Abstract: A lifesaving handle system for a watercraft surface such as, but not limited to, a boat hull. The handle system remains attached to an exterior surface of a watercraft hull when the watercraft is upright (i.e., when it is not capsized) such as when it is flowing on a body of water in normal operation. The handle may be rotatably attached to a hinge attachment such that when the boat is upright, as in non-capsized operation, the handle hangs vertically and is not within the flow of water passing along and around the watercraft hull when the boat is motivated on a body of water; and when the boat is overturned or capsized, the handle rotates out from the watercraft hull under the force of gravity such that the grip handle is presented to a person in the water.

Abstract: A shade assembly for personal watercraft to provide shade for the user from direct exposure of at least some sunlight. The shade assembly comprises a shade top, a front fixing structure, and a rear supporting structure. The shade top is designed to be attached to the front fixing structure and the rear supporting structure to create a shade that extends over the user. The front fixing structure comprises two or more fasteners to securely attach the shade top to the steering control handle or two or more supporting pillars, while the rear supporting structure comprises two or more supporting pillars to be fixed on the aft side of the personal watercraft. This shade assembly provides a simple and efficient solution to protect the user of personal watercraft from harmful sun exposure.

Abstract: A spreading device for trawl fishing, seismic survey operations or other water activities where it is desirable to keep distance between two sides of a towed device is provided, the spreading device having at least one part comprising two or more foils, where each foil has a front surface and a rear surface, the surfaces each being defined by two edges and two side limitations, in use being front and rear edges, an upper and lower side limitations connected to respective upper and lower frames, where at least one foil is stationary and where one or more sections of another foil is pivotably connected to the another foil, such that the section may be moved from a position where the surface of the section is flush with the surface of the another foil, to a position where the surface is out of plane with the surface of the another foil.

Abstract: Provided is a position control apparatus of an unmanned marine observation device, the position control apparatus including a main body part including a hollow portion into which the unmanned marine observation device is coupled, a movement part extending outward from the main body part and configured to move the unmanned marine observation device and the position control apparatus in the ocean, a GPS signal receiver configured to receive a GPS signal and produce position information on the basis of the GPS signal, and a controller configured to control an operation of the movement part on the basis of the GPS signal.

Abstract: A method of transshipping liquid cargo in a tanker, including loading and unloading. Before loading, inserts are arranged in cargo tanks, with inlet and outlet openings of the inserts attached at corresponding openings of hatches, after which the inserts are unfolded. A temporary cargo system is assembled, including a pipeline with adapters and portable hoses, which are lowered into the openings of the inserts. The cargo is loaded into the tanks at a port of origin through the hatches into the inserts. After loading, the cargo system is disassembled. For unloading, the cargo system is assembled, with submersible pumps attached to ends of the hoses, the hoses with the pumps are lowered into the inserts, and the cargo is unloaded from the tanks to reservoirs at a port of destination using the pumps. The cargo system is disassembled and the inserts are removed from the tanks and sent for disposal.

Abstract: The wakesurfing system may include a first and second reel assembly arranged and configured to retract a discarded surf rope. The second reel assembly may be replaced by a retraction device. The first reel assembly may have a telescoping and rotatable boom and may be coupled to a side of the watercraft. The second reel assembly or retraction device may be coupled to a rear portion of the watercraft. The first reel assembly may have a first reel cord coupled to a handle of the surf rope, and the second reel assembly may have a second reel cord coupled to a proximal location of the surf rope. The first reel cord and either second reel cord or retraction device, and the surf rope, may be in a retracted position when not in use, and in an extended position when used by a wakesurfer.

Abstract: A gyroscopic roll stabilizer comprises a gimbal having a support frame and enclosure configured to maintain a below-ambient pressure, a flywheel assembly including a flywheel and flywheel shaft, one or more bearings for rotatably mounting the flywheel inside the enclosure, a motor for rotating the flywheel, and bearing cooling system for cooling the bearings supporting the flywheel. For smaller units, the bearing cooling system is effective to enable a flywheel with a moment of inertia less than 40,000 lb in2 to be accelerated at a rate of 5 rpm/s or greater. For larger units, the bearing cooling system is effective to enable a flywheel with a moment of inertia greater than 40,000 lb in2 to be accelerated at a rate of 2.5 rpm/s or greater.

