Abstract: A sports-related measurement system that can include a forward facing camera, a global positioning satellite receiver, and the necessary data collection and processing capabilities to calculate the aerodynamic drag of a moving object. The data collected can include altitude, air pressure, air moisture content, temperature, and the like. The system can include a display for presenting data to the user and may also include memory for storage of data, photos, video, and the like. In some embodiments, the system may be configured as a bicycle computer adapted to mount on a bicycle.

Abstract: A sports-related measurement system that can include a forward facing camera, a global positioning satellite receiver, and the necessary data collection and processing capabilities to calculate the aerodynamic drag and cyclist applied power of a moving object, such as a bicycle. The data collected can include altitude, air pressure, air moisture content, temperature, and the like. The system can include a display for presenting data to the user and may also include memory for storage of data, photos, video, and the like. In some embodiments, the system may be configured as a bicycle computer adapted to mount on a bicycle.

Abstract: A scooter is provided. The scooter may include a front wheel assembly, a pair of connector elements, and a pair of rear wheel caster assemblies. The pair of connector elements may be cooperable with the front wheel assembly for lateral movement relative thereto. Each of the pair of rear wheel caster assemblies may be secured to a rear portion of one of the connector elements and may have a caster defining a caster axis and a rear wheel mounted for rotation to the caster. The front wheel assembly and connector elements may be arranged with one another such that adjustment of a height of a front portion of each of the connector elements adjusts an angle of the respective caster axis relative to an underlying surface. The scooter may include a lock mechanism to selectively engage the connector elements and to facilitate transition between multiple types of scooter movement.

Abstract: A motorized foldable bicycle assembly is foldably collapsible from a ridable elongated, segmented four sectioned frame arrangement. The frame consisting of a front wheel support frame, a front frame, a mid frame and a rear wheel support frame, with a set of electronically controlled motorized front and rear wheels spaced longitudinal alignment, apart one on each end of the four-sectioned elongated frame arrangement. The frame sections are foldable into an unridable configuration wherein the front wheel and a displaced rear wheel are arranged in an aligned, side-by-side adjacent, tandem configuration controllably guided by a steering column supported handlebar motor speed and direction control arrangement. A bicycle-supported tilt sensor actuator is in communication with a control computer and a circuit electronically connected to a bicycle handlebar switch, to permit operator controlled non-riding, self-powered, electric-motor-engaged movement of the tilted, partially foldably collapsed bicycle.

Abstract: Disclosed is a thumb switch for operating a mobile communication device and/or electric components of a vehicle, said thumb switch comprising a housing, on which at least one operating element is arranged. In order to allow for ease of operation, the thumb switch has communication electronics for generating control signals for functions that can be carried out on the mobile communication device and/or on at least one electrical component of the vehicle. The invention further relates to control system comprising such a thumb switch.

Abstract: An axle assembly including: an axle sleeve having first and second end faces, an axially extending through opening, and a radially extending first engagement surface; and a control shaft extending within the opening and having a radially extending second engagement surface. The control shaft is axially displaceable relative to the axle sleeve and is axially retained to the axle sleeve by means of an overlie engagement between the first and second engagement surfaces. At least one of the first and second engagement surfaces is radially displaceable between an engaged orientation corresponding to the overlie engagement and a released orientation corresponding to a release of the overlie engagement. The overlie engagement serves to axially retain the control shaft to the axle sleeve and the released orientation serves to remove the overlie engagement and permit the control shaft to be axially withdrawn and separated from the axle sleeve in the retracting direction.

Abstract: A bicycle hydraulic operating device is basically provided with a base member, a piston, an operating member and a hydraulic reservoir. The base member includes a cylinder bore. The piston is movably disposed in the cylinder bore. The operating member coupled to the piston to move the piston within the cylinder bore. The hydraulic reservoir includes a hydraulic reservoir tank and a reservoir lid. The hydraulic reservoir tank is fluidly connected to the cylinder bore. The reservoir lid closes a tank opening of the hydraulic reservoir tank. The tank opening defines an opening cross sectional area. The hydraulic reservoir tank defines a tank cross sectional area parallel to the opening cross sectional area. The opening cross sectional area of the tank opening is smaller than the tank cross sectional area of the hydraulic reservoir tank.

