Abstract: The present disclosure refers to an anti-slip pad for a sliding sports board, as for example water sports boards, snowboards or skateboards, said pad comprised mostly of cork.

Abstract: A floating vessel modular protection and security device includes a stationary bowed frame configured to be positioned over a floating vessel, the stationary frame and a moveable bowed frame. A stationary flexible cover extends from one end to the other end of the stationary bowed frame, covering stationary crossbeams. The stationary flexible cover having a length from end to end that is shorter than a length of the floating vessel. A moveable flexible cover extends from one end to the other end of the moveable bowed frame, covering the movable bowed frame crossbeams. The movable bowed frames slides on the upper moveable frame track and lower stationary frame track simultaneously to repeatedly retract and deploy to access or secure a floating vessel.

Abstract: A ventilated life jacket is an apparatus that facilitates airflow through the vest. The apparatus includes a vest, a first buoyant foam layer, a second buoyant foam layer, at least one first ventilation track, at least one second ventilation track, and a plurality of harnesses. The vest further includes a first panel and a second panel. The first panel houses the first buoyant foam layer. Similarly, the second panel houses the second buoyant foam layer. The at least one first ventilation track and the at least one second ventilation track traverses through and across the first buoyant foam layer and the second buoyant foam layer, respectively, for increased airflow. The plurality of harnesses secures the vest around a user. The at least one first ventilation track and the at least one second ventilation track may be a series of holes or a continuous slot.

Abstract: A snorkel mask is disclosed comprising a faceplate having a lateral partition on an interior surface delineating an upper and lower section, the lower section comprising a region that extends away from the upper section and includes a cutout section fitted with a complementary-shaped flexible insert that enables a user to grasp the nose. The snorkel mask further includes a rigid frame bonded to the faceplate and sandwiched between the faceplate and a flexible annular sidewall skirt that is hollow and filled with a gas or other cushioning substance. The flexible skirt includes a lateral nose piece section attached to the partition. The lateral nose piece section having an inlet aperture and check valve for inhaled air, and an orifice through which an exhalation conduit extends from the lower chamber to a snorkel device forming a passageway for exhaled air to pass through the upper chamber to the snorkel device.

Abstract: A snorkel and diving mask is disclosed comprising a faceplate having a lateral partition on an interior surface delineating an upper and lower section, the lower section comprising a region that extends away from the upper section and includes a cutout section fitted with a complementary-shaped flexible insert that enables a user to grasp the nose. The faceplate further includes a snorkel coupling having a passageway contained therein. The snorkel and diving mask further includes a tubular interface sleeve which fluidly connects the snorkel coupling passageway to a mouthpiece receiver tube of a conventional second stage scuba regulator.

Abstract: A diving mask system is disclosed comprising a faceplate having a lateral partition on an interior surface delineating an upper and lower section, the lower section comprising a region that extends away from the upper section and includes at least one cutout section fitted with a complementary-shaped flexible insert that enables a user to grasp the nose. The faceplate further includes a rigid annular support frame either bonded to or extending out from a backside of said flange, the frame being configured within the outer periphery of said flange. A flexible annular sidewall skirt is attached to the support frame. The flexible skirt includes a lateral nose piece section attached to the partition. The lateral nose piece section having an inlet aperture and check valve for inhaled air, and an orifice through which an exhalation conduit having a separate check valve extends from the lower chamber to a snorkel device forming a passageway for exhaled air to pass through the upper chamber to the snorkel device.

Abstract: A diving mask system is disclosed comprising a faceplate having a lateral partition on an interior surface delineating an upper and lower section, the lower section comprising a region that extends away from the upper section and includes at least one cutout section fitted with a complementary-shaped flexible insert that enables a user to grasp the nose. The faceplate further includes a flexible tubular insert defining a passageway extending through the faceplate to a lower chamber. The tubular insert has a distal end dimensioned to fit and seal onto the mouthpiece receiver tube of a conventional second stage scuba regulator permitting the mask to be scuba enabled. A quick-release clasp mechanism attached to the mask's elastic retention straps is also disclosed.

Abstract: An oscillating reversible motor providing a novel means of converting oscillating motion into selectable clockwise or counterclockwise rotary motion. More particularly, the invention presents a novel approach to a foot or hand pedal driven apparatus with which a traditional rotary water propeller or other output device may be employed in both forward and reverse directions of relative motion.

