Abstract: A fan assembly includes a fan having a shroud having an inner surface defining a flow chamber and an outer surface defining a plurality of teeth arrayed circularly around a circumference of the shroud. The fan also includes a plurality of blades arranged circularly around a central axis of the fan and extending radially inwardly from the shroud towards the central axis of the fan. Each of the plurality of blades is arranged inside the flow chamber and includes an outer edge connected to the inner surface of the shroud. The fan assembly further includes a drive assembly arranged outside the shroud and operatively engaged with the plurality of teeth of the shroud to rotate the fan around the central axis.

Abstract: Embodiments of the invention(s) cover a method and system in which the system monitors outputs of a set of subsystems associated with a flying vehicle, wherein the flying vehicle comprises a set of fixed-wing operation modes and a set of vertical take-off and landing (VTOL) operation modes, and wherein the set of subsystems generate signals associated with an operational environment surrounding the flying vehicle; from said outputs of the set of subsystems, generating a risk assessment characterizing one or more potential hazards associated with the environment surrounding the flying vehicle; based upon the risk assessment, returning instructions for execution of a detect and avoid operation; and optionally, executing the detect and avoid operation.

Abstract: A vertical axis turbine having a first rotor and at least one second rotor, the first rotor being configured to rotate around a first rotation axis that is vertical or more vertical than horizontal. The first rotor may be configured to be driven and/or rotated by wind or water flow. The at least one second rotor is provided on or coupled to the first rotor such that the first rotor is operable to move the second rotor upon rotation of the first rotor. The second rotor is operable to drive a power take off system. Each second rotor rotates around a respective second rotation axis that may be angled or perpendicular to the first rotation axis of the first rotor. The first and second rotors are configured so that the power take-off system can be driven without the need for a gearbox.

Abstract: A method of verifying operation of an aircraft in a pre-defined flight mode includes operating the aircraft in a first flight mode, commanding the aircraft to transition to a second flight mode, evaluating a plurality of motor performance parameters, and based on values of the plurality of motor performance parameters, determining whether the aircraft has successfully transitioned to the second flight mode.

Abstract: A ducted axial fan. The fan includes a rotor rotatable around an axis X and having a plurality of blades, and a duct suitable for defining a circular section channel developing in an axial direction around the rotor. The duct includes an annular seat circumferentially extending around the rotor, and the blade tips are at least partially received in the annular seat of the duct.

Abstract: A yaw control system for a helicopter having a tailboom and a forward flight mode includes a surface coupled to the tailboom, one or more tail rotors coupled to the surface, a flight control computer implementing a yaw controller having a rudder control module and a tail rotor rotational speed reduction module and a rudder rotatably coupled to the surface. The tail rotor rotational speed reduction module is configured to selectively switch the one or more tail rotors into a rotational speed reduction mode in the helicopter forward flight mode. The rudder control module is configured to rotate the rudder in the rotational speed reduction mode of the one or more tail rotors to control the yaw of the helicopter.

Abstract: A propulsion system for a rotorcraft includes a first fan assembly including a plurality of first fan blades, a second fan assembly including a plurality of second fan blades and a drive system adapted to provide torque to the first and second fan blades. The first fan blades have a larger rotational inertia than the second fan blades. The second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft.

Abstract: There is disclosed an aircraft engine assembly including an engine having an engine shaft; an output shaft; a clutch in driving engagement between the engine shaft and the output shaft. The clutch has a first component in driving engagement with the engine shaft and a second component. The clutch is operable between first and second configurations. In the first configuration, the first component is rotatable relative to the second component and the engine shaft is rotatable relative to the output shaft. In the second configuration, the first and second components are engaged with one another and the engine shaft rotates with the output shaft. A mechanical lock is operable between first and second positions. In the first position, the mechanical lock is disengaged from the first component. In the second position, the first and second components are secured for joint rotation one relative to the other.

Abstract: A method of improving a blade and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack.

Abstract: A pusher rotorcraft is provided in one example embodiment and may include at least one engine in mechanical communication with a drop-down gearbox; a driveshaft in mechanical communication with the drop-down gearbox, a main rotor gearbox, and a tail system gearbox; a main rotor system in mechanical communication with the main rotor gearbox; an anti-torque system in mechanical communication with the tail system gearbox; and a pusher propeller system in mechanical communication with the tail system gearbox.