Abstract: A bicycle hydraulic operating device is basically provided with a base member, a piston, an operating member, a hydraulic reservoir tank and a diaphragm. The base member includes a cylinder bore. The piston is movably disposed in the cylinder bore. The operating member is coupled to the piston to move the piston within the cylinder bore. The hydraulic reservoir tank is fluidly connected to the cylinder bore. The diaphragm is at least partially disposed inside the hydraulic reservoir tank and divides the hydraulic reservoir tank into a hydraulic fluid chamber and an air chamber. The air chamber is at least partially located closer to the cylinder bore than the hydraulic fluid chamber.

Abstract: A torque sensor system for a pedelec includes an annular gear (6), a planetary gear train (5), a sun gear output shaft (2), a pressure conversion device (9) and a signal processing component (8). The annular gear (6), the planetary gear train (5), and the sun gear output shaft (2) are engaged in turn. The annular gear (6) is driven by the planetary gear train (5), and an applied force signal is transmitted to the signal processing component (8) via the pressure conversion device (9) at an edge of the annular gear (6). The applied force signal is converted to an electric signal by the signal processing component (8) and transmitted to a controller, so as to realize a torque feedback. As a result, a problem that a speed sensor is not applicable to a pedelec when climbing is solved; and a user will feel real and comfortable when riding.

Abstract: The invention relates to a drive unit for fitting or retrofitting a two-wheeled vehicle (1), preferably a bicycle, having an electric motor which is designed as a disc motor (10), comprising a rotor disc (11) having permanent magnets (12) and an annular stator (13) with windings, which generate an electrical alternating field for driving the rotor disc (11), wherein the rotor disc (11) can be fastened non-rotatably to a receptacle (6) on the front or rear wheel of the two-wheeled vehicle (1) and the annular stator (13) can be fastened to a frame part (4, 5) of the two-wheeled vehicle (1). For tool-free dismantling the annular stator (13) can be unfolded in the circumferential direction and can be removed or pulled off from the rotor disc (11).

Abstract: Apparatuses and methods relating to hub motors having enhanced thermal characteristics may include a hub motor having a stator comprising steel and a central axle (e.g., a mandrel and shaft) comprising a material with a substantially higher thermal conductivity than the stator (e.g., aluminum). Heat may be transferred from the stator through the axle of the motor to an outside heat sink. Manufacturing of thermally enhanced hub motors may include extrusion and/or cryogenic fitting methods relating to the central mandrel and shaft.

Abstract: A multiple bicycle sprocket assembly is basically provided with a first sprocket supporting member and a second sprocket supporting member. A first sprocket is coupled to one of a first bicycle inbound facing side and a first bicycle outbound facing side of the first sprocket supporting member, and is a separate member therefrom. A second sprocket is coupled to one of a second bicycle inbound facing side and a second bicycle outbound facing side of the second sprocket supporting member, and is a separate member therefrom. At least one fastening member connects the first sprocket supporting member and the second sprocket supporting member, and is a separate member therefrom. At least one hub engaged sprocket is free from connection with the at least one fastening member, and is a separate member from the first and second sprocket supporting members.

Abstract: A multihull sailing vessel includes at least two buoyant hulls extending along their longitudinal axes, with the hulls being connected to each other and a first hydrofoil connected to the hulls and oriented transverse to the hulls. The first hydrofoil is movably coupled to the hulls between a first position above a resting waterline of the hulls and a second position below a lowest extent of the hulls. When the first hydrofoil is in the second position, a configuration of the first hydrofoil is adjustable to vary an amount of lifting force generated by the first hydrofoil when the hulls move forward through water when the first hydrofoil is in the second position.

Abstract: A watercraft comprising: a chassis; a drive means; a hydrofoil; and a drive transfer arm, wherein the drive means is operatively connected to a first end of the drive transfer arm, and the hydrofoil is pivotably connected to a second end of the drive transfer arm, the watercraft configured such that operation of the drive means causes the hydrofoil to oscillate, to provide thrust.

Abstract: The present invention discloses a bionic high holding power anchor, which includes an anchor rod, a suspension clasp coupled with one end of the anchor rod and an anchor fluke hinged with the other end of the anchor rod, wherein a plurality of fluke heads arranged at equal intervals are extended from a front end of the anchor fluke, fin-like streamlined balance wings are arranged at two sides of the anchor fluke; the fluke head is in a shape of triangle-like taper containing a plane side wall and two curved side walls, the plane side wall is an isosceles triangle, the two curved side walls are smooth curved surfaces, and the two smooth curved surfaces are symmetrical around a normal plane of the plane side wall.