Abstract: A wave-powered water vehicle includes a surface float, a submerged swimmer, and a tether which connects the float and the swimmer, so that the swimmer moves up and down as a result of wave motion. The swimmer includes one or more fins which interact with the water as the swimmer moves up and down, and generate forces which propel the vehicle forward. The vehicle, which need not be manned, can carry communication and control equipment so that it can follow a course directed by signals sent to it, and so that it can record or transmit data from sensors on the vehicle.

Abstract: A structural tube within a marine propulsion system directly provides steering functionality from its interaction with the water and houses hardware used to transmit power from the engine to the propeller shaft. Said invention comprises a long, hollow, tube of constant cross section, the exterior profile of which takes the shape of an airfoil.

Abstract: A hydraulic steering system for a watercraft has first and second hydraulic steering actuators for steering first and second outdrives respectively, at least one hydraulic pump selectively supplying hydraulic pressure to at least one of the first and second actuators, a steering controller operatively connected to the at least one pump, a hydraulic helm selectively supplying hydraulic pressure to the first and second actuators, an auxiliary steering input device connected to the controller, and at least one mode selection valve having first and second mode positions for steering the watercraft in first and second steering modes respectively. In the first steering mode, the hydraulic helm is hydraulically connected to the first and second actuators. In the second steering mode, the hydraulic helm is hydraulically disconnected from the first and second actuators. A watercraft having the steering system and a method for steering a watercraft are also disclosed.

Abstract: Apparatus for laminar flow control for a skin panel for an aircraft including a body for receipt into a recess of the skin panel. The body defines a chamber. The body includes an outer portion defining one or more micro apertures through the outer portion, each of the one or more micro apertures being in fluid communication with the chamber. The body includes a support portion supporting the outer portion, the support portion defining at least one outlet for allowing air to be drawn from the chamber in use by a suction means in fluid communication with the outlet in use. The apparatus is arranged such that, in use, air is drawn through the one or more micro apertures into the chamber and out of the outlet, thereby to promote laminar airflow over the outer portion in use.

Abstract: A hat-shaped stringer includes a wrap of at least one composite ply which includes a cap portion and a first flange which extends from a first side of the cap portion and a second flange which extends from a second side of the cap portion, wherein the cap portion defines a recess positioned between the first flange and the second flange. Further included is a first composite wall which extends in a first direction along a first plane within the recess, wherein the first plane intersects the cap portion and opposing sides of the first composite wall are spaced apart from the cap portion.

Abstract: An aircraft fuselage includes: at least one lower part, at least one upper part, structural connections connecting the lower part and the upper part in joining zones, in each joining zone, at least one space between the lower and upper parts and the structural connections, and a transparent wall for closing off each space.

Abstract: A fuselage structure for an aircraft, comprising a fuselage vessel and a pressure bulkhead arranged in an end region of the fuselage vessel and having a central region extending in a planar manner and a connection region adjoining the central region in a radial direction and surrounding the central region and being secured to the fuselage vessel. The pressure bulkhead divides the fuselage vessel with respect to the longitudinal direction into a first region for subjecting to an internal pressure and a second region for subjecting to an external pressure which is lower than the internal pressure. The central region of the pressure bulkhead has an arching in the direction of the first region of the fuselage vessel.

Abstract: An aircraft viewing platform system and method that enables passengers to view the exterior of the aircraft while in flight includes a canopy assembly, a platform assembly supporting at least one seat, and an elevating mechanism to facilitate raising the platform into a volume of the canopy assembly extending through a fuselage cutout beyond the fuselage periphery. The system and method may include an actuating mechanism such as a jack screw or a telescoping system. The platform can have integrated rollers slide configured to roll in guide rails. The system can include a control panel that regulates the elevating mechanism motion. The control panel allows the viewer to move the platform. The platform can include a rotating pedestal to allow passengers have a 360-degree view of the aircraft exterior.

Abstract: An aircraft canopy includes a window pane, a frame from a primary structure of the aircraft, and a flange fastened to the frame with fastening screw, characterized in that: the flange is secured to the peripheral edge of the window pane by engaging of at least one plate of the flange between plies of the window pane, so that flange and window pane form an all in one-piece assembly, at each fastening screw, a load-transferring and distributing member is arranged between an outer surface of the flange and the fasting screw, a cavity being provided in the flange for receiving the load-transferring and distributing member, the member having a recess for receiving the screw head.

