Abstract: A floating platform dimensioned and configured to receive and transport an automated pool cleaner on the surface of the water is disclosed. For convenience, the floating platform is referred to as a pontoon. The pontoon is also configured to control the retrieval of the pool cleaner. The pontoon includes a buoyant housing having a first end and a second end. An inclined platform ramp is positioned in the pontoon housing at an angle from the first end towards the second end. The pontoon includes a winch for winding and unwinding a cable connected to the pool cleaner to thereby selectively release and retrieve the cleaner.

Abstract: A flexible inflatable container that includes a flexible inflatable core having opposing first and second panel members, each with an interior side. A plurality of longitudinally oriented stringers is disposed on at least one interior side of one of the opposing first and second panel members. Each stringer has at least one edge. Zippers join stringers portions to one another or to the panel members or both. An inflation valve on one of the panel members is provided for introducing fluid into the flexible inflatable core. The core is covered by a flexible outer skin.

Abstract: A wave riding hoard is provided herein that has a body including a top, a bottom, a right edge, a left edge, a front, a rear and a length defined from the front to the rear. The bottom of the body includes one or more steps. A first channel is defined at least partially between the one or more steps. The first channel extends along at least a portion of the length of the body. At least one of the one or more steps extends at least partially around the left edge or the right edge of the body.

Abstract: An embodiment includes an open/non-closed hull collar assembly that is shaped to increase encapsulated volume of a hull. The hull collar assembly may include a hull collar structure and a foam module. The hull collar structure may include a gunwale, an outboard boundary, and an inboard boundary. The outboard boundary extends in an outward lateral direction from a lower hull portion and extends in a longitudinal direction from the lower hull portion such that at least a portion of the hull collar structure is at least partially included in a freeboard portion of a boat hull. The inboard boundary extends from the gunwale a portion of a distance to a deck such that the hull collar structure is at least partially open or non-closed to an inner hull volume. The foam module is comprised of a non-expansive, closed cell foam. The foam module is shaped for disposition within the hull collar structure.

Abstract: A search and rescue drone system includes a buoyant body member, a frame attached to the buoyant body member for carrying a motor and propeller, and an electronic array including a camera, GPS, an EPIRB radio distress beacon, and a transmitter/receiver for remote control flying the drone and communicating with an operator. The search and rescue drone may be flown manually, or may have some autonomous flight and locator capabilities. For example, in one embodiment, the search and rescue drone may be programmed to simply fly to the location of an electronic wearable device, like a bracelet, that is worn by a man overboard. In another embodiment, the search and rescue drone includes a basket, harness, or other means for actually recovering a swimmer in distress, and flying that person back to safety on a ship or on shore.

Abstract: A search and rescue drone system includes a buoyant body member, a frame attached to the buoyant body member for carrying a motor and propeller, and an electronic array including a camera, GPS, an EPIRB radio distress beacon, and a transmitter/receiver for remote control flying the drone and communicating with an operator. A laser guidance system may provide coordinates for landing near a swimmer in distress. The search and rescue drone may also be programmed to simply fly to the location of an electronic wearable device, like a bracelet, that is worn by a man overboard. In another embodiment, the search and rescue drone includes pivoting motor mounts, so that it can take off and land vertically with propellers rotating in a horizontal plane, and then the propellers may pivot to rotate in a vertical plane for propulsion across water similar to a fan boat with rescued people aboard.

Abstract: An inline for an inflatable assembly may comprise a first end defining a primary gas inlet and a second end defining a primary gas outlet. An internal surface may define a flow path extending from the primary gas inlet to the primary gas outlet. An orifice may be located between the first end and the second end. The orifice may be defined, at least partially, by a radial wall extending from the internal surface to the external surface. The orifice may be configured to entrain ambient air with a primary gas flowing from the primary gas inlet to the primary gas outlet.

Abstract: A personal survival system for use in water includes an inflatable chamber (9) and in inflation system (31) operable to inflate the inflatable chamber (9), wherein the inflation system (31) is mounted separately from and remotely from the inflatable chamber (9). Also disclosed are: a survival system for use in water includes an inflatable chamber including an inner layer and an outer layer, wherein the inner layer is separate from the outer layer; an inflation control system for use with an in-water survival system, the inflation control system comprises a selectively sealable chamber configured to contain water-triggered automatic inflation device of the survival system; and a personal survival system including an inflatable bladder and a moulded cover constructed from a flexible polymer.