Abstract: An emergency vessel towing system includes a vessel attachment system, a retrieving system, and a towing line. The vessel attachment system is configured to connect to a vessel at sea, and includes a bridle system and a hawser line. The bridle system is operatively connected to the hawser line's proximal end. The bridle system is configured to engage at least four fittings on a foredeck of the vessel to distribute the load over the foredeck. The retrieving system includes a retrieving line with a proximal end that is detachably connected to the hawser line's distal end in a setup position. The towing line is detachably connected to the hawser line's distal end in a towing position.

Abstract: An emergency ship arrest system includes a vessel attachment system, a retrieving system, and an anchor system. The vessel attachment system is configured to connect to a vessel at sea, and includes a bridle system and a hawser line. The bridle system is operatively connected to the hawser line's proximal end. The bridle system is configured to engage at least four fittings on a foredeck of the vessel to distribute the load over the foredeck. The retrieving system includes a retrieving line with a proximal end that is detachably connected to the hawser line's distal end in a setup position. The anchor system includes a main rode and a para sea anchor. The main rode's proximal end is detachably connected to the hawser line's distal end in an anchor position.

Abstract: The invention relates to a hull of a vessel having characteristic surface properties, allowing an increase in surface runoff while benefiting from an inherent anti-fouling property and an original aesthetic appearance. Furthermore, the invention allows the incorporation of said outer composite envelope into the structure of the hull, thereby preventing delamination problems and inherently providing a vessel hull with the above-mentioned properties.

Abstract: The invention relates to a device for viewing underwater objects without getting wet while experiencing the sensation of walking on water. The device comprises an inflated raft with a clear bottom designed to allow a person to sit or lie face down and view underwater objects while experiencing the movement of the water without getting wet. This clear bottom has no air pockets and is flexible, thus the person receives the sensation of walking on water instead of air.

Abstract: An apparatus for sweeping influence mines, including an operating unit having a plurality of propulsion devices designed to be immersed in water and at least one floating body connected to the propulsion devices, the latter being designed to overcome the hydrostatic thrust acting on the floating body to keep the operating unit immersed at a predetermined depth.

Abstract: A jet propelled watercraft includes a watercraft body, an engine housed in the watercraft body, a jet propulsion unit that suctions and jets water with a drive force of the engine, a first exhaust pipe connected to an exhaust port of the engine, and a catalyst storage connected to the first exhaust pipe, wherein the first exhaust pipe and the catalyst storage are integral and unitary with each other.

Abstract: An outboard motor and methods of use thereof in general, includes a powerhead removeably affixed to the transom of a boat, and a gear case rotationally connected to a propeller shaft, the outboard motor including a telescopic drive shaft, the telescopic drive shaft having a first drive shaft section rotationally connected to the motor and a second drive shaft section rotationally connected to the gear case, and a telescopic drive shaft housing, the telescopic drive shaft housing configured to support the telescopic drive shaft internally therethrough, whereby the telescopic drive shaft and the telescopic drive shaft housing are configured to provide depth adjustment for the gear case and the propeller shaft, and thus enable the propeller to be raised and lowered during propulsion to improve propulsion efficiency.

Abstract: An outboard-motor vibration-isolating cooler system apparatus providing a retrofit substitute for the midsection and the lower unit of a standard outboard motor, having a substitute closed-loop cooling system with an exterior heat exchanger, a substitute oil reservoir, a substitute exhaust system, and a substitute propulsion system with an isolating power-take-off shaft, allowing an existing standard outboard-motor powerhead to be used in conditions not conducive to standard open-loop water cooling, such as shallow-water, muddy-water, obstructed-water, seawater, or corrosive-water conditions.

Abstract: A jet propelled watercraft includes a first exhaust pipe connected to an exhaust port, a catalyst storage connected to the first exhaust pipe, a second exhaust pipe connected to the catalyst storage, and a water lock connected to the second exhaust pipe. The catalyst storage and the water lock are located outward in a width direction with respect to the exhaust port of the engine in a plan view of the jet propelled watercraft.

Abstract: The present invention is realized by apparatus and methods for harvesting, storing, and generating energy by permanently placing a large rigid buoyant platform high in the earth's atmosphere, above clouds, moisture, dust, and wind. Long, strong and light tethers can connect the buoyant structure to the ground which can hold it in position against wind forces. Weights suspended from the buoyant platform with cables are raised and lowered by electric winches to store and release gravitational potential energy. High voltage transmission lines electrically connect the platform to the earth's surface. Electrical energy from the high voltage transmission lines or from photovoltaic arrays on the platform can be stored as gravitational potential energy and subsequently released as electricity from generators driven from the stored gravitational potential energy and used on the platform or transmitted via the high voltage transmission lines.