Abstract: A composite sandwich panel includes a perforated heater element in the middle of two structural plies, attached by a resin infiltrating perforations on the surface of the heater element. The heater element in the sandwich panel can withstand greater shear stress than non-perforated elements. The composite sandwich panel includes support layers such as honeycomb or foam.

Abstract: An aircraft assembly is disclosed having a wing tip device connected to a wing tip of a wing by a first connector, a second connector, and a third connector. The wing tip device includes a front device spar and a rear device spar. The first connector is associated with the rear device spar. The second connector is spaced apart in a chordwise direction forward of the first connector, and the third connector is spaced apart in a chordwise direction rearward of the first connector. The third connector includes a spigot mounting formation.

Abstract: A wing for an aircraft includes, but is not limited to, a wing body having a wingtip, a leading-edge, and a trailing edge. The wingtip comprises an outboard-most portion of the wing body. The leading-edge is disposed along a forward portion of the wing body and is configured to cause a vortex to extend off the trailing edge at a location inboard of the wingtip when the aircraft is flown sub-sonically at a predetermined angle of attack. The trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip at a position that corresponds with the location where the vortex extends off the trailing edge.

Abstract: Described herein is vehicle comprising a body. The vehicle also comprises a cargo door assembly, coupled to the body. The cargo door assembly comprises a first door, movable, relative to the body, between a first closed position and a first open position. The cargo door assembly also comprises a first aerodynamics control surface, coupled to the first door and selectively movable relative to the first door. The preceding subject matter of this paragraph characterizes example 1 of the present disclosure.

Abstract: An aerodynamic structure comprising an aerodynamic surface. The aerodynamic surface is formed by a first part of the aerodynamic structure; a second part of the aerodynamic structure; and a sealed gap between the first part and the second part. The sealed gap contains a sealant material and a support material.

Abstract: Oil transfer tube for a system to control the regulation of a turbine engine propeller pitch, in particular of an aircraft, the tube being intended to be mounted coaxially inside a tubular shaft of the propeller, the tube having an elongated shape and including a first male longitudinal end part intended to be inserted in a female housing of a stator casing equipped with an oil supply circuit of the tube, and a second male longitudinal end part around which is intended to be mounted a hydrodynamic bearing to guide the tube in the shaft, wherein the first end part includes a free annular end with a convex rounded cross-section intended to bear axially against an annular bottom of said housing, and in that said second end part comprises an outer axial annular bearing surface of an inner ring of the bearing, the annular bearing surface presenting in cross-section a convex curved shape.

Abstract: Features for a tail-sitter aircraft having efficiently designed propulsive elements are disclosed. The aircraft may have a tail with landing mounts to support the aircraft in a vertical position for takeoff and landing. The aircraft may have a hybrid propulsion system including an electric power source, such as a generator and an electric motor, and a prime power subsystem, such as an internal combustion engine. The electric and prime power subsystems may be used controllably in varying amounts depending on the phase of flight, such as takeoff, horizontal flight, landing, or maneuvers. The aircraft may have blades with piezo elements to provide shape-changing capability to the blade. The shape of the blade, such as the pitch and/or twist, may be controllably changed for optimal efficiency with the blade depending on phase of flight. The blade shape may be changed from a rotor-like shape during takeoff and landing, to a propeller-like shape during horizontal flight.

Abstract: A pitch actuation system for a turbomachine propeller, comprising an actuator with a movable portion configured to be connected to blades of the propeller in order to rotate them relative to the blade-pitch setting axes, wherein the actuator is an electromechanical actuator and comprises: blade-pitch control having a transmission screw rotated about an axis; a nut through which said transmission screw passes; and a member configured to engage with the blades in order to move the blades, wherein the nut is connected to the member via a decoupler configured such that a translational movement of the nut causes a translational movement of the member, but rotational movement of the member does not cause rotational movement of the nut.

Abstract: The present invention is to provide a system, a method, and a program for adjusting the balance of an insect killer hung from a robot that are capable to adjust the position of the insect killer. The system for adjusting the balance of an insect killer 1 hung from a robot 10 moving by a propeller 410 through a support arm 100 adjusts the balance of the insect killer 200 so that the angle between the support arm 100 and the direction of gravitational force from the robot 10 has a predetermined value or more; and adds a weight 300 to an end of the same support arm 100 as the support arm 100 in the negative direction to an angle of the predetermined value and calculates the weight 300 to adjust the balance of the insect killer 200.

