Abstract: A drive system for a high speed rotary-wing aircraft includes a combiner gearbox in meshing engagement with a main gearbox. The combiner gearbox is driven by one or more engines such that a main rotor system and a translational thrust system are driven thereby. The engine drives the combiner gearbox and thus the main gearbox through an overrunning clutch. The drive system permits the main rotor system RPM to be controlled by offloading power to the translational thrust system during a high speed flight profile.

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: An aircraft has a streamlined structure (10) pierced by an air flow duct (20) having an axis of symmetry (AX) contained in a plane of symmetry (P) perpendicular to a longitudinal axis (AL) of the aircraft, the aircraft possessing a shrouded rotor (1) having a plurality of blades (2) arranged in the air flow duct (20). The aircraft is also fitted with blower elements (40) suitable for propelling compressed air towards a first injection zone (44) opening out in a first front inject (22?) of a first lip (22) of the periphery (21) of the duct (20) and towards a second injection zone (45) opening out in a second front portion (24?) of a second lip (22) of the periphery (21) of the duct (20).

Abstract: Disclosed is a rotary winged aircraft. More specifically, this invention relates to an aircraft wherein lift is generated by two discs which rotate about a central axis. The discs generate equal and opposite forces such that the central axis remains fixed, thereby allowing it to be used for a crew compartment. In one embodiment, the two discs are concentrically located.

Abstract: The present invention relates to a power plant (10) having a single engine (13) together with both a main gearbox (MGB) suitable for driving the rotary wing (3) of a helicopter (1) and a tail gearbox (TGB) suitable for driving an anti-torque rotor (4) of a helicopter (1). The power plant (10) also includes a first electric motor (11) mechanically connected to said main gearbox (MGB) in order to be capable of driving said main gearbox (MGB), and a second electric motor (12) mechanically connected to said tail gearbox (TGB) in order to be capable of driving said tail gearbox (TGB).

Abstract: A rotary-wing apparatus that is aeronautically stable, easy to fly with a multidimensional control, small size, and safe to fly and low cost to produce. The rotary-wing apparatus includes a coaxial, counter rotating rotor drive providing lifting power with an inherent aeronautical stability; auxiliary propellers that face the direction of flight and are located on opposite sides of said coaxial rotary-wing apparatus and enable flying forwards, backwards and perform yawing. The rotary-wing coaxial helicopter toy is remotely controlled and safe to fly in doors and out doors, while performing exciting maneuvers even by untrained kids.

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: 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 helicopter that adopts a two-stroke internal combustion engine equipped with a centrifugal force-resistant propeller fan or fan turbine, or that can rotate clockwise (CW) and counterclockwise (CCW) during driving to directly propel the rotors and realize flight using a rotor wing that reconfigures into a hovering state. The helicopter reduces emissions via improved ventilation and a scavenging air system, reduces aerodynamic loss, reduces the access fee, and possesses the functions of a rotor wing that reconfigures into a hovering state.

Abstract: The Invention is a rotary-wing aircraft having at least two vectored thrusters that may be tilted from a horizontal to a vertical position and to positions intermediate between the horizontal and vertical positions. The two vectored thrusters are equipped with propellers having separately variable pitch. The two vectored thrusters also are equipped with vanes having selectable vane angles to direct separately the air flow from the two vectored thrusters. A control system detects the flight condition of the aircraft and selects vectored thruster control settings corresponding to the detected flight condition and consistent with predetermined control rules to provide lift, thrust, yaw moments and roll moments.

Abstract: A de-rotation system includes a planetary gear set, and a fairing support structure mounted for rotation with a first ring gear.

Abstract: An aircraft comprising a main propeller 1 at the top of the aircraft which consists of an assembly of blades 2, 3, a rotor 4. The propeller is rotated by a main power plant 5. The main power plant is connected to the main body 6 of the aircraft by a tilt enabling joint 7. The tilt enabling joint allows tilting of the main power plant 5 and propeller relative to the main body 6 of the aircraft to occur in a controlled manner during flight. To counter the rotational force exerted on the main body 6 of the aircraft by the rotation of the blades 2, 3, an additional power plant is attached to aircraft which comprises an additional propeller which is rotated by an additional engine assembly 16. The additional propeller is a rotor and blade assembly consisting of blades 17 and 18, and a rotor 19. Rotation of the additional propeller pushes air in a primarily horizontal direction by way of the pitch of the blades 17 and 18.

Abstract: An absorbent structure for reducing the propagation of soundwaves emitted by noisy devices such as rotors or motors, the structure includes a rigid partition (1), at least one porous wall (4), and separator elements (2) for placing the porous wall (4) at a determined distance from the rigid partition (1), defining cavities (3) of a height h1 between the porous wall (4) and the rigid partition (1), the height h1 being determined to obtain maximum absorption of a given frequency of the emitted soundwaves, wherein includes additional absorption elements for obtaining maximum absorption of at least one additional frequency of the emitted soundwave.