Abstract: The present utility model discloses a full face dive mask, comprising a facial mask, a head strap connected with the facial mask and a respiratory pipe connected with the facial mask, wherein the side surface of the upper end of the facial mask is provided with a guide rail, the side surface of the lower end of the respiratory pipe is provided with a fixing shaft slidably connected with the guide rail, and the respiratory pipe is pulled outwards along the guide rail and revolved to fold in the facial mask. The utility model is simple in structure, small in size for the respiratory pipe can be folded to place, easy to store and capable of guaranteeing smooth breathing of a user.

Abstract: A first-stage diving regulator comprising the profiled body, swivel turret and the cylinder connector, whereas the axis of rotation of the swivel turret is perpendicular to the body axis, thus enabling by preferable arrangement of medium pressure LP ports and high pressure HP ports of the body, and preferable arrangement of medium pressure LP ports in the swivel turret and proper hose configuration at any possible equipment configuration by using the same first-stage regulator.

Abstract: A second stage diving regulator with separated stages that allows changing a position of connection of a LP hose for low/medium pressure supplied from a first stage of the regulator, characterized in that around connected bodies there is a rotating ring with a valve seat and a valve terminated with a threat to which a low/medium pressure LP coming from the first stage of the machine is connected horizontally. The rotation of the rotary ring is ensured at least in the range of 180 degrees from the starting position, through all the intermediate angles downwards towards the cylinder, up to a horizontal position opposite to the starting position, the side of the body.

Abstract: A submarine support ship is preferably a triple-hulled vessel; the lower portion of the ship is a paired-hull catamaran which is capable of deep diving, clasping the submarine at deep sea, and floating upwards together with the clasped submarine. The upper portion of the ship is a buoyancy tank, which can supply air to and pull up the deep-diving lower portion, and can also conduct security of an ocean-going submarine.

Abstract: Provided is a propeller for a submersible, comprising a housing (1) having a cylindrical structure with two open ends, a stator sleeve (2) having a cylindrical structure with one open end, the stator sleeve suspended in an internal cavity of the housing (1), a motor stator (3) fixed inside the stator sleeve (2), a rotor sleeve (4) having a cylindrical structure with one open end and disposed on the stator sleeve (2), a motor rotor (5) fixed to an inner wall of the rotor sleeve (4), and a propeller (6) fixed to an outer wall of the rotor sleeve (4). The propeller (6) of the underwater propeller is directly fixed to the rotor sleeve (4) so that the structure of the motor is compact, and the rotational shaft transmission is not required so that the length of the propeller is shortened and the volume is reduced.

Abstract: In a rotating electrical machine apparatus, a rotor portion provided in a cylindrical portion and a stator portion provided in a recessed portion in which the rotor portion is housed are aligned along the rotation axis of a rim such that a force is generated in a direction opposite to the direction of a load that acts along the rotation axis of the rim of loads that act on the rim following rotation of a blade.

Abstract: The present disclosure relates to a boat drive for driving a boat, comprising a drive unit comprising an electric motor and a mounting connected to the drive unit for connecting the boat drive to the boat, wherein the mounting is provided for distancing the drive unit from a hull of the boat, wherein a decoupling arrangement for decoupling of oscillations (S) generated in the drive unit is arranged between the drive unit and the mounting.

Abstract: A method of operating a wireless lanyard system on a marine vessel having at least one propulsion device includes defining a permitted zone with respect to a helm area where an operator should occupy based on one or more conditions of the marine vessel. Generating a location inquiry signal by a helm transceiver at the helm area of the marine vessel, and receiving an operator location signal from an operator fob worn by the operator of the marine vessel in response to the location inquiry signal. The method further includes determining whether the operator is within the permitted zone with respect to the helm area based on the operator location signal, and generating a lanyard event when the operator is not within the permitted zone. Upon generation of the lanyard event, the propulsion device is controlled to reduce an engine RPM to an idle RPM or the propulsion device is turned off.

Abstract: A lateral marine thruster is disclosed for mounting to an outboard motor. The lateral marine thruster has a bi-directional thruster with a central body portion and at least one propeller, the central body portion housing at least one high torque electric motor, which is rotatably coupled to at least one propeller, the rotational axis of the high torque electric motor and the propeller being oriented perpendicular to the centerline of the outboard motor. The bi-directional thruster is secured to the anti-cavitation plate or a similar mounting location of the outboard motor to provide lateral thrust for ease of docking or mooring a vessel.

