Abstract: The present invention provides a mechanism (90) for damping vibrations to prevent coupling of vibration modes of the carrier structure (106) with vibration modes of a rotor (100) secured to said carrier structure (106). The mechanism comprises a support (3) suitable for being fastened to said rotor (100) and at least one resonator (1) including a mass (5) carried by said support (3) via mobile mounting means (6) for mounting said mass (5) to move on said support (3), said mechanism (90) including damper means (8) for damping the resonator (1), which means are interposed between the resonator (1) and an engagement member (9) on said support (3).

Abstract: A helicopter includes a main rotor guided and protected in minor impacts by a guide-ring. In selected embodiments, the rotor is powered by an electric motor employing a magnetic field generator carried by the main rotor and stator coils installed on the guide-ring. The helicopter's main rotor thus effectively functions as the rotor of the electric power plant of the helicopter. In selected embodiments, the rotor's blades are arranged so as to create an opening in the center of the rotor, allowing pilot ejection or deployment of a parachute capable of safely lowering the helicopter in case of an emergency.

Abstract: A transmission gearbox for a rotary-wing aircraft includes a main gearbox and a variable speed gearbox in meshing engagement with the main rotor gearbox. The variable speed gearbox permits at least two different RPMs for the main rotor system without disengaging the engine(s) or changing engine RPMs. The variable speed gearbox includes a clutch, preferably a multi-plate clutch, and a freewheel unit for each engine. A gear path drives the main gearbox in a “high rotor speed mode” when the clutch is engaged to drive the main rotor system at high rotor rpm for hover flight profile. A reduced gear path drives the main gearbox in a “low rotor speed mode” when the clutch is disengaged and power is transferred through the freewheel unit, to drive the main rotor system at lower rotor rpm for high speed flight. The variable speed gearbox may be configured for a tail drive system that operates at a continuous speed, a tail drive system that changes speed with the main rotor shaft or for no tail drive system.

Abstract: Conventional bottom blade type flight vehicles have a complex structure and complex flying control operations in that several pairs of fixing plates, and forward/backward and left and right rotation adjustment blades are separately mounted and adjusted to remove the anti-torque of the flight vehicle caused by the rotation of the propellers and to fly the flight vehicle, so that the flight vehicles has difficulties in scouting and surveillance of an indoor area due to the heavy weight and the great volume. The flight vehicle of the disclosure continuously rotates in a state in which the anti-torque is not removed by one adjustment blade. The flight vehicle stops, ascends, descends, advances forward, backward, leftward, or rightward, or left or right rotates, performs flight in a narrow space, scouting and surveillance in an indoor area with a simple structure, simple control, light weight, and small size, and increases power efficiency.

Abstract: A vehicle (1) for riding on land and flying in air comprises: a cabin (2) with wheels (3, 4), the cabin (2) being designed for accommodating at least one person, a rotor (40) having a rotor axle (41), a rotor base (44) and rotor blades (45) mounted to the rotor base (44); a support bracket (30) carrying the rotor (40), the support bracket (30) having a bottom section (31) extending substantially parallel to the cabin roof, and having at least one leg section (32) extending substantially parallel to the cabin side, the leg section (32) having a free end connected to the cabin (2); wherein the rotor blades (45) are hingedly mounted to the rotor base (44); and wherein the bottom bracket (31) part with the rotor (40) is displaceable in the longitudinal direction of the vehicle (1).

Abstract: A head-up display (HUD) is disclosed. The HUD is on board a rotary wing aircraft. The HUD comprises a projector. The HUD also comprises a combiner. The combiner enables viewing of the world outside of the combiner and allows viewing of information provided from the projector. Further, the HUD comprises a computer coupled to the projector in providing hover and touchdown symbols conformally mapped onto the combiner. A conformal mapping of hover and touchdown symbols is also provided on the combiner.

Abstract: A flight control system includes a collective position command module for a lift axis (collective pitch) which, in combination with an active collective system, provides a force feedback such that a pilot may seamlessly command vertical speed, flight path angle or directly change collective blade pitch. The collective position command module utilizes displacement of the collective controller to command direct collective blade pitch change, while a constant force application to the collective controller within a “level flight” detent commands vertical velocity or flight path angle. The “level flight” detent provides a tactile cue for collective position to reference the aircraft level flight attitude without the pilot having to refer to the instruments and without excessive collective controller movement.