Abstract: A rotorcraft having an enhanced configuration in which a simple wing and a propulsive anti-torque system are combined is disclosed. The propulsive anti-torque system includes an anti-torque thruster system in which a variable pitch fan is installed internal to the tail boom of the rotorcraft and an anti-torque thruster nozzle is mounted at the extremity of the tail boom. The fan is driven directly from the main rotor drive. The configuration and location of the fan allows the primary exhaust from the engine to be mixed with the compressed air flow from the fan. The mixed air flow from the fan and the engine passes through the tail boom and out the thruster nozzle.

Abstract: The present invention relates to a tail rotor system for an aircraft, in particular for a helicopter, with a multi-blade tail rotor with fixed blade angle of attack and to a method for controlling a tail rotor system for an aircraft, in particular for a helicopter.

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 take-off aircraft is disclosed. Looking at the aircraft it can be seen that the aircraft comprises a main power plant 1 at the top of the aircraft which consists of an assembly of blades 2, 3, a rotor 4 and a main engine assembly 5. The main power plant is connected to the main body 6 of the aircraft by a tilt enabling joint 7. The tilt enabling joint 7 allows tilting of the main power plant 1 relative to the main body 6 of the aircraft to occur in a controlled manner during flight. A universal joint 8 is used to allow tilting to occur. The tilt enabling joint 7 is fitted with a combination of hydraulic actuators 9, 10 and springs 11, 12 and 13 that allow the tilting of the tilt enabling joint 7 to be controlled. Tilting of the main power plant 1 thus initiates changes in the direction of travel of the aircraft without the need to change the pitch angles of the blades 2 and 3.

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 thrust generator is provided. The thrust generator is configured to introduce a motive fluid along a Coanda profile and to entrain additional fluid to create a high velocity fluid flow, wherein the high velocity fluid flow is configured to generate thrust for counter-acting a torque generated by a rotating component.

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.

Abstract: A yaw control system and a method of controlling yaw for an aircraft are provided. The yaw control system includes a first wing set and a second wing set which are rotatable in opposite directions. Each of the wing sets includes at least two wings each including a pivotable flap forming a trailing edge of its respective wing. A flap control assembly controls the pivotable flaps of the first wing set and of the second wing set such that when the pivotable flaps of the first wing set are pivoted in a first direction by a first set angle, the pivotable flaps of the second wing set are simultaneously pivoted by a second set angle in an opposite direction, thereby providing yaw control for the aircraft.

Abstract: This disclosure involves aerial robots that dispenses conductive filament or systems, methods, and software for support such aerial robots. One remotely powered aerial robot system includes an aerial robot and a power source. The aerial robot comprises a body, a first propeller coupled to the body and operable to provide thrust to the aerial robot, a rotatable spool coupled to the body, and a conductive filament that is dispensed from the spool by rotation of the spool is one direction and retrieved by rotation of the spool in another direction. The power source is coupled with, and remote from, the aerial robot via the conductive filament, where the conductive filament is operable to power the first propeller using power from the power source.

Abstract: A rotor hub fairing system includes an upper hub fairing, a lower hub fairing and a shaft fairing therebetween. The rotor hub fairing system is attached to the counter-rotating, coaxial rotor system through a bearing arrangement such that the shaft fairing may be positioned at an azimuthal position about the main rotor axis of rotation relative the airframe by a de-rotation system. The de-rotation system controls the position of the shaft fairing about the axis of rotation such that the shaft fairing is prevented from rotating freely in unison with either shaft as may otherwise result during some flight regimes.

Abstract: A de-rotation system includes a first ring gear defined about an axis of rotation, a second ring gear defined about the axis of rotation and a gear set in meshing engagement with the first ring gear and the second ring gear to control a position of a housing about the axis of rotation.

Abstract: The Invention is a rotary-wing aircraft having at least two vectored thrusters that may be tilted from a horizontal to a vertical position and to positions intermediate between the horizontal and vertical positions. The two vectored thrusters are equipped with propellers having separately variable pitch. The two vectored thrusters also are equipped with vanes having selectable vane angles to direct separately the air flow from the two vectored thrusters. A control system detects the flight condition of the aircraft and selects vectored thruster control settings corresponding to the detected flight condition and consistent with predetermined control rules to provide lift, thrust, yaw moments and roll moments.

Abstract: A rotary-wing aircraft with an electric motor mounted along an axis of rotation to drive a rotor system about the axis of rotation.