Abstract: Aspects of the present disclosure present floor panels and floor panel assemblies that include incorporated burnthrough resistant materials and/or include burnthrough resistant layers applied to floor panels used in floor panel assemblies, along with methods for inhibiting fire penetration into compartments and methods of making and installing burnthrough resistant floor panels and floor assemblies including such apparatuses and methods as they relate to vehicles, including aircraft.

Abstract: Apparatuses for a projectile are provided, the projectile configured for weapons band launching, examples of the apparatus comprising a body, an inflation system and external walls. The body is inflatable by the inflation system, from a deflated configuration having a first volume to an inflated configuration having a second volume, greater than the first volume. The external walls are deployable from an undeployed configuration to a deployed configuration responsive to the body being inflated. In the undeployed configuration and at an operating airspeed, the center of pressure is located at a first position with respect to the projectile. In the deployed configuration the external walls provide a deployed external surface geometry exposed to an airflow corresponding to the operating airspeed, such that the center of pressure is located at a second position with respect to the projectile, different from the first position.

Abstract: An aircraft with stealth double wings comprises a main body and stealth double wings. The main body has two main wings respectively having a surface into which a space is formed. The stealth double wings respectively are located in the spaces and include a first and a second rotating shaft, a link rod, a first and a second wing. The link rod has two ends respectively connected with the two rotating shafts. The two rotating shafts respectively have another end connected with the first and second wings. Thereby, when the first wing is moved to cover and enclose the space's opening, the second wing is driven to be located within the space, and when the first wing is moved upwardly away from the space, the second wing is driven to cover and enclose the space's opening, so as to keep the surface intact.

Abstract: A camber adjustment system for a wing of an aircraft includes a droop panel that is configured to moveably couple to a portion of the wing, a flap, a cam rod moveably coupled to the droop panel, a bell crank cam arm moveably coupled to the flap, and a jackscrew interface between the cam rod and the bell crank cam arm. The droop panel is configured to move in response to movement of the flap via the jackscrew interface.

Abstract: Aircraft fly-by-wire systems and related vehicle electrical systems are provided. In one embodiment, an electrical system suitable for use with a control surface of a vehicle, such as an aircraft, is provided. The electrical system includes a plurality of communications buses and a plurality of control modules, wherein each of the plurality of control modules is connected to a respective subset of the plurality of communications buses that is unique among the plurality of control modules, and a plurality of actuation control modules associated with the control surface, wherein each of the plurality of actuation control modules is connected to a respective subset of the plurality of communications buses that is unique among the plurality of actuation control modules. Thus, each of the control modules is isolated from at least one of the communications buses.

Abstract: A flow body of an aircraft includes: a flow surface exposed to an airstream during flight of the aircraft, the flow surface generating at least one region of turbulent airflow during flight of the aircraft, at least one perforated area including a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings, and at least one suction duct having a first end and a second end, the first end being in fluid communication with the manifold, the second end including a suction opening and being arranged in the at least one region of turbulent airflow, wherein the suction opening is adapted for inducing a suction force in the at least one suction duct when the flow surface is exposed to an airstream during flight, thereby inducing a flow of air from through the plurality of openings.

Abstract: A fluid control system includes a deformable surface that covers a body in at least a first and second direction. The first direction is orthogonal to the second direction. The deformable surface includes a bottom side that faces the body and a top side that is opposite the bottom side. The fluid control system also includes at least one deformer between the deformable surface and the body. The at least one deformer is configured to modify a boundary layer of a fluid that is flowing over the deformable surface by selectively deforming the top side of the surface.

Abstract: A landing gear including an outer cylinder rotatably coupled to a frame of an aircraft about a trunnion axis of rotation, a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder, and a shrink mechanism including a first shrink link member pivotally coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member pivotally coupled to the outer cylinder, a drive member coupling the crank member to a walking beam (a.k.a. retract actuator beam) of a landing gear retract mechanism, and a driven member coupling the crank member to the first shrink link member.