Abstract: A method and a device (D) for detecting and signaling the approach to a vortex domain by a rotorcraft, the device includes: first elements (1) for measuring the instantaneous vertical speed v of a rotorcraft; second elements (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; third elements (3) constituting a database BDD relating to representing at least one instantaneous vortex domain; fourth elements (4) connected via first, second, and third connections (l1, l2, l3) respectively to the first, second, and third elements, the fourth elements being designed to detect the approach to a vortex domain by the rotorcraft; and fifth elements (5) for signaling the approach to a vortex domain by the rotorcraft, the fifth elements being connected to the fourth elements (4) via a connection (l4).

Abstract: A light weight, split torque, geared power transmission having a reduced number of gears and useful for, e.g., transmitting power from an engine to the main rotor of a rotorcraft, includes a ring gear having a pair of oppositely facing angular bevel gears respectively formed on opposite sides of a medial plane thereof, and a first pinion having an elongated drive shaft extending through the medial plane of the ring gear and disposed at an oblique angle relative thereto. The first pinion includes a pair of cylindrical gears mounted coaxially on the drive shaft and respectively disposed in conjugate meshing engagement with respective ones of the bevel gears of the ring gear. An elongated annular output shaft made of a strong, light weight composite material is coupled to a circumferential periphery of the ring gear.

Abstract: The rotary flap (1) is liable to turn about a longitudinal axis of rotation (4) defined according to the first span (5) of said flap (1), said flap (1) having a profile (6) extending along the chord (CO) and comprising a first leading edge (7), a first trailing edge (8), an inner surface (9) and an outer surface (10), The inner surface (9) and outer surface (10) have non-concave shapes, first leading edge (7) having a rounded shape provided with a curve radius (R) more or less constant or elliptical in shape whose first major axis to minor axis quotient is less than or equal to 1.5, with first trailing edge (8) having a main angle (?) that is included between 10° and 30°, and axis of rotation (4) is situated at a first distance (C1) from first leading edge (7), that is included between 15% and 35% of the chord (CO) of flap (1).

Abstract: A mechanical flight control system for a rotary-wing aircraft is disclosed. The flight control system comprises an upstream portion, a downstream portion, and an assembly for connecting the upstream portion to the downstream portion. The assembly may comprise dual concentric valve actuators and/or a variety of system load limiting features.

Abstract: A single place helicopter comprising a lower airframe and an upper airframe, having a rotor shaft attached thereto, rotor blades, and a hub on said rotor shaft with means to change blade pitch for vertical flight. The upper airframe comprising a rotor system, engine, tail boom and tail rotor tilt as one unit with the pilot forward, rearward and in a lateral attitude for directional flight control by means of a hinged gimbal joint or block fastened between the vertical tubes on the lower airframe that connect the upper and lower airframes. By allowing the pilot to move with the rotor system, this configuration combines weight and CG manipulation in a tilt rotor design that eliminates the angular differences between advancing and retreating rotor blades during lateral flight and allows for a simplified human interface flight control system in a single-main-tilt rotor helicopter.

Abstract: A flying apparatus having a frame configured to couple to a high voltage tether system, and at least one motor module mounted to the frame, the module including a holding structure attached to the frame, a rotating structure, including a rotor shaft, configured to rotate relative to the holding structure, a rotor attached to the rotor shaft and a plurality of motors attached to the holding structure, each including a drive shaft configured to engage with the rotor shaft, wherein the motors are configured to receive electrical energy from the tether system and drive the drive shafts to create a torque on the rotor shaft to thereby rotate the rotor and create lift to fly the apparatus from the ground to a desired position aloft while remaining coupled to the tether system.

Abstract: A toy helicopter, in accordance with the present disclosure, includes a body having a longitudinal length and a main rotor. There is an element movable along the longitudinal length. The element allows a user to selectively adjust the location of the center of gravity of a toy helicopter by moving the element along the longitudinal length, thereby changing the velocity of the helicopter.