Abstract: Adjustment mechanisms, systems and methods allow for a moveable aerodynamic surface to be positionally adjusted relative to a stationary adjustment surface so as to ensure smooth aerodynamic transition between such surfaces. The adjustment mechanisms may include a base structure adapted for fixed connection to the moveable aerodynamic surface, a fixed-position receiver opposing the base structure and adapted for positionally fixed connection to the support structure of the moveable aerodynamic surface and an adjustment bolt having a head and a threaded shaft extending from the head through an elongate slot of the base structure, the slot defining an elongate axis which is aligned with an adjustment axis for the moveable aerodynamic surface, and being threadably coupled to the receiver to operably interconnect the base structure and the receiver.

Abstract: A system (40) for controlling a ground lateral trajectory of an aircraft includes a command module (120) configured to generate a command of an instruction lateral trajectory, a limiting module (58) configured to determine, as a function of a speed and a maximum authorized sideslip angle of the wheel (5) of the aircraft, a steering angle range of the wheel (5) such that, the steering angle of the wheel (5) being in this range, the steering angle of the wheel (5) is smaller than the maximum steering angle, and a control module (130) configured to determine, as a function of the command, an instruction steering angle included in the range and able to cause a lateral movement of the aircraft according to or tending toward the instruction trajectory, and to send a steering instruction to the wheel (5) in order to orient it along the instruction angle.

Abstract: A system for controlling a lateral trajectory of an aircraft includes a rudder bar. Each pedal of the rudder bar is movable between a neutral position (pn) and an end-of-travel position (pf) along a unique travel. A movement of the pedal between the neutral position (pn) and an activation position (pact) commands a lateral movement by actuating a lateral movement device of a first set including a nose gear wheel, the different braking of the aircraft being nonactive. A movement of the pedal from the activation position (pact) to the end-of-travel position (pf) commands a lateral movement by actuating a device of the first set and the differential braking. A haptic feedback generator applies a first haptic profile to each pedal between the neutral position (pn) and the activation position (pact) and a second haptic profile from the activation position (pact) toward the end-of-travel position (pf).

Abstract: An unmanned aerial vehicle includes a propulsion system having at least one propulsion module comprised of at least one propeller and at least two motors/engines, one or more of the motors/engines providing mechanical energy to drive the propeller, wherein the difference between the angular velocities of the motors/engines provides energy input to a mechanical or magneto-mechanical linkage system to change the blade pitch angle of the propeller, in cyclic and/or collective manner.

Abstract: Systems and methods of operating a tiltrotor aircraft include providing a control system that includes sensors and/or gauges that provide feedback regarding hub shear forces in rotor systems of the aircraft that produce aeroelastic instability known as whirl flutter. Feedback from the sensors and/or gauges is communicated to a flight control subsystem that includes an algorithm that provides a cascading set of responses to control whirl flutter and a failsafe that adjusts operational characteristics of the aircraft in response to the continuation or excitation of the whirl flutter.

Abstract: Features for a tail-sitter aircraft having efficiently designed propulsive elements are disclosed. The aircraft may have a tail with landing mounts to support the aircraft in a vertical position for takeoff and landing. The aircraft may have a hybrid propulsion system including an electric power source, such as a generator and an electric motor, and a prime power subsystem, such as an internal combustion engine. The electric and prime power subsystems may be used controllably in varying amounts depending on the phase of flight, such as takeoff, horizontal flight, landing, or maneuvers. The aircraft may have blades with piezo elements to provide shape-changing capability to the blade. The shape of the blade, such as the pitch and/or twist, may be controllably changed for optimal efficiency with the blade depending on phase of flight. The blade shape may be changed from a rotor-like shape during takeoff and landing, to a propeller-like shape during horizontal flight.