Abstract: An aerial vehicle, such as an unmanned aerial vehicle, includes a fuselage having a forward end, an aft end, and a duct extending between said forward end and said aft end, said duct being oriented along a longitudinal axis of said fuselage; a primary propulsion unit mounted within said duct and generating lift for upward and downward motion while said fuselage is in a substantially vertical orientation and thrust for forward motion while said fuselage is in a substantially horizontal orientation; a plurality of airfoils each having a proximal end attached at opposite sides of the fuselage, said airfoils providing lift during forward motion of said fuselage; and a plurality of secondary propulsion units generating thrust to tilt the fuselage between said substantially vertical orientation and said substantially horizontal orientation.

Abstract: A hub for a rotary wing aircraft includes a plurality of rotor blades, and a heat dissipation system including an aerodynamic faring arranged outwardly of the hub. The aerodynamic fairing has an outer surface and an inner surface defining a component receiving zone. An electronic component is mounted to the inner surface of the aerodynamic faring in the component receiving zone.

Abstract: Disclosed herein are aspects of an unmanned aerial vehicle (UAV). In one embodiment, the UAV includes a container body having a cargo bay configured to hold cargo, and a plurality of rotor assemblies coupled to the container body. Each rotor assembly is configured to provide the container body with propulsion. A control system may be held by the container body and operatively connected to the rotor assemblies. The control system may be configured to fly the container body to a destination. The rotor assemblies may be moveable between a flight configuration and a shipping configuration. In the flight configuration, the rotor assemblies may extend outward from the container body such that the rotor assemblies are positioned to propel the container body through the air. In the shipping configuration, the rotor assemblies may be folded to the container body such that the container body is configured to be shipped to a destination.

Abstract: Techniques to control flight of an aircraft are disclosed. In various embodiments, a set of inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is determined, including by minimizing a weighted set of costs that includes costs associated with one or more errors each corresponding to a difference between a requested force or moment and a corresponding force or moment achieved by the computed solution.

Abstract: An aircraft comprising fixed wings, an upper rotor system, and a lower rotor system. The upper rotor system comprises only one upper blade. Furthermore, the upper rotor system is configured to rotate the upper blade in a clockwise rotational direction about a yaw axis of the aircraft in a vertical take-off mode, and halt rotation of the upper blade in a first rearward orientation parallel to the roll axis of the aircraft in a high-speed cruise mode. The lower rotor system comprises only one lower blade. Additionally, the lower rotor system is configured to rotate the lower blade in a counter-clockwise rotational direction, opposite the clockwise rotational direction, about the yaw axis in the vertical take-off mode, and halt rotation of the lower blade in a second rearward orientation parallel to the roll axis in the high-speed cruise mode.

Abstract: A tiltrotor aircraft may be provided and may include a mast assembly, in which the mast assembly may include a mast; a bearing system; a housing; and a housing cap secured to the housing, wherein the bearing system is between the mast and the housing. The bearing system may further include a first bearing assembly including a first inner race, a first outer race, and a plurality of first tapered roller bearings; a second bearing assembly including a second inner race, a second outer race, and a plurality of second tapered roller bearings; an inner spacer and an outer spacer in which the inner and outer spacers are between the first and second bearing assemblies; and a retaining device in which the retaining device and the housing cap provide, at least in part, pre-loading for the first and second bearing assemblies.

Abstract: A vertical takeoff and landing (VTOL) light aircraft comprising: a tilt-wing comprising port and starboard wings; a power train having: an electric motor coupled to a rotor for providing the aircraft with thrust for flight mounted to each of the port and starboard wings; a battery configured to store electric energy to power the electric motors; an electric generator, and a combustion engine configured to drive the generator to produce electric energy for storage in the battery; and a controller configured to autonomously control the tilt-wing and power train to provide VTOL takeoffs and landing having relatively short hover periods.

Abstract: Systems and methods for autonomously herding birds in accordance with embodiments of the invention are illustrated. One embodiment includes an autonomous flock herding system, including a bird location sensor, a drone; and a control system, including a processor, and a memory, the memory containing a flock herding application, where the application directs the processor to obtain bird position data from the at least one bird location sensor, where the bird position data describes the location of birds in a flock of birds, determine if the flock of birds will enter a protected zone, generate a set of waypoints using a flock dynamics model, instruct the unmanned aerial vehicle to navigate to at least one waypoint in the set of waypoints such that the flock of birds will, in response to the presence of the unmanned aerial vehicle at the at least one waypoint, change trajectory away from the protected zone.