Abstract: A bottom blade type vehicle includes a fixed screw-pitch leaf horizontally mounted taking a center axis as the center; a power part mounted above the leaf; a controlling part mounted under the leaf; a first and a second fixing plates and a first and a second protecting plates being crossed each other in a cross-shape taking the controlling part as the center, one end of the first and the second fixing plates and the first and the second protecting plates connected to the controlling part and the other end of them connected to a round frame; a bridge plate vertically fixedly mounted under the round frame; and a first and a second adjusting controlled by a controlling device of the controlling part, wherein the first and the second adjusting blades are mounted on the first and the second protecting plates respectively.

Abstract: Electrically powered Vertical Takeoff and Landing (VTOL) aircraft are presented. Contemplated VTOL aircraft can include one or more electrical energy stores capable of delivering electrical power to one or more electric motors disposed within one or more rotor housings, where the motors can drive the rotors. The VTOL aircraft can also include one or more sustainer energy/power sources (e.g., batteries, engines, generators, fuel-cells, semi-cells, etc.) capable of driving the motors should the energy stores fail or deplete. Various VTOL configurations are presented including an all-battery purebred design, a light hybrid design, and a heavy hybrid design. The contemplated configurations address safety, noise, and outwash concerns to allow such designs to operate in built-up areas while retaining competitive performance relative to existing aircraft.

Abstract: A rotorcraft is equipped with a rotor hub of large diameter in order to accommodate high loads from a hingeless rotor. In preferred embodiments, a rotorcraft has a rotor disposed on a mast with blades attached to a hub by means of a feather bearing that receives a shank of a blade. The hub is attached to non-rotating structure such as a tilting nacelle by means of a hub bearing. This facilitates the transfer of moments generated on the rotor to the airframe. The hub and feather bearings can be sized and arranged such that a feather bearing on a hub is disposed within an imaginary cylinder centered at a rotational axis of the hub and having a diameter no greater 1.2 times an inner diameter of the hub bearing. This can result in a large diameter hub and hub bearing capable of withstanding very large bending moments.

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Abstract: The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption.

Abstract: A helicopter having a rotor, a fuselage connected to the rotor by connecting means, and a control device for controlling vibration of the fuselage; the control device including generating means for generating signals associated with vibration of the fuselage, and actuating means for producing a force on the fuselage associated with the signals to reduce vibration; and the actuating means being carried by the connecting means.

Abstract: A hub fairing system (12) for a stopped-rotor aircraft (10) having a fuselage (14) including a hub (16). The hub (16) is mechanically coupled to the fuselage (14) and to multiple blades (40) and is rotated by an engine (22). A retractable fairing (60, 64) covers a portion of the hub (16). An actuator (26) is coupled to the fairing (60, 64). A controller (28) is coupled to the actuator (26) and retracts the fairing (60, 64). A method of reducing drag on the aircraft includes transitioning between a rotary-wing mode and a fixed-wing mode. The fairing (60, 64) is deployed over a portion of the hub (16) upon the completion of the transition between flight modes.

Abstract: A rotorcraft, such a helicopter or a tiltrotor aircraft, includes a light emitting device configured to provide light at a tip of a rotor blade. The light emitting device includes a light emitting diode arranged on the rotor blade, and a power source, wherein the power source is configured to power the light emitting diode due to a movement of the rotor blade. The power source may include a piezo-electric material configured to create a voltage due to movements of the rotor blade or an electrical generator including a stationary magnet assembly and a moveable coil assembly arranged on a shaft that rotates the rotor blade.

Abstract: A helicopter collapsible deck having at least one longitudinal member and at least one cross member, which extend respectively in a first and second direction intersecting at a point; the cross member is interrupted at the point of intersection; the deck also has an anchoring device for connecting the longitudinal member and the cross member at the point of intersection; and the anchoring device has at least one local permanent deformation section lying in a plane crosswise to the deck and for dissipating the energy transmitted to the deck in the event of impact.

Abstract: A locknut which defines a multiple of inner apertures about an inner diameter and a multiple of outer apertures about an outer diameter.