Abstract: A method and a system for controlling a marine vessel having first and second trim deflectors is disclosed. The first and second trim deflectors have a first surface having a first area and a second surface having a second area, wherein the second planar surface is coupled to the first surface. The method and system control the first and second trim deflectors to induce any of a net yawing force, a net rolling force, and a net trimming force to the marine vessel without inducing any other substantial forces to the marine vessel by controlling the first and second trim deflectors.

Abstract: The present disclosure relates to a rolling reduction boat, and more particularly, to a rolling reduction boat having a structure that allows a rolling reduction tube, which is formed to surround a boat main body, to be filled with water. The present disclosure has the following advantageous effects. That is, according to the present disclosure, by filling a rolling reduction tube, which surrounds a boat main body, with water, there are advantages that the overall weight of the boat is increased, and the center of mass is moved downward and distributed, thus making it easy to get on the boat even in water, and the degree to which the boat tilts or rolls due to external factors such as a strong wind, a wave, and a change in the position of a passenger is reduced and a restoring force of the boat is increased, thus making it possible to more safely sail the boat.

Abstract: A method for repairing a damaged area of a hull of a water vessel includes providing a patch assembly having (i) a first flexible outer layer, (ii) a second flexible outer layer and (iii) an inner layer of composite material sealed between the first flexible outer layer and the second flexible outer layer. When the inner layer is heated and then cures, the composite material transforms from a flexible uncured state to a fixed cured state. With the composite material in the uncured state, the patch assembly is positioned at a damaged area of a hull of a water vessel and conforms to a shape of the hull. An electric heating element is electrically operated to heat the inner layer, and when the inner layer is cured, the composite material is cured, where the shape of the inner layer is fixed relative to the shape of the hull.

Abstract: A navigational information displaying device sequentially acquires first geographic coordinates of a first ship traveling on the sea, and generates a first object indicative of the first ship at first indication coordinates in an image displayed on a display unit. The device generates a first window indicating the first object and moving in the image in association with movement of the first object or an indication viewpoint, accepts a specification of second indication coordinates in the image from a user, and generates a second window indicating the second indication coordinates. The device acquires second geographic coordinates corresponding to the second indication coordinates, and calculates navigational information including a distance between the first and second geographic coordinates. The device displays the first object, the first window, the second window, and the navigational information in the image, and controls the first and second windows to not overlap with each other.

Abstract: An objective of the present disclosure is to provide an integrated condition monitoring system and method for an ice-going vessel, the system and method for acquiring voyage information and environment information when a vessel sails a polar ocean area. In order to achieve the objective, an integrated condition monitoring system for an ice-going vessel includes: imaging units installed at a bow, a stern, and left and right sides of the vessel, and imaging an ice environment; and a server monitoring an integrated condition of the vessel on the basis of images taken by the imaging units.

Abstract: A water mat for a boat and a boat. The boat may be a pontoon boat. The water mat may include a cut-out. The cut-out may be formed in a forward side of the water mat, with the forward side of the water mat is connected to the stern of the boat such that the outboard motor is positioned in the cut-out of the water mat. A flexible connecting sheet, that is configured to connect the water mat with the boat, may be attached to a connection side of the water mat and extend along the connection side of the water mat.

Abstract: A technique for carrying a payload by a UUV includes providing a structure that extends around an outer surface of the UUV along a length of the UUV. The structure has an outer membrane that forms a streamlined shape around the UUV and contains the payload.

Abstract: Invention relates to a thruster assembly for a marine vessel including a body including a duct having a longitudinal axis, and a first end and a second end, a support structure for a propeller including a propeller shaft at a centre line of the duct, a propeller, positioned into the duct and being attached to the propeller shaft, wherein the propeller including at least three blades and a boss which is supported to the shaft, and further a circular rim to which radial ends of the propeller blades are attached, wherein a circumferential slot is provided, opening inside the duct between the first end and the second end, into which slot the circular rim is arranged to extend radially, and at least one gas inlet arranged to open into the slot. Invention relates also to a transverse tunnel thruster and a steerable azimuthing thruster provided with the thruster assembly.

