the curvature follows an Euler spiral.

Abstract: An electromechanical actuator includes an actuator that is translatable along an axis relative to a case and that is made up of a deployed part and a non-deployed part, which are following one another along the axis and which are respectively deployed and not deployed outside the case. The axial span of the deployed part varies proportionally opposite that of the non-deployed part as a function of the translated position of the actuator. The actuator also includes an electric motor for translating the actuator, which is supported by the case and is connected to the non-deployed part of the actuator by a transmission. The case defines an inner volume inside which the non-deployed part of the actuator, the motor and the transmission are arranged. The inner volume is, during operation of the actuator, pressurized while being filled with a gaseous atmosphere.

Abstract: A locking device of an aircraft landing gear for locking the landing gear in a retracted and an extended position. A locking cylinder is arranged on a landing gear leg and a locking bolt is movably arranged in the locking cylinder. In the retracted position and in the extended position of the landing gear the locking bolt serves to fix the landing gear leg.

Abstract: A method of applying rotary drive by friction to an aircraft wheel that is provided with a drive track and that is mounted to rotate about an axis of rotation (X) on an axle carried by a low portion of aircraft landing gear by means of at least one friction roller (21) driven by a drive actuator (11) and associated with an actuator (23A, 23B, 30) for moving the roller between a disengaged position in which the roller is spaced apart from the drive track of the wheel and an engaged position in which the roller is kept pressed against the drive track. The method includes the step of controlling the force delivered by the actuator while they are holding the roller in the engaged position.

Abstract: A system and method for objectively evaluating an airport runway condition, where conditions pertaining to aircraft landing factors are compiled and used to determine a runway braking condition. One set of conditions pertains to aircraft landing factors, including brake metered pressure, wheel speed, and aircraft deceleration, and a second set of factors relate to pilot controlled parameters. A condition report is generated and made available to pilots of subsequently landing aircrafts prior to landing.

Abstract: According to one embodiment, a linear control motor includes a first permanent magnet, a coil, a shaft, a first non-magnetic material, and a joint coupled between the shaft and a spool operable to convert rotations of the shaft into axial movements of the spool. The first non-magnetic material is disposed between at least one of the movable components and at least one of the static components and operable to prevent physical contact between at least one of the movable components and at least one of the static components.

Abstract: A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled.

Abstract: A system and method for detaching an extractable unit from an extraction unit pulling the extractable unit in an extraction direction out of a cargo bay of an aerospace vehicle for aerial delivery. The system includes a detachment unit which is connectable to an extractable unit and which is operable for controllably detaching an extraction unit from the extractable unit, a guiding system and a release unit. The release unit is movably attached to the guiding system and physically connected to the detachment unit such that the release unit is movable with an extractable unit to which the detachment unit has been connected in the extraction direction along the guiding system. The release unit is controllable to operate the detachment unit to which the release unit is connected for detaching an extraction unit from the extractable unit.

Abstract: A device is provided. The device includes one or more electric sifters externally mounted to an aircraft and configured to store a payload. Each electric sifter includes a loading port to add the payload and a distribution apparatus to distribute the payload when the aircraft is airborne. The device also includes an uploaded program, configured to control the aircraft and the device. The uploaded program directs the aircraft to land at a designated location in response to a payload of a designated one of the one or more electric sifters reaching a predetermined level. In response to the device receives a command to activate the distribution apparatus, the distribution apparatus distributes the payload from the device.

Abstract: An aircraft has a wing and at least a portion of a hoist system disposed within the wing. A method of hoisting an item includes disposing at least a portion of a hoist system within a wing of an aircraft and extending a cable of the hoist system through an access hole of an exterior wall of the wing.

Abstract: An external cargo damping system includes lifting gear and a damping assembly. The lifting gear has a lifting body attachment end and an opposed external cargo end, and defines a load path that extends between the lifting body attachment and external cargo ends of the lifting gear. The damping assembly is connected in series with the lifting gear and is disposed along the load path to damp vibratory force transmitted between the lifting gear lifting body attachment and lifting gear ends.

Abstract: A device for locking a holding pin connected with a cover with a holding pin for the cover, with a magnet. The device has a rotational body held in an end position by the magnet. The rotational body has inside a receiving area provided with an inner wall for at least one ball and for the holding pin, wherein in the receiving area of the rotational body the at least one ball is arranged between the inner wall of the receiving area of the rotational body and the holding pin arranged inside the receiving area under formation of a form fit for locking the holding pin and for unlocking the holding pin by turning the rotational body, the clamp effect of the at least one ball is reduced or removed through the spacing of the at least one ball from the holding pin so that the holding pin is movable.

Abstract: A retractable support for a screen, and interior layout assembly for an aircraft cabin comprising such a support are provided. The retractable support for a screen includes a housing for receiving the screen in a retracted position, and an arm movably mounted relatively to the housing between a retracted position inside the housing and a deployed position outside the housing. The arm includes first and second rigid segments jointed with each other so that the second segment pivots relatively to the first segment around a first pivot axis between a compact configuration, in which the second segment is fitted into a recess of the first segment, and an extended configuration, in which the second segment extends out of said recess.

Abstract: A retractable support for a screen, and aircraft cabin seat including such a support are provided. The retractable support for a screen comprises a support arm for the screen and a housing for receiving the arm in a retracted position inside the housing. The housing comprises a mechanism for deploying the arm outside the housing. The support further comprises a compartment defining a cavity for receiving the housing in a retracted position inside the compartment. The housing is mounted movably relative to the compartment between the retracted position and a free position outside the compartment.