Abstract: A vehicle that can operate as either a motorcycle or an autogiro, said vehicle having a flight mode and a motorcycle mode, said vehicle comprising: a frame having a front part and a rear part; a center-line that passes from the front of said vehicle to the rear of said vehicle through the center of said vehicle such that said vehicle's weight is distributed nearly equally to either side of said center-line; a propeller mounted to a propeller barrel that is rotatably mounted to said frame such that the junction where said frame's front part meets said frame's rear part is located within said propeller barrel; an engine mounted to the rear part of said frame, wherein said engine powers said propeller in said flight mode; a cockpit fixedly mounted to the front part of said frame, said cockpit comprising means for controlling said vehicle; at least one aircraft lift means comprising: at least one rotor that is rotatably mounted to said frame when said vehicle is in said flight mode; a front wheel steerably and

Abstract: The present invention consists of an aerial device, comprising a structure and a rotating element equipped with at least one blade, suitable for effecting a rotation relative to the structure around a rotation axis, wherein the device is equipped with means making it possible to cause the rotating element to rotate relative to the structure and wherein these means include a gas generator and a pipe that makes it possible to guide the gas towards an orifice at a distance from this rotation axis in order to cause the rotating elements to rotate by means of the gas ejected through the orifice, characterised in that the generator outlet and the pipe are part of the rotating elements and are suitable for rotating around the rotation axis relative to the structures.

Abstract: A rotor assembly having a rotor hub, a plurality of yokes, and a plurality of swing arms is provided. The yoke depending from the rotor hub. Each swing arm is movably positioned on the rotor hub for rotation between an unlocked position and a locked position. The yokes are freely movable about a pitch axis and a lead/lag axis when the swing arms are in the unlocked position and the yokes are locked in a predetermined pitch position and a predetermined lead/lag position when the swing arms are in the locked position.

Abstract: A helicopter having a drive in turn having an air intake conduit; a main rotor connected functionally to the drive; and a transmission interposed functionally between the main rotor and the drive and housed in a housing. The helicopter has at least one air intake in turn having: a first inlet connected fluidically to the intake conduit; at least one second inlet connected fluidically to the housing; and deflecting means interacting, in use, with an airflow to divide the airflow into a first and a second airflow. The air intake also has guide means for guiding the first airflow along a first path extending from the deflecting means to the first inlet, and for guiding the second airflow along a second path separate from the first path and extending from the deflecting means to the second inlet.

Abstract: A centrifugal force bearing having a means for providing a steady pitching moment is disclosed. The centrifugal force bearing may optionally comprise a coning means. A rotor system having the centrifugal force bearing is disclosed. A rotary-wing aircraft having the centrifugal force bearing is disclosed.

Abstract: A system for limiting the exchange of shock and vibration motions and forces between a load and its supporting structure including an isolator. In one aspect, the isolator is designed for in-line mounting with a support strut. The isolator includes an elastomer member that may be substantially permanently maintained in a compression/shear state.

Abstract: An apparatus for converting a manned aircraft of a type including at least one pilot control capable of manipulation to affect operation of the aircraft for unmanned flight operations includes first and second actuators, each configured to selectively provide movement or resistance to movement in a first manner including linear or rotational motion, first and second clutches, each configured to selectively couple movement of the associated actuator to the pilot control, and a vehicle controller capable of being selectively enabled to operate the pilot control actuators and clutches and thereby provide unmanned operation of the aircraft, or of being disabled, thereby providing for manned operation of the aircraft. The first actuator has a first scope describing a first amount of allowable movement, while the second actuator has a second scope larger than the first scope.

Abstract: The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC1 and MC2). The device is remarkable in that it comprises check means (C) provided with main means (C1), the main means (C1) controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f) as determined in accordance with the method of the invention.

Abstract: An unmanned aerial vehicle (UAV) has a payload or body affixed at one end of an elongated airfoil. The entire airfoil/payload combination rotates about a center of mass to define a rotor disk. Thrust is provided by air-augmented rocket engine thrusting tangentially at a location remote from the payload. A control system maintains knowledge of its environment, as by a camera, to produce directional control signals which actuate lift control means in synchronism with the rotational position of the vehicle. A deployable object may be carried. Protection of the stowed vehicle is provided by blister packaging.

Abstract: The invention relates to a rotor blade (20), especially for a rotary wing aircraft.