Abstract: Tethered-wing traction system including: a traction wing (5), a base platform (3), a mooring mast (4), a plurality of folding lines (10A,10B,10C), a furling line (13), a mooring carriage (12B), a folding carriage (12C, 12D, 12E), a furling carriage (12A), and a control module (64) having at least the following two operating modes: a folding mode in which the mooring carriage (12B) and the folding carriage (12C, 12D, 12E) are spaced apart from each other; and a furling mode in which the furling carriage (12A) and the mooring carriage (12B) are spaced apart from each other.

Abstract: A watercraft propulsion system includes a bow thruster to generate a lateral propulsive force, a propulsion device on a stern of a hull and having a variable steering angle, and a controller configured or programmed to control the bow thruster and the propulsion device to perform a fixed point holding control to maintain a position and an azimuth of the hull. The fixed point holding control includes a translation mode in which the hull position is maintained by controlling the propulsive force of the propulsion device with the steering angle set to a translation mode steering angle and the hull azimuth is adjusted by controlling the propulsive force of the bow thruster, and a bow turning mode in which the hull azimuth is adjusted by controlling the propulsive forces of the bow thruster and the propulsion device with the steering angle set to a bow turning mode steering angle.

Abstract: A watercraft propulsion system includes a bow thruster at a bow of a hull to generate a lateral propulsive force, at least two propulsion devices on a stern of the hull each having a variable steering angle, and a controller configured or programmed to control the propulsive force of the bow thruster and control the propulsive forces and the steering angles of the two propulsion devices to perform an azimuth control to control an azimuth of the hull. The azimuth control includes a bow thruster mode in which the bow thruster is controlled, and a combinational mode in which the bow thruster is controlled and the two propulsion devices are driven forward and in reverse, respectively. The controller switches between the bow thruster mode and the combinational mode based on a predetermined switching condition during the azimuth control.

Abstract: A watercraft propulsion system includes a bow thruster, at least two propulsion devices, a translation operator to command a hull translation movement, and a controller configured or programmed to, in a translation watercraft maneuvering mode, control the propulsion devices so that propulsive force action lines thereof cross each other in the hull, and to drive one of the propulsion devices forward and drive another of the propulsion device in reverse. In a standby state, the controller is configured or programmed to prevent the bow thruster and the propulsion devices from generating propulsive forces, and set the steering angles of the propulsion devices to translation standby steering angles. In response to the operation of the translation operator, the controller is configured or programmed to cause the bow thruster and the propulsion devices to start generating the propulsive forces, and change the steering angles of the propulsion devices to translation steering angles.

Abstract: A ballast dispenser system and method for flight vehicles, such as high altitude lighter than air vehicles. The system passively retains ballast without power and deploys ballast in response to applying power. An electro-permanent magnet passively retains ballast within the dispenser. Application of power to a coil produces an opposing magnetic field that reduces the overall strength of a net magnetic field acting on the ballast. Lateral positional control of the electro-permanent magnet provides calibration and control of the retaining magnetic field strength. A collapsible silo may hold ballast prior to dispensing ballast and collapse upon landing for minimizing damage.

Abstract: An aircraft, a center wing box assembly for an aircraft, and a spanwise beam section for a center wing box assembly that includes a segmented structural configuration with an optimized access hole to accommodate user access into an interior space of the center wing box for purposes of assembly and maintenance. The center wing box assembly includes a first spanwise beam section, a second spanwise beam section, spaced from the first spanwise beam section, and a plurality of chord members serving as load-bearing structural reinforcement members for the first spanwise beam section and the second spanwise beam section. The chord members extend across the space between the first spanwise beam section and the second spanwise beam section to connect the first spanwise beam section and the second spanwise beam section in a manner which defines an access hole at the interior space.

Abstract: A skin assembly that includes a first ceramic-matrix-composite skin panel including one or more first fingers extending along a first direction. The skin assembly further includes a second ceramic-matrix-composite skin panel including one or more second fingers extending along the first direction. The one or more second fingers interdigitated with the one or more first fingers to define a plurality of staggered expansion gaps between the first ceramic-matrix-composite skin panel and the second ceramic-matrix-composite skin panel wherein the plurality of staggered expansion gaps are configured to accommodate thermal expansion of at least a portion of the skin assembly.