Abstract: Systems and methods to form distributed and reconfigurable aerial vehicle configurations are described. An aerial vehicle configuration may include a plurality of aerial vehicles that are connected to a payload via respective tethers in order to complete a task, e.g., delivery of the payload to a location. The plurality of aerial vehicles selected as part of the aerial vehicle configuration may be of various types and may form a particular initial configuration. During operation, the aerial vehicle configuration may be modified based on changes to various operating parameters associated with aerial vehicles, the aerial vehicle configuration, the task, and/or the environment. The modifications may include changing positions, altitudes, and/or orientations of aerial vehicles with respect to each other and/or the payload, releasing aerial vehicles from the configuration, or adding new aerial vehicles to the configuration.

Abstract: An unmanned autonomous vehicle assessment and reporting system may implement a crisscross boustrophedonic flight pattern for capturing images of a structure to develop a three-dimensional model of the same. Patch scan analysis of predefined sample sizes of the roof may be captured in a separate scan and/or as part of the crisscross boustrophedonic flight pattern. The crisscross boustrophedonic flight pattern may include integrated oblique image captures via structure-facing camera angles during approach portions of each pass of a boustrophedonic flight pattern, via structure-facing end passes, and/or via rounded structure-facing end passes. A crisscross boustrophedonic flight pattern may include two or more boustrophedonic flight patterns that are at angles relative to one another.

Abstract: A method for adaptive mission execution by an unmanned aerial vehicle includes receiving a set of pre-calculated mission parameters corresponding to an initial UAV mission; collecting UAV operation data during flight of the unmanned aerial vehicle; calculating a set of modified mission parameters from the set of pre-calculated mission parameters and the UAV operation data, the set of modified mission parameters corresponding to a modified UAV mission; and executing the modified UAV mission on the unmanned aerial vehicle.

Abstract: A curtain header assembly is configured to be selectively positioned within an internal cabin of a vehicle. The curtain header assembly includes a main spanning bracket having a first end and a second end that is opposite from the first end. The main spanning bracket connects to a curtain track that retains one or more curtain couplings that are configured to moveably secure a curtain to the main spanning bracket. A first connection arm extends from the first end of the main spanning bracket, and is configured to be removably secured to a first fitting secured to a first fixed structure within the internal cabin. A second connection arm extends from the second end of the main spanning bracket, and is configured to be removably secured to a second fitting secured to a second fixed structure within the internal cabin.

Abstract: A foot washing system includes a support panel, and a basin including a foot-washing area and a drain that is configured to drain water out of the foot-washing area. The basin is moveably coupled to the support panel. The basin is selectively moveable between a stowed position and a deployed position in relation to the support panel. The deployed position allows for foot washing within the foot-washing area.

Abstract: Described is a breakover mechanism for a passenger seat that includes a frame member with a rear portion attached to two opposing sides of a seat back of the passenger seat wherein the frame member is at least partially disposed under a seat pan of the passenger seat, at least one moving portion attached to a forward portion of the frame member, a carriage portion fixedly attached to the seat pan; and a single point mechanism attached to the carriage portion. Once a threshold loading condition occurs, the single point mechanism changes states to facilitate movement of the moving portion relative to the carriage portion.

Abstract: An aircraft seating assembly including a replaceable underseat passenger accommodation feature tray includes passenger seats incorporating in-flight entertainment (IFE) system components for the use of the occupying passengers or neighboring passengers in the seats immediately behind. The IFE system components are connected by internal cabling paths within the seating assembly to contact points, and seat electronic boxes (SEB) mounted to a replaceable passenger accommodation feature tray provide IFE services to the system components. The SEB is connected to a second set of contact points on the feature tray by cabling paths that circumvent the spreader and leg structures of the seating assembly. When the feature tray is fully mounted to the seating assembly, the SEB is connected to the IFE system components through the cabling paths and contact points at which the cabling paths terminate, each contact point on the feature tray having a counterpart in the seating assembly.

Abstract: Lightweight passenger seats that are especially adapted for use in aircraft cabins. The seats will include a seat back and a seat bottom having a basin which defines a recessed central interior space, a plurality of straps having opposed ends connected to respective upper edge regions of the basin so as to be positioned under tension over the recessed central interior space; and a cover cushion covering the straps and connected to the basin. The seat back may be connected at opposed sides thereof to upright support members adjacent a lumbar region thereof so as to establish an upper region of the seat back above the lumbar region which is capable of being resiliently flexed between upright and rearwardly inclined positions.