Abstract: Embodiments of systems and methods for enhancing the performance of rotary wing aircraft through reduced torque, noise and vibration are disclosed. In one embodiment, a method includes configuring the rotorcraft in a selected flight condition, communicating input signals to a control system operable to position sails coupled to tips of blades of a rotor assembly, processing the input signals according to a constraint condition to generate sail positional information, and transferring the sail positional information to the sail. Alternately, input signals may be communicated to a control system operable to position a plurality of sails, each sail having an aerodynamic shape and positioned proximate to a tip portion of the rotor blade. The input signals may be configured to rotate each sail about a longitudinal axis into a corresponding pitch angle independently of the other sails.

Abstract: A method of transitioning from a complex response flight state to a ground operation control state. Pilot intent is determined through collective position information to control the transition. An independent cockpit switch activates an emergency surface contact transition function for use with a fly-by-wire (FBW) flight control system. Once the surface contact transition function is active, FBW control laws transition from a fully augmented flight state, through an augmentation deactivation state and into the surface contact state.

Abstract: The invention relates to an unmanned helicopter comprising an internal combustion engine and an associated fuel tank. The unit (1) formed by the internal combustion engine and the gearbox is arranged essentially in a self-supporting housing (2) which is at least partially closed all the way round, and preferably consists of carbon fiber-reinforced plastic (CFK), a nose body (3) being connected to the front of said housing. In this way, a compact structure can be achieved.

Abstract: The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second end (22) connected to the engine at the rearmost portion thereof.

Abstract: A vehicle, comprising: a vehicle frame; a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame; a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid through from an inlet at the upper end of the duct through an exit at the lower end of the duct, and thereby produce an upward lift force applied to the vehicle; a first plurality of substantially parallel, spaced vanes non-pivotally mounted across at least the inlet end of the duct; and fluidic means for affecting the ambient fluid flow around the vanes to generate horizontal force components to the lift force applied to the vehicle.

Abstract: The design and refinement of a tethered hovering platform into a feasible working system is presented. To determine a starting point for the design, a detailed historical search was conducted to find the history and the current state of such technology. Real world current needs are analyzed to produce a mission specification and to drive the preliminary vehicle design. Analysis of environmental conditions and decisions about an initial payload package are made in conjunction with motor and propeller sizing. Initial concept testing to discover feasibility and operational issues was performed; from this, instability issues were discovered. Analyzing these instability issues using known rotorcraft and momentum effects, in conjunction with flight testing, yields possible solutions to the problem. The use of constrained layer dampers as a means of passive stabilization is addressed and suggested as the preferred solution. Testing of passive constrained layer damping verifies the stability of the solution.

Abstract: An aircraft capable of hovering, and having a fuselage defining an access opening; driving means for operating a rescue cradle; and a first wall movable between a closed position engaging a first portion of the opening, and a first open position allowing access to the first portion of the opening. The aircraft has a member connected functionally to the first wall and in turn having at least one flat surface; and the member is movable with respect to the wall into a first position, in which the flat surface defines a supporting surface for the cradle when the first wall is in the first open position.

Abstract: The invention is an unmanned flying helicopter aircraft platform (“aircraft platform”) that can be powered by either interchangeable electric motors or by fuel powered internal combustion engines. The aircraft platform is surrounded by a lightweight exoskeleton cage that protects the rotor blades from coming into contact with external objects. The aircraft platform uses a weight located on the bottom side of the aircraft platform that can be remotely moved to adjust the center of gravity in order to navigate in any direction. The aircraft platform has a place on its bottom side where attachments can be added or removed which allows the aircraft platform to be used for multiple different purposes. The aircraft platform can be flown and operated either remotely using a hand held control unit or it can be flown and operated by an onboard pilot located in the human carrying attachment.

Abstract: A vertical takeoff and landing aircraft, using for vertical lift and lateral thrust a redundant plurality of essentially similar electrically-powered and electronically-controlled thrust units mounted in a mechanically static or fixed fashion relative to one another in a substantially horizontal plane. The thrust units are situated in this planar array in aerodynamically approximate pairs, such that a complete failure of a single thrust unit would not substantially compromise the ability of the aircraft to maintain flight.