Abstract: A wind turbine assembly comprising a cantilever support, a rotor assembly having a rotor hub rotatably coupled to the cantilever support, and a plurality of rotors radially arranged about and coupled to the rotor hub is provided. Each rotor includes a rotor arm defining an arm axis, a blade element, and an adjustment mechanism coupled between the rotor arm and the blade element. The blade element has a concave face portion and defines a target axis. The adjustment mechanism is movable between a first rake angle defined between the first arm axis and the target axis, and a second rake angle to position each of the blade elements relative to each other.

Abstract: A rotary wing aircraft including a prime mover, a main rotor assembly having a first plurality of rotor blades operatively coupled to a main rotor shaft rotatable at a first speed ratio, a tail rotor assembly including a second plurality of rotor blades operatively coupled to a tail rotor shaft rotatable at a second speed ratio, and a variable ratio gearbox assembly mechanically connected to the tail rotor assembly. The variable ratio gearbox assembly operates to selectively vary the second speed ratio relative to the first speed ratio.

Abstract: A gas turbine engine is disclosed with a first spool having a first turbine connected to a first compressor through a first rotatable shaft; a second spool having a second turbine connected to a second compressor through a second rotatable shaft; and a gearbox having a power input port coupled to each of the first and second shafts and a power output port connected to a third shaft, wherein the rotational speed of the third shaft is lower than the rotational speed of each of the first and second shafts.

Abstract: The main purpose of the invention is an air circulation device (1) for a turbomachine (10), comprising an air conveyance circuit (2, 4b, 9, 4a, 3) adapted to bring hot bleed air (A1) from the turbomachine (10) to a part to be heated (38), comprising a first segment fixed in rotation to a rotating part (31, 24) and comprising at least one hot air (A2) conveyance conduit (3, 9), and a hot air passage device (4a, 4b), comprising an annular compartment fixed in rotation to the first segment, characterise in that the annular compartment comprises a heat exchanger in contact with external air, and in that the hot air passage device (4a, 4b) comprises a hot air bypass system to deviate air entering into the device and to make it circulate along the heat exchanger when the temperature of this intake air is above a predetermined threshold.

Abstract: A fan module for an aircraft is disclosed herein. The fan module includes a fan rotor and an optional power supply system. The fan rotor is mounted for rotation about a central axis and configured to couple to a rotational power source. The fan rotor includes a plurality of variable-pitch fan blades each movable from a thrust-generation orientation to a power-generation orientation.

Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.

Abstract: A hydrokinetic energy conversion system (1) comprising a turbine device (2) comprising a rotor (3) displaying a rotational axis (O), which turbine device is arranged to operate with the rotational axis in an inclined orientation vis-à-vis an incoming body of water (W), and which rotor comprises a blade (10) which is arranged to interact with the incoming body of water such that rotational energy is imparted to the rotor. The blade comprises a first, convex surface (12), a second, concave surface (13) and a free, distal edge (E) where the first surface and the second surface meet. The curvature of the second surface, when viewed in a plane orthogonal to the rotational axis, is such that a maximum depth (Dmax) of the second surface, when measured from a straight line intersecting the rotational axis and the distal edge, is at least 35% of the distance between the rotational axis and the distal edge.

Abstract: A rotary wing aircraft and method of operating a tail drive system thereof, wherein the tail drive system includes a gearbox that contains a first transmissive device and a second transmissive device in parallel, each transmissive device having an input operatively connected to a first shaft that is powered by the main rotor drive system. The first and second transmissive devices each have an output operatively connected to a second shaft that drives the secondary rotary device.

Abstract: A monolithic blade of a rotorcraft rotor, the blade comprising at least locally an airfoil zone having a pressure side face and a suction side face. The invention is remarkable in that the blade has a root zone including a finger with a spherical bearing surface arranged at a root end of the blade, a recess suitable for receiving a laminated spherical bearing, and a flexible portion having a preferred direction of deformation in bending about a flapping axis of the blade, the flexible portion being arranged between the finger and the recess.