Abstract: Embodiments herein describe a reconfigurable UAV to allow for the deployment of a subsurface sensor. The UAV includes a rotor assembly that is slidably coupled to a landing base. The rotor assembly includes a plurality of rotors and a ring circumscribing the rotors. Upon landing, the rotor assembly rotates in a first direction with respect to the landing base, which reduces a spacing between the rotor assembly and the ground and drives a sensor coupled to the rotor assembly into the ground. To remove the sensor from the ground, the rotor assembly rotates in a second direction to increase the spacing between the rotor assembly and the ground. The ring and/or the landing base may include interlocking features such as helical threads that are utilized to translate a rotational motion of the rotor assembly into a linear translation of the rotor assembly along the length of the landing base.

Abstract: A multi-rotor unmanned aerial vehicle (UAV) comprises: a fuselage; a plurality of rotor mechanisms disposed on the fuselage, each rotor mechanism including a rotor; and a plurality of connection mechanisms disposed on the fuselage. The plurality of connection mechanisms have a one-to-one correspondence with the plurality of rotor mechanisms, each connection mechanism corresponding to one of the plurality of rotor mechanisms. Each rotor mechanism is movably connected to the fuselage through the corresponding connection mechanism; and the plurality of rotor mechanisms are configured to be rotated with respect to the corresponding connection mechanisms to cause the plurality of rotor mechanisms to overlap with each other and form a rotor mechanism assembly.

Abstract: A computer is programmed to deploy an aerial drone to fly within a specified distance of a first vehicle. The computer is programmed to detect a second vehicle and then activate an aerial drone light.

Abstract: A disposable unmanned aerial glider (UAG) with pre-determined UAG flight capabilities. The UAG comprises a flight module comprising at least one aerodynamic arrangement; and a fuselage module comprising a container configured for storing therein a payload and having structural integrity. The container is pressurized so as to maintain structural integrity thereof at least during flight, so that the UAG flight capabilities are provided only when the container is pressurized.

Abstract: Systems and methods for authenticating a user include monitoring a monitored space for a condition to provide an interaction between a drone and an individual. In response to the condition to provide the interaction between the drone and the individual being satisfied, the drone may obtain a first set of sensor data corresponding to the individual. The first set of sensor data may indicate that the individual requires a service that requires authentication of the individual as a user of the service and that the individual is unable to provide a primary authentication response. The drone may then obtain a second set of sensor data corresponding to the individual unable to provide the primary authentication response. The drone authentication system then determines, based on the second set of sensor data and identity data that the individual corresponds to identity data of a user of the service and performs the service.

Abstract: A computer that includes a processor and memory which stores instructions executable by the processor. The instructions include: initiate, from a vehicle, a fuel delivery request for fuel delivery by an unmanned aerial vehicle (UAV); in response to the initiation, instruct a communication module in the vehicle to transmit a beacon signal to enable the UAV to locate the vehicle; and coordinate a docking procedure between the UAV and the vehicle to receive fuel from the UAV.

Abstract: Payload engagement systems and related methods. A payload engagement system includes a vehicle with at least one engagement latch and a payload with at least one engagement receptor. Each engagement latch is configured to be selectively transitioned between an engaged configuration and a disengaged configuration. The payload engagement system includes an alignment guide configured to guide the payload to a predetermined coupling position prior to each engagement latch transitioning to the engaged configuration. A method of utilizing a payload engagement system includes positioning a vehicle on a first side of a docking platform, guiding a payload toward the vehicle, and coupling the payload to the vehicle via engagement between at least one engagement latch and at least one engagement receptor. Specifically, the coupling the payload to the vehicle includes transitioning each engagement latch from a disengaged configuration to an engaged configuration.

Abstract: Vehicle docking systems, payload transfer systems, and related methods. A vehicle docking system includes a vehicle with a plurality of docking insert units and a docking platform with a plurality of docking receptor units. Each docking receptor unit is configured to transition between an unlocked configuration and a locked configuration. A method of utilizing a vehicle docking system includes bringing a vehicle to a docked position on a docking platform and securing the vehicle in the docked position. The docking platform includes a plurality of docking receptor units and the vehicle includes a plurality of docking insert units, each docking receptor unit configured to receive a corresponding docking insert unit. The securing the vehicle in the docked position includes transitioning each docking receptor unit from an unlocked configuration to a locked configuration. A payload transfer system includes a payload engagement system and a vehicle docking system.