Abstract: A door is provided for a furniture structure of a vehicle cabin. The door includes a frame configured to expand and collapse along a longitudinal axis of the door between a collapsed position and an expanded position. The door includes a cover extending over at least a portion of the frame.

Abstract: A floor panel for installation in an aircraft includes a plurality of thermoplastic C-shaped stringers, a consolidated thermoplastic deltoid filler, a thermoplastic upper facing sheet, and a thermoplastic lower facing sheet. The stringers are disposed in a parallel arrangement with one another. The deltoid filler is disposed within a longitudinally-extending notch defined by a pair of adjacent stringers. The upper facing sheet covers an upper surface of the stringers and the deltoid filler. The lower facing sheet covers a lower surface of the stringers and the deltoid filler. The stringers, the deltoid filler, and the upper and lower facing sheets are integrally consolidated forming a unitary construction.

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

Abstract: There is provided a strut assembly for a wing of an aircraft. The strut assembly has a strut having an outboard end, an inboard end, and an elongate body. The outboard end is coupled to the wing of the aircraft, and the inboard end is coupled to a fuselage of the aircraft. The strut assembly further has at least one tensioner member having a first end coupled to the strut. The strut assembly further has a first fitting element having a through opening receiving a first portion of the strut and a bearing surface facing inboard. The strut assembly further has a second fitting element having a through opening receiving a second portion of the strut and a bearing surface facing outboard. The at least one tensioner member maintains tension in the strut, to keep the strut taut and in tension, to prevent or to minimize drooping of the strut.

Abstract: A reduced noise curved surface, including the elements of a curved substrate and a plurality of micropillars operationally connected to the curved substrate and defining a coating, wherein the respective micropillars are positioned to define an aperiodic sequence based on the golden ratio, and wherein the plurality of aperiodically sequenced micropillars increase sound absorption and drag reduction of the curved surface.

Abstract: A multi-layer braided article and a method of making the multi-layer braided article. The multi-layer braided article includes a braid extending along a first axis, wherein the braid is folded over itself to form a first layer and a second layer; and a wrapper laid over the first layer of the braid and extending circumferentially around the first axis, wherein the wrapper defines an edge of the first layer about which the braid is folded. The multi-layer braided article may form part of a blade for an aircraft. A sleeve may be provided around a conical portion of the article to connect the article to something else, such as a propeller hub, where the multi-layer braided article is formed as part of a blade. The sleeve may provide a primary or secondary load path.

Abstract: A propeller control unit for an aircraft propulsion system including a propeller is provided. The propeller control unit includes an actuator, a pump, a flow regulator, a pressure sensor, and a controller. The actuator is configured to control a pitch of each of the propeller blades. The pump is configured to direct hydraulic fluid to the actuator. The flow regulator is in fluid communication with the pump and configured to control a hydraulic fluid pressure of the hydraulic fluid downstream of the pump. The pressure sensor is disposed downstream of the pump and upstream of the actuator. The pressure sensor is configured to measure the hydraulic fluid pressure and generate a hydraulic fluid pressure signal. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to monitor the hydraulic fluid pressure signal.

Abstract: A method for unmanned delivery of an item to a desired delivery location includes receiving, at an unmanned vehicle, first data representative of an approximate geographic location of the desired delivery location, receiving, at the unmanned vehicle, second data representative of a fiducial expected to be detectable at the desired delivery location, using the first data to operate the unmanned vehicle to travel to the approximate geographic location of the desired delivery location, upon arriving at the approximate geographic location of the desired delivery location, using the second data to operate the unmanned vehicle to detect the fiducial; and upon detecting the fiducial, using the fiducial to operate the unmanned vehicle to deliver the item.

Abstract: An electric aircraft includes a fuselage, at least one rotor, at least one coupling structure, at least one electric motor, a battery and wirings. The at least one coupling structure couples the at least one rotor to the fuselage. The at least one electric motor is for rotating the at least one rotor. The battery is attached to the fuselage. The battery is for supplying current to the at least one electric motor. The wirings electrically couples the battery to the at least one electric motor. At least a part of the wirings includes rigid conductors. At least a part of the at least one coupling structure includes the rigid conductors. At least a part of a load on the fuselage from the at least one rotor is received with the rigid conductors.