Abstract: A tail rotor recovery control system has a detection module configured to detect a loss of tail rotor drive from a tail rotor sensor of an aircraft; and a regulation module configured to augment or deactivate manual flight control signals and transmit automated signals to control modules of a primary flight control system. The automated signals facilitate the aircraft to attain or maintain a preset tip path plane level, attain or maintain a preset aircraft state, or to execute an automated recovery to forward flight.

Abstract: A gas turbine engine with a transmission having a variable ratio is discussed. A first gear train is in driving engagement with the low pressure spool and has a first output gear. A second gear train is in driving engagement with the high pressure spool and has a second output gear spaced apart from the first output gear. A third gear train defines a driving engagement between the low pressure spool and the low pressure compressor rotor with a variable transmission ratio. A fourth gear train is in driving engagement with the first and second output gears, and in driving engagement with the third gear train to determine the transmission ratio. A method of adjusting a speed of a low pressure compressor rotor of a gas turbine engine is also discussed.

Abstract: In one implementation, a hydropower module for use in a flowing body of water is described. The module includes an axle and a plurality of paddle fans rotatably coupled to the axle and having a paddle fan rotation. Each paddle fan of the plurality of paddle fans includes a plurality of blades configured to be driven by the body of water. The plurality of paddle fans are oriented in an arc wherein the blades of adjacent paddle fans are closer together at a top of the paddle fan rotation than at a bottom of the paddle fan rotation.

Abstract: An energy extraction device for extracting energy from a flow of fluid is provided. The energy extraction device comprises a rotating member for rotatably mounting to a support structure, at least one rotatable bank of blades connected to the rotating member through a connection disposed radially from the main axis of rotation of the rotating member, and, a pitch control system for controlling the angular position of the at least one rotatable bank of blades relative to a direction of the flow of fluid. The rotating member has a main axis of rotation and the at least one bank of blades comprises an array of spaced-apart blades secured together. Each of the at least one bank of blades has a bank axis of rotation.

Abstract: A fan module includes a framework and at least two blade assemblies arranged inside the framework. Each blade assembly includes at least two blade units arranged in line. The rotating direction of each blade assembly is opposite to that of adjacent blade assembly.

Abstract: A rotorcraft with two counter-rotating rotors and method for inertially controlling the rotorcraft. The rotorcraft includes a hinged frame configured such that at least one inter-rotor angle of the two counter-rotating rotors is controlled by at least one actuated hinge of the hinged frame and the rotational axes of the two counter-rotating rotors are substantially collinear when the actuated hinge is in a fully open position. The sum of the magnitudes of torque applied to the two counter-rotating rotors is varied to control the lift of the rotorcraft. The difference of the magnitudes of torque applied to the two counter-rotating rotors is varied to control the yaw of the rotorcraft. The at least one inter-rotor angle is varied using the at least one actuated hinge to control the pitch and/or roll of the rotorcraft.

Abstract: An electronics cooling fan comprises a centrifugal clutch adapted to disengage and freewheel upon fan failure.

Abstract: A wind power plant includes four main elements: a foundation (29), at least one supporting structure (21), a carrying construction (23) having a vertical axis (25) and being rotatable around the vertical axis, and at least one rotor (45), (49), (52) positioned on the carrying construction. The rotors can have horizontal, vertical, and inclined axes of rotation in different combinations. Each rotor has at least two blades (53) arranged along its axis of rotation. Since the rotors used in the invention have a small diameter, the wind power plant can produce energy under high and low wind speeds, consequently producing more energy per year than known wind turbines. Also, because the rotors have rectilinear blades for their manufacture expensive composite materials and complicated expensive equipment are not required. For these reasons the wind power plant of this invention will produce energy at lower cost.

Abstract: A multi-fan assembly whose revolution speed can be controlled by a member fan designed with a reverse rotating structure, which includes a housing in which is provided a rotatable member; a positive-rotation member fan is equipped with a positive-rotation motor, the positive-rotation motor serves to rotate blade holders and fan blades mounted on the blade holders, the positive-rotation member fan is fixed to the rotatable member via a holding arm; a reverse-rotation member fan is equipped with a reverse-rotation motor, the reverse-rotation motor serves to rotate blade holders and fan blades mounted on the blade holders, the reverse-rotation motor's rotating direction is opposite to that of the positive-rotation motor, the reverse-rotation member fan is fixed to the rotatable member via a holding arm.