Abstract: A pressure bulkhead for an aircraft includes a wall assembly. The wall assembly includes a first wall section which extends in a direction nonparallel to a length of the aircraft. The wall assembly further includes a second wall section secured to the first wall section wherein the second wall section includes a curved shape. The curved shape includes a convex portion which extends further along the length of the aircraft in a direction toward the aft end of the aircraft than the first wall section. A method for assembling a pressure bulkhead is also provided.

Abstract: A dry bay sealing assembly is provided that includes a first end plate and a second end plate that are configured to be disposed on respective opposite first and second sides of a structural member proximate to a joint defined between the structural member and a fitting. The first end plate and the second end plate are configured to define an interior volume therebetween containing at least a portion of a fastener joining the structural member and the fitting. The first end plate and the second end plate are configured to cooperate with the structural member to seal the interior volume from an exterior volume.

Abstract: An aircraft includes a structure exhibiting a median plane XZ and including a fuselage, a fixed vertical stabilizer at the rear of the fuselage, an adjustable horizontal stabilizer rotatably mounted about a horizontal axis on a first section of the structure, and extending on either side of the median plane XZ, and at the rear, two elevators mounted rotatably about a horizontal axis on a second section of the structure on either side of the median plane XZ independently of the adjustable horizontal stabilizer. In an aircraft of this kind, the elevators no longer have any impact on the adjustable horizontal stabilizer, which allows, among other things, the dimensions of the adjustable horizontal stabilizer, and also of the actuator operating them, to be reduced.

Abstract: An aircraft wing incorporating an active flow control (AFC) device The AFC device comprises a fluid chamber housed in the wing providing a conduit for receiving fluid and accommodating the fluid at elevated pressure. Forward and rearward fluid channels having respective inlets and outlets are also provided, wherein the inlets are in fluid communication with the fluid chamber and the outlets emerge on the upper surface of the wing at or adjacent the leading edge. A valve assembly allows the channels to be opened and closed as desired. During flight, fluid at elevated pressure can be supplied to the fluid chamber and released through either the forward or the rearward fluid channel or both, so as to influence the air flow, e.g., to reduce or increase lift, or to equalize pressure in the air stream direction.

Abstract: A control circuit for changing the angle of propeller blades includes a propeller control unit controlling a supply of oil to modify an angle of propeller blades, and a fixed-displacement pump providing the supply of oil from an engine oil return system to the propeller control unit. An oil cooling line extends between an outlet of the pump and the engine oil return system. The oil cooling line defines an oil leakage path leading to the engine oil return system for cooling the oil. A flow regulator between the pump and the propeller control unit is operable between an open position where oil is directed through the oil cooling line to the engine oil return system for cooling the oil, and a closed position blocking the oil cooling line and directing oil toward the propeller control unit to modify the angle of the propeller blades.

Abstract: A self-adjusting flight control system is disclosed. In various embodiments, an input interface receives an input signal generated by an inceptor based at least in part on a position of an input device comprising the inceptor. A processor coupled to the input interface determines dynamically a mapping to be used to map input signals received from the inceptor to corresponding output signals associated with flight control and uses the determined mapping to map the input signal to a corresponding output signal. The processor determines the mapping at least in part by computing a running average of the output signal over an averaging period and adjusting the mapping at least in part to associate a neutral position of the input device comprising the inceptor with a corresponding output level that is determined at least in part by the computed running average.

Abstract: A positioning and position maintaining device comprises a solenoid having an armature and an electromagnetic holder. The solenoid is arranged to effect positioning of an object upon translation of the armature and the electromagnetic holder is arranged to effect position maintaining in order to maintain the object in the position effected by the solenoid. An apparatus for aircraft autopilot and manual control feel-force control switching comprises an autopilot mechanism and the positioning and position maintaining device. The positioning and position maintaining device is arranged to engage the autopilot mechanism and maintain the engagement thereof. A method of switching between autopilot and manual control in an aircraft is also envisaged.