Abstract: DARPA's Heliplane Program Manager, Don Woodbury indicated that they did not realize how much of a challenge 400 mph (cruise speed) was. The interviewer noted: “In their initial assessment of the hurdles posed by the Heliplane's requirements GBA considered, rotor head drag was believed to be the simplest to deal with. . . . opposite . . . true.” Faster Gyrodynes . . . allows planes to have both Lift/Drag ratios and speeds equal, or approaching, those of fixed wing planes while having the VTOL/hover capability of a gyrodyne. This is achieved by making the rotor and related components retractable which eliminates their drag. If retracted within the fuselage and the presence of door(s) does not add parasitic drag, the L/D ratio should be the same as an otherwise identical fixed wing craft. If an external pod is required its drag will reduce the L/D ratio to some extent, Focus has been on the invention in context of its origin, the convertable fixed wing/gyrodyne hybrid.

Abstract: Apparatus and methods for alleviating rotary aircraft downloads are disclosed. In one embodiment, a rotary aircraft includes an airframe assembly having a fuselage, at least one rotor assembly operatively coupled to the airframe assembly and configured to provide a downwash over at least a portion of the airframe assembly during operation of the at least one rotor assembly, and at least one download alleviation strake operatively coupled to the fuselage, each download alleviation strake extending at least partially along a length of the fuselage and being configured to reduce a downwash download during operation of the at least one rotor assembly. In some embodiments, the airframe assembly includes at least one fuel tank, and the at least one download alleviation strake is coupled to the at least one fuel tank. The download alleviation strake may be pivotably coupled to the at least one fuel tank.

Abstract: A rotary aircraft has a fuselage with wings and a rotor. The blades of the rotor are twistable about a pitch axis to vary collective pitch. A collective pitch shaft moves in an advancing direction to increase the collective pitch. Weights are mounted to the blades for outward movement along the blades in response to an increase in rotational speed of the blades. A linkage between each of the weights and the collective pitch shaft moves the collective pitch shaft in the advancing direction in response to an increase in rotational speed. A spring acting through a cam mechanism exerts a non linear force in opposition to the outward movement of the blades.

Abstract: A helicopter includes a system to effect motion in a horizontal dimension thereby to direct the desired direction. The rotor blades are driven by a rotor shaft and which is hinge mounted on this rotor shaft, such that the angle between the plane of rotation of the main rotor and the rotor shaft may vary. A control for moving the angle of incidence of at least one blade of the rotor cyclically along at least part of a 360-degree rotation path around the rotor shaft. This causes a variation in a lift force of the blade along at least part of the rotations path. This causes the body to be urged in a relatively horizontal direction from a relative position of rest. The control includes an actuator for engaging with an assembly depending from the rotor, the inter-engagement of the actuator and assembly effecting a change in the angle of incidence of at least the one blade of the rotor. The system includes a rotor, preferably complemented with a stabilizer rotor.

Abstract: A dual ducted fan arrangement in which the duct components, engine, and avionics/payload pods are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan, stator, and control vane design. Assembly connections between ducted fans and electronic modules are also identical. An engine or APU drives the dual ducted fans through a splined shaft to a differential or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms on each of the splined shafts between the differential and ducted fans. In the electric motor case relative speed is through electronic speed control. The fans are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

Abstract: There is described a helicopter having a first member movable with respect to a second member; lubricated supporting means for supporting the first member with respect to the second member; and a primary lubricating circuit for lubricating the supporting means and in turn having primary storage means for accumulating a lubricating fluid, and primary fluid feed means for feeding the lubricating fluid to the supporting means; the helicopter also has an auxiliary lubricating circuit supplied continually by the primary storage means with a first lubricating fluid flow value, and itself continually supplying the supporting means with a second lubricating fluid flow value lower than the first value, so as to produce an auxiliary storage volume of lubricating fluid for use in the event of breakdown of the primary lubricating circuit.

Abstract: A gearbox of a rotary-wing aircraft includes at least one variable speed system which optimizes the main rotor speed for different flight regimes such as a hover flight profile and a high speed cruise flight profile for any rotary wing aircraft while maintaining an independently variable tail rotor speed.