Abstract: An objective of the invention, focusing on these issues involved in the use of a small, hobby-type, unmanned helicopter, is to develop an autonomous control system comprising autonomous control systems for a small unmanned helicopter, to be mounted on said small unmanned helicopter; a servo pulse mixing/switching unit; a radio-controlled pulse generator; and autonomous control algorithms that are appropriate for the autonomous control of the aforementioned small unmanned helicopter, thereby providing an autonomous control system that provides autonomous control on the helicopter toward target values.

Abstract: An aircraft has a streamlined structure (10) pierced by an air flow duct (20) having an axis of symmetry (AX) contained in a plane of symmetry (P) perpendicular to a longitudinal axis (AL) of the aircraft, the aircraft possessing a shrouded rotor (1) having a plurality of blades (2) arranged in the air flow duct (20). The aircraft is also fitted with blower elements (40) suitable for propelling compressed air towards a first injection zone (44) opening out in a first front inject (22?) of a first lip (22) of the periphery (21) of the duct (20) and towards a second injection zone (45) opening out in a second front portion (24?) of a second lip (22) of the periphery (21) of the duct (20).

Abstract: According to the present invention, In case of tail rotor failure in a helicopter, pilot will activate Cockpit control unit which is installed in cockpit, wherein said unit contains activation switch and electronic circuits that automatically performs steps of: determining and releasing a predetermined pressurized gas from a capsule, wherein said capsule is located within the helicopter, and wherein said predetermined pressurized gas is based on a level of pressure in said capsule, and feedback received form yaw movement; and thereby compensating tail rotors torque and stabilizing said helicopter.

Abstract: A de-rotation system includes a first ring gear defined about an axis of rotation, a second ring gear defined about the axis of rotation and a gear set in meshing engagement with the first ring gear and the second ring gear to control a position of a housing about the axis of rotation.

Abstract: An aerial robot is disclosed. The aerial robot may include at least one pair of counter-rotating blades or propellers, which may be contained within a circumferential shroud or a duct. In one embodiment, the aerial robot may have the ability to hover and move indefinitely. Electric power to the robot may be provided by a tether or an on-board power supply. In tethered embodiments, a solid-state, electronic voltage transformer may be used to reduce a high voltage, low current source to lower voltage, higher current source. In one embodiment, secure data communication between a ground unit and the aerial robot is facilitated by impressing high bandwidth serial data onto the high voltage tether wires or a thin optical fiber which is co-aligned with the tether wires. In one embodiment, precise navigational and position controls, even under extreme wind loads, are facilitated by an on-board GPS unit and optical digital signal processors.

Abstract: A helicopter tail assembly includes a tail boom that extends along a tail axis, a tail fin mounted on one end of the tail boom, and a rudder mounted on the tail fin and pivotable relative to the tail fin about a pivot axis that is inclined with respect to the tail axis at an angle greater than 0 degrees and less than 90 degrees.

Abstract: The Invention is a rotary-wing aircraft having at least two vectored thrusters that may be tilted from a horizontal to a vertical position and to positions intermediate between the horizontal and vertical positions. The two vectored thrusters are equipped with propellers having separately variable pitch. The two vectored thrusters also are equipped with vanes having selectable vane angles to direct separately the air flow from the two vectored thrusters. A control system detects the flight condition of the aircraft and selects vectored thruster control settings corresponding to the detected flight condition and consistent with predetermined control rules to provide lift, thrust, yaw moments and roll moments.

Abstract: An aircraft can include a tail section and a stabilizing system coupled to the tail section. The stabilizing system has a vertical stabilizer and at least one strake that cooperate to generate forces that compensate for a reaction torque generated by a main lifting rotor that produces lifting forces when the aircraft is in flight. Methods for improving aircraft performance include installing the at least one strake and retrofitting of a vertical stabilizer to increase thrust forces produced by a tail rotor.

Abstract: A method and a device reduces the vibration generated on the structure 17 of a helicopter 2 by the flow of air through the main rotor 5 and by the flow of air along the fuselage 3. The device 1 includes: at least one sensor 18, 19, 20 measuring the vibration generated on the structure 17; and computer element 30 responsive to the vibration measurements to determine variation in the angle of incidence of a tail fin 9 of the helicopter 2 suitable for generating an opposing force {right arrow over (T1)}, {right arrow over (T2)} for opposing the vibration, and transmitting the variation in angle of incidence as determined in this way to a control system 10 for controlling the angle of incidence of the tail fin 9.

Abstract: A method and a device allow for reducing the vibration generated on the structure 17 of a helicopter 2 by the air flow through the main rotor 5 and by the air flow along the fuselage 3. The device 1 includes: at least one sensor 18, 19, 20 measuring the vibration generated on the structure 17; and computer element 30 responsive to the measurements to determine a variation in angle of incidence for a stabilizer 39 of the helicopter 2 that is suitable for generating a vertical opposing force {right arrow over (TZ)} for opposing the vertical vibration, with the variation in angle of incidence as determined in this way being transmitted to a system 10 for controlling the angle of incidence of the stabilizer 39.