Abstract: A multi-fan assembly includes: a down rod assembly having a first end for fixing to a ceiling wall and having a second end provided with a canopy, a rotary assembly being fixed to a lower end of the down rod assembly and covered by the canopy. At both sides of the rotary assembly is provided with a fixed arm for connecting with a member fan respectively, a pair of vertical oscillating means are disposed between the fixed arm and the member fan, and a speed control device is mounted on the rotary assembly and then covered by the canopy of the down rod assembly.

Abstract: A multi-fan assembly with a built in electromagnetic control device composed of a magnetic induction mask fixedly received in a space in a rotatable member, a magnetic flux coil fixedly connected to a central main shaft and snugly surrounded by the magnetic induction mask, and a current control unit also fixedly connected to a central main shaft, wherein the current control unit sends a desired current to the magnetic flux coil to produce a magnetic flux which magnetizes the silicon steel core of the magnetic flux coil to attract the metal magnetic induction mask thereby generating a resistant force to reduce the revolving speed of the two member fans round the central main shaft. Three options are designed for manipulating the current coming out of the current control unit; a direct wired wall control switch, or a wireless remote controlling using infra-red design or an automatic speed control using a speed detecting sensor.

Abstract: A wind energy conversion apparatus comprising a supporting structure including a number of spokes, which is rotatably journalled on a horizontal main shaft, wherein auxilliary rotors having an at least substantially circular plane of inflow are mounted on the ends of the spokes, wherein each of the auxilliary rotors has a plane of inflow which includes an acute angle with the central axis of the main shaft and which intersects the central axis upstream of the main shaft, and wherein the auxilliary rotors are made up of rotors including rotor blades or of conical bodies having a large apex angle, whose base is directed towards the oncoming wind.

Abstract: The wing movement has a gearbox, a reference gear extending through the gearbox and being movably mounted to the gearbox, an input shaft extending through the reference gear and into the gearbox and first and second output shafts movably extending from the gearbox at right angles with the input shaft. There is also provided a motor having a drive shaft connected to the input shaft of the gearbox for rotation of the input shaft. A bracket is connected to the motor base and to the reference gear for retaining the reference gear to the motor base, with an axis of the reference gear in alignment with the drive shaft of the motor. A gearing system is mounted inside the gearbox for rotating the first and second output shafts one full turn in opposite directions relative to each other, upon a rotation of the input shaft one full turn, and for rotating the gearbox one full turn about the reference gear upon a rotation of the first and second output shafts one full turn.

Abstract: Apparatus and method for harnessing fluid energy from a fluid current and converting it into mechanical energy. The invention comprises a big wheel and a little wheel where the little wheel rotates about on axis parallel to but offset from an axis about which the big wheel rotates. The little wheel rotates within the big wheel. Flexible sails are fastened between masts of the big wheel and masts of the little wheel so that when the wheels rotate each sail is unfurled and extended during one phase of operation and said sail is folded upon itself during another phase of operation. When extended or stretched open, the sail derives power from the fluid current. When the sail is folded, it offers a reduced resistance to the fluid current into which said sail is moving.

Abstract: A power takeoff for an unducted fan gas turbine engine having first and second counterrotating coaxial rotors coupled respectively to first and second propellers. The rotors and propellers are oriented for rotation about a longitudinal axis of the engine. A gear is coupled to each of the rotors for rotation therewith and arranged to provide rotational motion about an axis transverse to the engine axis. A shaft is coupled to the gear for rotation about the transverse axis. Each of the propellers includes a plurality of propeller blades, each of the blades is rotatable about a corresponding blade axis, and a control is coupled to the blades for varying the pitch thereof whereby power is selectively distributed between the propellers and the power takeoff. The power takeoff may include a propeller coupled to the shaft for developing thrust substantially transverse to the engine axis and/or a pump, compressor, or generator to supply fluids or electric power to other apparatus.