Abstract: A seating system (1100) for a vehicle (1000) that comprises floor beams (1020), which support floor panels (1060) that define a floor surface (1062). The vehicle (1000) has a virtual longitudinal plane (1012), perpendicular to the floor surface (1062), and a virtual longitudinal axis (1010), parallel to the floor surface (1062) and lying in the virtual longitudinal plane (1012). The seating system (1100) comprises a primary pair of seat tracks (1300), a secondary pair of seat tracks (1310), one of which is positioned between seat tracks of the primary pair of seat tracks (1300), and a first seat assembly (1200). The first seat assembly (1200) comprises a first seat support (1202) and a first plurality of seats (1204), attached to the first seat support (1202). The first seat support (1202) is attached to the primary pair of seat tracks (1300).

Abstract: A seating system (1100) for a vehicle (1000) that comprises floor beams (1020), which support floor panels (1060) that define a floor surface (1062). The vehicle (1000) has a virtual longitudinal plane (1012), perpendicular to the floor surface (1062), and a virtual longitudinal axis (1010), parallel to the floor surface (1062) and lying in the virtual longitudinal plane (1012). The seating system (1100) comprises a primary pair of seat tracks (1300), a secondary pair of seat tracks (1310), one of which is positioned between seat tracks of the primary pair of seat tracks (1300), and a first seat assembly (1200). The first seat assembly (1200) comprises a first seat support (1202) and a first plurality of seats (1204), attached to the first seat support (1202). The first seat support (1202) is attached to the primary pair of seat tracks (1300).

Abstract: A seating system (1100) for a vehicle (1000) that comprises floor beams (1020), which support floor panels (1060) that define a floor surface (1062). The vehicle (1000) has a virtual longitudinal plane (1012), perpendicular to the floor surface (1062), and a virtual longitudinal axis (1010), parallel to the floor surface (1062) and lying in the virtual longitudinal plane (1012). The seating system (1100) comprises a primary pair of seat tracks (1300), a secondary pair of seat tracks (1310), one of which is positioned between seat tracks of the primary pair of seat tracks (1300), and a first seat assembly (1200). The first seat assembly (1200) comprises a first seat support (1202) and a first plurality of seats (1204), attached to the first seat support (1202). The first seat support (1202) is attached to the primary pair of seat tracks (1300).

Abstract: A frost protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel and an air intake lip forming a leading edge of the nacelle. The protection system comprises a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the at least one acoustic panel.

Abstract: An inflatable evacuation slide is disclosed. The inflatable evacuation slide includes an inflatable tube having a first end and a second end spaced from the first end and an anti-kiting device disposed proximate the second end of the inflatable tube, wherein the anti-kiting device may include a suction surface panel having a first side portion attached to an outer surface of the inflatable tube and a second side portion attached to the outer surface of the inflatable tube.

Abstract: There is provided a heat management system for a hybrid electrical aircraft comprising electric propulsors powered by a power plant. The heat management system comprises a heat exchanger integrated to a nacelle of at least one of the electric propulsors for dissipating heat withdrawn from the power components of the power plant into ambient air.

Abstract: A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

Abstract: An actuator is provided for an aircraft engine and includes a tubular base layer and a visco-elastic layer adhesively disposed on the tubular base layer.

Abstract: A power distribution system for a DC network, the DC network comprising electrical loads, the power distribution system being boarded on an aircraft and comprising: a plurality of AC/DC converters, and at least one AC power source. The power distribution system comprises: an “n” number of AC/DC converters, each one comprising an “(n?1)” number of first outputs and at least an additional output, and an “(n?1)·n” number of electrical loads. Each electrical load comprises two inputs: a first input for being connected with a corresponding first output, and a second input for being connected with any of the additional outputs. The power distribution system is configured to continue supplying electrical power to the DC network in case an AC/DC converter is not energized, such that the second input of such electrical load is connected to any additional output of another AC/DC converter, being the first input disconnected.

Abstract: A rotor system including a hub; a rim configured to rotate about the hub, the rim including an interior surface and an engagement surface; a plurality of rotor blades extending from the hub and coupled to the interior surface of the rim; and one or more outer drive gears disposed adjacent to the engagement surface of the rim; each of the one or more outer drive gears including a plurality of teeth for engaging the engagement surface of the rim; wherein the one or more outer drive gears are configured to rotate the rim such that the plurality of rotor blades rotates about the hub. Other aspects provide an aircraft rotor system and methods of operating an aircraft rotor system.