Abstract: A joint for coupling a wing tip to a wing base includes a linking member that extends from a first end to a second end. The linking member first end is coupleable to the wing base, and the linking member second end is coupleable to the wing tip. The linking member defines first second hinge lines that are substantially parallel. The joint also includes at least one actuator. A first end of each at least one actuator is coupled to the linking member, and a second end of each at least one actuator is coupleable to one of the wing base and the wing tip. The at least one actuator is operable to rotate the wing tip about the first and second hinge lines between a first orientation and a second orientation relative to the wing base.

Abstract: A thin-skin support member is provided. The thin-skin support member may include a semi-circular edge and a flat edge that define a hollow cavity. A cylindrical cavity may be adjacent the hollow cavity and at least partially defined by the semi-circular edge. The cylindrical cavity may be configured to retain a strut assembly. A mounting interface may be coupled to the semi-circular edge and the flat edge. A torsion interface may be disposed adjacent the cylindrical cavity and configured to receive a torsion link. The thin-skin support member may be made using additive manufacturing and thus may have a grain structure grown in the direction of material being added.

Abstract: A landing gear assembly is also provided. The landing gear assembly may include a thin-skin support member defining a cavity and a cylindrical cavity. A cylinder may extend from the cylindrical cavity with an axle extending from the cylinder. A torsion link may be coupled to the axle and a torsion interface of the thin-skin support member.

Abstract: An auxiliary rotating structure adapted for a tire of an aircraft includes a first side wall and a second side wall. The first side wall is fixed on a wall of the tire and rotates along with the tire. A side of the second side wall is connected to a side of the first side wall to form a chamber between the first side wall and the second side wall. An opening is formed between the other side of the first side wall and the other side of the second side wall and communicated with the chamber. The second side wall is made of resilient material. When the auxiliary rotating structure is located at a lower side of the tire, an air flow passes through the opening into the chamber to generate a first torque along a first rotary direction for rotating the tire.

Abstract: A rotor system is provided including a rotor hub configured to rotate about an axis and a plurality of rotor blade assemblies mounted to the rotor hub and configured to rotate within a plane about the axis. A vibration reducing system is operably coupled to the rotor hub. The vibration reducing system is arranged at a position offset from a center of rotation of the rotor hub.

Abstract: A rotary-wing drone includes a drone body that includes an electronic board controlling the piloting of the drone, and four link arms that include a rigidly connected propulsion unit. The link arms form lift-producing wings.

Abstract: A drone package receiving system is provided, utilizing a package-to-receiver system coupler that mates to a receiver pole. The coupler is attached to the drone package and “clips” onto the receiver pole to secure the package from the drone. The receiver pole is affixed to receptacle that is at a “customer-side” end of the pole, wherein the package is translated from the pole's end into the receptacle for safe and hands-free delivery to the customer.

Abstract: The present invention relates;—to a drone comprising a fuselage (1) provided with a carrying means (11, 12) capable of allowing a belly-to-ground flight position and an inverted flight position, at least one propulsion means (2), autonomous navigation instruments and an axial compartment (10) forming a recess incorporated into an upper part of the fuselage in order to receive a parachutist (h) in the lying position, avionics provided with programmable control means coupled to the autonomous navigation instruments and means for releasing said parachutist controlled by said avionics, characterised in that said release means are designed and intended to ensure the release of said parachutist in the inverted flight position, and,—to a piece of airborne intervention equipment.

Abstract: The present disclosure relates to a flying vehicle comprising an annular hollow outer body having an outer circumferential open portion and an inner circumferential open portion; a blade system disposed in the outer body and configured to allow air flow from the outer circumferential open portion to the inner circumferential open portion; a first magnetic system configured to enable the blade system to be kept to have a clearance with the annular hollow outer body and to be kept in a floated state using a first magnetic force; a second magnetic system configured to allow the blade system to rotate using a second magnetic force; and a steering system configured to allow air discharged from the inner circumferential open portion via the blade system to flow upwardly or downwardly.

Abstract: An air cushion cargo shuttle includes a frame having a channel, an air curtain disposed within the channel of the frame, an air blower configured to blow air into an air volume beneath the air cushion cargo shuttle, and an air cushion formed by the air curtain configured to maintain the air volume.

Abstract: An expandable cargo storage for a transportation means, comprising a first storage wall and a second storage wall opposite of the first storage wall, and a plurality of foldable walls arranged between the first and the second storage wall, each of the plurality of foldable walls being foldable between a first position in which the respective foldable wall is arranged essentially in parallel with the second storage wall, and a second position in which the foldable wall is arranged essentially perpendicularly to the second storage wall, wherein, when each of the foldable walls is arranged in its first position, the cargo storage is in a first operational state enclosing a first volume, and when each of the foldable walls is in its second position, the cargo storage is in a second operational state enclosing a second volume which is larger than the first volume.