Abstract: A helicopter tail rotor (10, 130) includes a drive mast (12) having an axis of rotation (14). A first blade pair (20) is mounted for rotation about the drive mast (12). The first blade pair (20) includes a pitch change axis (54) perpendicularly disposed to the drive mast axis of rotation (14). A second blade pair (34) is mounted for rotation about the drive mast (12) and is spaced apart from and parallel disposed to the first blade pair (20). The second blade pair (34) includes a pitch change axis (60) parallel to the pitch change axis (54) of the first blade pair (20).

Abstract: An auxiliary helicopter rotor on which at least two blades extend radially from a hub, each of which blades presents a root connecting it to the hub, and a beam having two wings extending respectively along the back and face of the blade; the wings of the beam diverging along the root in such a manner as to form a fork engaged both by a center plate on the hub, to which the fork is connected via a spherical joint, and by a flexible leaf extending from the center plate inside the fork and connected to the beam of the blade by means of an axial joint.

Abstract: Main helicopter drive for transmitting drive to the countershaft even when the main shaft connected to the rotor is idle, and on which a sleeve, turned by a drive shaft and connected by gears to the countershaft, supports in rotary and axially-sliding manner, an inner tubular body angularly integral with the main shaft; an actuator being connected to the said tubular body for moving it between a normal position, in which the said tubular body is connected to the said sleeve by a freewheel on the latter, and a position in which the said freewheel engages the outer casing of a bearing fitted on to the said tubular body.

Abstract: A tail rotor arrangement for rotary wing aircraft, comprising a tunnel of axis X--X transverse with respect to the aircraft and in which is disposed a multi-blade rotor coaxial with respect to the tunnel and generating a transverse air flow. The arrangement comprises a plurality of fixed blades disposed inside of the tunnel downstream of the rotor with respect to the air flow and arranged in at least substantially radial manner with respect to the tunnel in order to be able to recover, in the form of an axial thrust, the energy of rotation of the air flow at the outlet of the rotor. The tail rotor arrangement provides an increase in thrust of the rotors, particularly paired rotors.

Abstract: A traversing blade rotary propeller useful as a propulsion system for various types of boats and aircraft or as a wind or water actuated turbine. A traversing blade rotary propeller of this type includes a stationary main shaft, a mount to which an end of the stationary main shaft is affixed, a central housing structured to carry a pair of alternately disposed, perpendicularly projecting radial arm shafts, and where the device is used as a propulsion system, power means for rotation of said central housing relative to the fixed axis formed by said stationary main shaft. A pair of propeller shafts extend perpendicularly from an end of each of said radial arm shafts, and flat propeller blades are attached to each. The inboard ends of each of the radial arm shafts are operatively engaged with the stationary main shaft, and the outboard ends are operatively engaged with the propeller shafts, as via gears such that rotation of the central housing produces rotation of the propeller shafts.

Abstract: A helicopter including a power absorber arranged to selectively absorb power from a sustaining rotor system during deceleration. In an illustrated embodiment for a helicopter having a single sustaining rotor, the power absorber comprises a tail rotor assembly having two tail rotors located one on each side of a tail cone, and a control operative to adjust the pitch setting of the tail rotors to provide lateral thrust forces in opposed directions with a net lateral thrust force in one direction in order to maintain a desired heading during deceleration.

Abstract: Disclosed herein is an apparatus for fashioning a wind wheel apparatus that utilizes the wheat field principle in association with a power generating station to provide back pumping in a dam environment to provide a greater efficiency. Specifically, a double array of wind wheels is disposed in a matrix on the horizontal plane oriented to address the angle of attack of the wind regardless of wind direction and is further provided with means to develop electrical current therefrom to be used in motivating pumping means for returning water that has generated electricity due to potential energy back into a reservoir. Thus the wind energy is stored in the reservoir as potential energy. Because of its low cost and abundance this energy is able to address the task of supplying energy to industries or municipalities engaged in processing and pumping of large quantities of ocean water to any desirable elevation.

Abstract: Compound helicopters, those having a rotor blade and a small wing, possess rear propulsion propeller adjacent to the tail rotor. The tail gearbox is driven through a drive train coupled to the main rotor drive shaft. In such aircraft the tail rotor is in operation when the propulsion propeller is turning, and vice versa. A mechanism is provided herein for stopping or feathering the tail rotor when driving the propulsion propeller, or for stopping the propulsion propeller when the tail rotor is in operation.