Abstract: A rotorcraft includes a fuselage, rotors and circular wings. The rotors are attached to the fuselage. The rotors are attached to the fuselage. The circular wings are disposed under the rotors respectively. Upper surfaces of the circular wings have annular curved surfaces and thereby are convex upward respectively. The circular wings cause Coanda effects by the upper surfaces respectively. First lift is generated by rotating the rotors. Second lift is generated by the Coanda effects by the circular wings. Third lift is generated by air jets deflected downward along the upper surfaces of the circular wings respectively.

Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

Abstract: Systems and methods for receiving packages from drones and other unmanned aerial vehicles (UAVs) are described. The systems can include a delivery package mounting unit, such as a unit configured to mount to the outside of a house or building, configured and adapted to facilitate the landing of a drone to the unit and receive to multiple packages from the drone and/or one or more other drones. In some embodiments, the mounting unit includes a landing tray configured to facilitate the landing of a drone to the unit, and a moveable package tray configured to receive packages and other cargo from the drone.

Abstract: A payload receiver apparatus including a base configured to receive a payload suspended from an uncrewed aerial vehicle (UAV), an extending member having an upper end positioned above the base, a first tether engager that extends in a first direction from the extending member, wherein the base includes a payload platform positioned below the first tether end of the channel and configured to receive a payload thereon, wherein the first tether engager is adapted to guide a tether having a first end attached to the UAV and a second end attached to a payload coupling apparatus to a position above the payload platform.

Abstract: A hanging structure applicable to an unmanned aerial vehicle includes a hook-shaped body and at least one hook claw. The hook-shaped body has a bottom, at least one pivoting end, and an abutting portion. A hook opening is provided between the at least one pivoting end and the abutting portion and is opposite to the bottom. In addition, the at least one hook claw has a pivoting portion, and a first claw portion and a second claw portion that extend from the pivoting portion, respectively. The pivoting portion is pivoted to the at least one pivoting end. The second claw portion is heavier than the first claw portion. When the hanging structure is in a hanging state, a first end of the first claw portion abuts against the abutting portion, and the hook opening is closed. An unmanned aerial vehicle hanging system including the above hanging structure is further provided.

Abstract: The present disclosure relates to an aerial drone with a central passage and a rotating frame. A payload moves within a central passage through the drone body into a deployed position. The payload engages with the rotating frame and can be rotated into a desired orientation below the drone.

Abstract: Systems to reduce the loads on highly flexible aircraft cargo, such as wind turbine blades, are disclosed. Such systems can be active and/or passive. Active systems can be in the form of open or closed loop active control systems comprising one or more sensors on the airframe and/or payload, actuators acting on the payload, and/or an electronic controller. Passive systems can include spring-and-damper suspensions, optionally combined with devices such as vibration absorbers, and can be controlled, for example, by the placement of payload fixtures and the degrees of constraint they impose on the payload.

Abstract: A cabin attendant seat is disclosed. The seat may include a seat pan and a seatback. The seat may include a device holder coupled to the seat pan. The device holder may include a main body including a plurality of main body walls that define a main body cavity and a cover including a plurality of cover walls that define a cover cavity. The main body cavity and the cover cavity may form a device holder cavity configured to stow a mobile device. The device holder may include an opening configured to receive the mobile device. The device holder may include a device securing assembly configured to rotate between a first and second position, when in the first position the securing assembly configured to secure the mobile device within the cavity, when in the second position the mobile device configured to be removed from the device holder cavity.

Abstract: A reclining seat comprises a fixed supporting frame, a reclining backrest, and a damping device providing, at lower ends of frame elements forming the seat frame, a lever which is revolvingly hinged on a respective pin integral to the supporting frame and which forms a rocker arm which rotates by a prefixed angle from a first position, corresponding to the reclining backrest in erected position, to a second position, corresponding to the reclining backrest in reclined position, a hydraulic cylinder being provided, with respective fastening ends revolvingly connected respectively to said second lever and to the fixed supporting frame in a prefixed position.