Abstract: An aircraft interior door assembly (10, 20, 30) for selectively increasing usable space within an aircraft lavatory (1) adjacent a passenger doorway area (2) of the aircraft or in the passenger doorway area (2) adjacent the lavatory (1) comprises a door element (12, 22, 32) and a door element supporting structure (13, 23, 33). The door element (12, 22, 32) is rotatably mounted to the door element supporting structure (13, 23, 33) so as to be at least rotatable between first and second closed positions relative to the door element supporting structure (13, 23, 33). The door element (12, 22, 32) has the same configuration in both of its closed positions.

Abstract: A galley refrigeration system includes a liquid heat exchange loop and an air heat exchange loop in thermal communication with the liquid heat exchange loop. The air heat exchange loop includes a heat exchanger configured to be coupled in flow communication with at least one galley cart. Optionally, the galley refrigeration system may include a control system in operative communication with the liquid heat exchange loop and the air heat exchange loop.

Abstract: An aircraft seat mounting device with at least one carrier profile, with at least one aircraft seat element and with at least one intermediate element, which at least substantially encompasses the at least one carrier profile and is coupled to the at least one aircraft seat element. The intermediate element is arranged rotatably with respect to the carrier profile at least in case of crash/deformation.

Abstract: A galley cart includes walls defining an interior cavity extending between a front and a rear of the galley cart and the interior cavity extending between a top end and a bottom end. A supply port is provided in flow communication with the interior cavity at or near either the top end or the bottom end of the cart. A return port is provided in flow communication with the interior cavity that is adjacent the supply port at or near the top end or the bottom end of the cart. A barrier is positioned between the supply port and the return port within the interior cavity of the cart to define a supply chamber and a return chamber to control airflow through the interior cavity.

Abstract: The system comprises at least one evaporator device arranged around a tube inside which a hot fluid flows and, for each evaporator device, a respective conduit connected at its opposite ends to the evaporator device so as to form with the latter a closed circuit containing a two-phase fluid. Each evaporator device comprises a casing, having an inner wall in contact with the respective tube and an outer wall enclosing a cavity with the inner wall, and a separating member of porous material arranged inside the casing so as to divide radially the cavity into an inner cavity, extending between the inner wall and the separating member, and an outer cavity extending between the separating member and the outer wall.

Abstract: An environmental control system for an aircraft includes a bleed air system. Also included is a ram air system. Further included is an air pressure and temperature conditioning system, wherein bleed air and ram air are mixed to satisfy a cabin fresh air requirement.

Abstract: The present disclosure refers to a method and a related system of flight termination for air vehicles. The method and the system of flight termination for air vehicles involve deploying a parachute for flight termination of an air vehicle. A flight termination system, which in turn comprises at least one microcontroller unit that is connected to at least one parachute deployment system for deploying an air vehicle's parachute when a major emergency is determined during an air vehicle's flight.

Abstract: An insert includes a shaft. The shaft includes a first end, a second end, and an external surface and an internal surface extending between the first end and the second end. The internal surface defines a passage through the shaft. The insert further includes a base flange located at the first end of the cylindrical shaft and having a first diameter. The insert also incudes a first disc member having a second diameter smaller than the first diameter and located at the second end of the cylindrical shaft. The insert still further includes a second disc member having a third diameter smaller than the first diameter and located on the cylindrical shaft between the base flange and the first disc member.

Abstract: An electrical network for an aircraft. The aircraft includes at least one variable pitch propulsor. The electrical network includes a wound field synchronous AC electrical generator having a wound rotor driven by an internal combustion engine. The network further includes a voltage regulator configured to regulate output voltage of the electrical generator by regulating rotor winding magnetic field strength, and a synchronous AC drive motor coupled to a respective variable pitch propulsor and provided with power from the output of the electrical generator.

Abstract: The invention relates to a nacelle (1) for an aircraft turbojet, the nacelle comprising a frustoconical radially outer annular wall (13), a pylon (9) extending radially outwards from said annular wall, the pylon (9) being designed to fasten the nacelle (1) to a fixed portion of the airplane, said nacelle being characterized in that it is provided with at least one projecting zone (22) extending radially outwards from the frustoconical outer wall (13), said projecting zone (22) being situated in the vicinity of a downstream annular edge (14) of said outer wall (13) and in the vicinity of the pylon (9).

Abstract: A turbomachine subassembly including an annular gas flow path is delimited by a radially inner shell and a radially outer shell, a radial arm between the inner shell and the outer shell, that delimits an isolated volume of the annular flow path, which is connected to the inner volume in which a segment of a conduit, and ventilation air supply to a chamber delimited at least partly by the inner shell, through one radial arm, wherein the volume delimited by the radial arm is connected to the inner volume of the chamber and to a ventilation air supply source, wherein the external radial end of the arm supports a first connection box that closes off the external radial end of the arm, that includes a device for connecting the segment to the remainder of the conduit and a device for connecting the internal volume of the arm to the ventilation air supply source.

Abstract: A method for displaying an outside scene on a cockpit display system. The system comprises two display areas contiguous along a horizontal aircraft axis and a processor to generate the display, on one of the areas, of an initial scene image from data from the aircraft's avionics electronics, the data comprising the aircraft's sideslip angle ?. The processor displays, on the scene image, a flight path vector indicating a point on the scene image towards which the aircraft is heading. When the measured angle ? exceeds a threshold, the processor displays the initial scene image on a first display area and the display of a supplementary outside scene image, on a second display area, the supplementary scene image representing a lateral extension of the initial scene image. The processor also displays the flight path vector superimposed on one of the two images based on a value of angle ?.