Abstract: Described are headrests with integrated entertainment systems. The headrest includes a shell that is coupled to a seat through a headrest mount that has at least one degree of freedom of movement. The headrest shell also supports a visor with at least one side arm and a display span that may rotate between stowed and deployed positions. A neutral position mechanism supports the headrest in a neutral position and provides resistance to movement between the headrest and the passenger seat. The attachment of the visor to the headrest shell may also include an adjustment slot to allow fore and aft translation of the visor with respect to the headrest shell. The fore and aft translation of the visor allows for positioning the visor at different focal lengths, and provides extra clearance for the visor as it moves between stowed and deployed positions.

Abstract: A table (30) for an aircraft includes a table surface (56) deployable between a retracted position and a deployed position, an arm (50) having a first end and a second end, the arm (50) supporting the table (66) surface at the first end, a support connected to the arm (50) at the second end, the support connecting the arm to a structure interior to the aircraft, a sensor (136) within the aircraft to detect if a seat adjacent to the table surface is occupied, and a mechanism (120) for retracting the table surface to the retracted position if the sensor (36) detects at least one of that the seat is not occupied and that the aircraft flight mode meets predetermined criteria.

Abstract: An airfoil (100) comprises a skin (110), comprising an external surface (112) and an internal surface (114), opposite the external surface (112). The skin (110) is magnetically and electrically conductive. The airfoil (100) also comprises an interior space (108), formed by the skin (110). The internal surface (114) faces the interior space (108). The airfoil (100) additionally comprises a leading edge (106) along the external surface (112). The airfoil (100) further comprises a hybrid acoustic induction-heating system (102), configured to impede formation of ice on the external surface (112). The hybrid acoustic induction-heating system (102) comprises an induction coil (130) within the interior space (108). At least a portion (136) of the induction coil (130) is sufficiently close to the internal surface (114) to produce an eddy current (180) in the skin (110) when an alternating electrical current (134) is flowing in the induction coil (130).

Abstract: An airfoil (200) comprises a skin (210), comprising an external surface (212) and an internal surface (214). The skin (210) has a controlled region (216). The airfoil (200) also comprises an interior space (208), formed by the skin (210). The airfoil (200) additionally comprises a hybrid acoustic induction-heating system (202), configured to impede formation of ice on the external surface (212). The hybrid acoustic induction-heating system (202) comprises an induction coil (230) and a control system (250). At least a portion (236) of the induction coil (230) is sufficiently close to the internal surface (214) to produce an eddy current (280) within the controlled region (216) when an alternating electrical current (234) is flowing in the induction coil (230).

Abstract: An airfoil (300) comprises a skin (310), comprising an external surface (312) and an internal surface (314). The skin (310) has a controlled region (316). The airfoil (300) also comprises an interior space (308), formed by the skin (310). The airfoil (300) additionally comprises a hybrid acoustic induction-heating system (302), configured to impede formation of ice on the external surface (312). The hybrid acoustic induction-heating system (302) comprises induction coils (328) and a control system (350). Each one of the induction coils (328) has a portion (336), arranged sufficiently close to the internal surface (314) to produce an eddy current (380) within the controlled region (316).

Abstract: A method (400) of impeding formation of ice on an exterior surface (104, 204, 304) of airfoil (100, 200, 300) is disclosed. The method (400) comprises detecting (402) first ambient conditions known to cause the ice to form on exterior surface (104, 204, 304). The method (400) also comprises supplying (404) inductive heat and acoustic pressure to exterior surface (104, 204, 304) when the first ambient conditions are detected. The method (400) additionally comprises detecting (406) second ambient conditions known to impede the ice from forming on exterior surface (104, 204, 304). The method (400) further comprises discontinuing (408) to supply the inductive heat and the acoustic pressure to exterior surface (104, 204, 304) when the second ambient conditions are detected.

Abstract: In order to further benefit from the principle of boundary layer ingestion by engines of an aircraft assembly, the rear portion of the fuselage of this aircraft assembly includes a front portion which splits up into at least two distinct rear portions, spaced apart from each other, and each integrating the rotary ring of the receiver of one of the engines.