Abstract: A reclining seat comprises a fixed supporting frame, a reclining backrest, a sitting portion and a stiffening mechanism with reduced overall dimensions, which in turn comprises, at lower ends of frame elements forming the seat frame, a lever which is revolvingly hinged on a respective pin integral with the supporting frame and forming a rocker arm which rotates by a pre-fixed angle from a first position, corresponding to the reclining backrest in erected position, to a second position, corresponding to the reclining backrest in reclined position, a stiff tie-rod being provided the ends thereof are joined to the respective distal ends of the rocker arms, thereby the rotation of one of them causes the rotation by an angle having the same width of the other rocker arm.

Abstract: Described are non-uniform tubes (104) for a furniture unit for an aircraft. The non-uniform tubes can include a first end (108), a second end (110), a wall (112), and a tube central axis (118). The second end may be opposite from the first end, and the wall can extend from the first end to the second end. The wall can include an inner surface and an outer surface in which the inner surface defines a cavity (120) extending from the first end to the second end. The non-uniform tubes can include a first portion (124) between the first end and the second end. The cavity can include a cavity central axis (122), and, in the first portion (124), the cavity central axis (122) may be offset from the tube central axis (118).

Abstract: Described are mounting assemblies for an item of aircraft furniture in an aircraft. The mounting assemblies each include a base, a first connector, and a second connector. The base includes a first slot elongated in a first direction and a second slot elongated in a second direction. The first connector is retained within and is movable within the first slot, and the second connector is retained within and is movable within the second slot. The first connector and the second connector may be simultaneously movable in the first direction and the second direction.

Abstract: An air conditioning pack management system for controlling distribution of a predetermined amount of conditioned air from a system comprising two or more air conditioning packs, the pack management system comprising a management unit arranged to proportion the predetermined amount of conditioned air to be provided by one or more of the two or more packs based on the respective operating efficiencies of the packs or other pre-selected metrics.

Abstract: An aircraft includes a fuselage and at least one primary wing having an upper surface, at least one recess in the upper surface and at least one conduit in fluid communication with the at least one recess. At least one ejector is disposed within the at least one recess and is configured to receive compressed air via the at least one conduit.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon includes: a thrust link coupled to the gas turbine engine and an aft mount, the gas turbine engine coupled to the pylon via a forward mount and the aft mount, a bending restraint having a first end and a second end, the bending restraint including an actuator positioned at the first end to apply a force to a fan section of the gas turbine engine, a first joint positioned at the first end of the bending restraint, the first joint coupled to the first end of the bending restraint and the fan section, and a second joint positioned at the second end of the bending restraint, the second joint coupled to the second end of the bending restraint.

Abstract: An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.

Abstract: An inner cowl arrangement for a gas turbine engine includes a first hinge and a second hinge pivotally connecting a first cowl member and a second cowl member, respectively, to a mounting structure. The inner cowl arrangement further includes a latch detachably securing the first and second cowl members. At least one of the first hinge, the second hinge, and the latch includes a pressure relief component that deforms or breaks when an applied load on the pressure relief component due to a pressure within an engine core is greater a normal operating load, causing at least one of the first cowl member and the second cowl member to move relative to the engine core, and forming an opening.

Abstract: An aircraft provided with at least one exhaust duct for discharging gases from an engine. The exhaust duct is partly accommodated in an internal housing of the aircraft, the housing being separated from an external environment situated outside the aircraft by at least one cowl that is able to move in relation to a load-bearing structure of the aircraft. The exhaust duct comprises an exhaust segment passing through a passage of the cowl without touching the cowl. A space separates the exhaust segment from the cowl. The aircraft comprises at least one stabilization system coupled to the exhaust duct, the stabilization system comprising a stiffening ring secured to the exhaust duct and at least one fastening connecting the exhaust duct to the cowl.

Abstract: An aviation propulsion system for an aircraft with two engines, comprising respectively a connecting shaft which is rotatably drivable in rotation by one of the engines, wherein mutually facing ends of both connecting shafts are connected to each other or are connectable to each other in a rotatably drivable manner. Both connecting shafts are connected via their mutually facing ends in a rotatably drivable manner to one of the mutually facing ends of the connecting shafts via a openable coupling.