Abstract: The invention relates to a system for remote monitoring of an area intended to accommodate at least one passenger of an aeroplane, notably a cargo area provisionally converted into cabin space, including: at least one control member configured to generate at least one signal relating to the safety of the passenger present in the area, and at least one interface means that is situated at a distance from the area and allows the cabin crew to have access to information relating to the area and/or to the passenger present in the area on the basis of the signal.

Abstract: A fastening system for passenger seats in a vehicle cabin has two or more guide rails to be integrated into or onto a cabin floor, and a plurality of slides, to be brought into engagement with the guide rails and having a flange for connection to a passenger seat in order to retain the passenger seat on a guide rail. Each guide rail has a profile cross section, perpendicularly to a main axis of extent, having a base region and a supporting region. Each slide has a cavity of complementary design with the profile cross section. The guide rails have a plurality of transverse openings spaced apart from one another between the base region and the supporting region. At least one slide has a displaceably mounted retaining body which, when the slide is in engagement with the guide rail, can be brought into engagement with one of the transverse openings.

Abstract: A vane assembly for distribution of a stratified fluid in an aircraft is taught herein. The vane assembly includes a housing including a housing inlet and a housing outlet. The housing inlet is configured to receive the stratified fluid with the stratified fluid including a first portion and a second portion. The housing outlet is configured to exhaust the stratified fluid. The housing defines an interior housing volume between the housing inlet and the housing outlet. The vane assembly further includes a vane disposed within the interior housing volume and bisecting the interior housing volume. The vane includes a leading edge adjacent the housing inlet and a trailing edge adjacent the housing outlet. The trailing edge is angularly offset from the leading edge.

Abstract: A mixer assembly for mixing two air streams in a ventilation system. The mixer assembly comprises a mixing chamber, which comprises an inlet and an outlet and a mixing chamber wall delimiting the mixing chamber, and also a shroud, which surrounds the mixing chamber wall, at least in certain portions. The shroud forms and delimits an intermediate space between the mixing chamber wall and the shroud. The mixer assembly also comprises a filter element, which fluidically connects the intermediate space to a surrounding area of the mixer assembly, the intermediate space being fluidically connected to the mixing chamber. Fluid can thus flow through the filter element into the intermediate space and further into the mixing chamber. A stowage space with a mixer assembly, an aircraft with such a stowage space and a method for producing a mixer assembly in an aircraft are also described.

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

Abstract: An aircraft (A) comprising at least a component part (1, 2, 3, 4, 5, 6, 7, 8) provided with thermal de-icing means (S) suitable to eliminate and/or prevent the formation of ice on said component part, said de-icing means (S) are directly integrated in the structure of said part (1, 2, 3, 4, 5, 6, 7, 8).

Abstract: A power system of an aircraft includes a hybrid energy storage system with at least two energy storage subsystems each having a different power-energy density. The power system also includes one or more electric motors operably coupled to the hybrid energy storage system and to an aircraft engine. The power system further includes a means for controlling one or more electric power flows of the hybrid energy storage system to/from the one or more electric motors based on a modeled electric power demand associated with an engine load of one or more spools of the aircraft engine.

Abstract: A method and to a device for managing energy of a hybrid power plant of a multi-rotor aircraft during a flight. The hybrid power plant comprises a thermal engine, an electricity generator, and a plurality of electric motors, together with a plurality of electrical energy storage devices. The aircraft has a plurality of rotors driven in rotation by respective electric motors. The flight of the aircraft comprises a takeoff stage, a cruising stage, and a landing stage, the takeoff stage and the landing stage being performed solely while consuming electrical energy. The method enables an electrification ratio RElec of the flight to be calculated as a function of the amounts of electrical and thermal energy that are consumed during the takeoff, landing, and cruising stages, thereby limiting the use of the thermal engine to the least possible amount during the cruising stage, and consequently reducing the associated nuisance.

Abstract: An assembly for an aircraft comprising a pylon having a mounting plate having a front face and a rear face and through which there passes, between the front face and the rear face, at least one central bore, a front engine mount comprising a spar with a rear face bearing against the mounting plate front face and which, for each central bore, has a complementary central bore aligned with the central bore, and for each central bore, a mounting system. The mounting system comprises a shear pin inserted into the central bore and the complementary central bore from the rear face with a flange bearing against the rear face, a support with a central hole, the diameter of which is greater than the flange diameter and fixed to the rear face, and a cap fixed to the support closing off the central hole and bearing against the shear pin.