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.

Abstract: Aircraft including an airframe having a fuselage extending between a forward end and an aft end and a fixed wing extending laterally from the fuselage. The aircraft includes a power plant mounted on the airframe producing exhaust during operation. The aircraft includes a rotor/wing rotatably mounted on the airframe including a plurality of blades and an adjustable nozzle mounted on the airframe downstream from the power plant exhaust for selectively directing the power plant exhaust to exit the aircraft at a pre-selected angle with respect to the airframe within a range of angles extending from about horizontally rearward to about vertically downward.

Abstract: An air-based thrust recovery system for use in a powered lift platform utilizing fixed-pitch propellers is provided. The system utilizes an air compressor coupled to the drive motor of the platform and an on-board, high pressure tank for air storage. The fixed-pitch propellers are coupled to the primary drive system with over-running clutches, thus allowing the thrust recovery system to rotate the propellers faster than if driven solely by the primary drive system. Preferably the propellers are surrounded by air ducts. The thrust recovery system uses individually, or in combination, cold air jets mounted at the tips of the propellers, a circulation control system which blows out the leading or trailing edge of the propellers, and one or more perforated tubing segments surrounding at least a portion of the platform's air ducts.

Abstract: An autogyro, or aircraft with a rotating wing, has an airframe providing a motorcycle-like configuration for the rider. The motorcycle-like straddle-type seat locates the rider in front of the rotating wing, behind a teardrop shaped simulated fuel tank, and above the motorcycle engine used for turning the front-mounted propeller. A motorcycle-like handlebar controls the aircraft, including the adjustment for the rotating wing axis of rotation with respect to the aircraft and the engine throttle. Additional controls for operating the aircraft on the ground, such as wheel brakes and the steering, are also controlled from the handlebar.

Abstract: A system for providing aircraft thrust includes a compressor, operable to take in a quantity of air, reduce the volume of the air to generate compressed air, and to deliver the compressed air to a tank. The tank is coupled to the compressor and is operable to receive the compressed air, store the compressed air, and deliver the compressed air to a nozzle mounted externally to the aircraft. The nozzle is operable to receive the compressed air and discharge the compressed air to provide thrust for the aircraft.

Abstract: A helicopter having a torque-correcting thruster device. The helicopter has an aerodynamic body which has opposite side portions, a top portion and a bottom portion. The aerodynamic body has a cockpit and a pilot seat in the cockpit. The helicopter includes landing gear attached to the bottom portion of the aerodynamic body. The helicopter includes a rotor that is supported by the aerodynamic body and a rotor blade attached to the rotor, and a thruster device operative on one of the side portions of the aerodynamic body to produce an aft-directed thrust that counteracts the torque produced by rotation of the rotor blade so as to control the yaw of the helicopter. The aft-directed thrust simultaneously supplements the forward thrust of the helicopter.

Abstract: A vertical stabilizer (38) is supported by and projects upwardly and rearwardly from the tail portion (14) of a helicopter fuselage (12). A tail rotor (TSR) is mounted on the vertical stabilizer (38) for rotation about a horizontal axis (C). The tail rotor (TSR) is positioned laterally outwardly from one side of the vertical stabilizer (38). The vertical stabilizer (38) has an upper end, a lower end and a rear edge recess (44) located between the upper end and the lower end. The recess (44) has a laterally convex rear edge (50). The tail portion (14) of fuselage (12) has a rear end extension (40) that extends rearwardly from the vertical stabilizer (38) and narrows in width as it extends rearwardly. The rear end extension (40) of the fuselage (12) provides vertical area to replace vertical area that was removed by placement of the recess (44) in the vertical stabilizer (38).

Abstract: An anti-torque thruster system implemented onboard an aircraft comprising a propulsion means coupled to the aircraft, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the aircraft, a fuel storage container coupled to the propulsion means via a fuel delivery conduit, wherein the fuel storage container is capable of storing an appropriate fuel for the propulsion means, a valve means disposed between the fuel storage container and the propulsion means, wherein the valve means may be useable to regulate the flow of fuel from the fuel storage container to the propulsion means, and a controller for controlling the valve means to regulate the flow of fuel from the fuel storage container to the propulsion means, wherein the controller is capable of receiving input from at least one input device.

Abstract: A tail rotor system for a helicopter includes a gear box housing retainer (66) coupled to the tail boom (16) of the helicopter. The tail rotor system also includes a power-limiting device (50) configured to disconnect the tail rotor from a power plant for driving the tail rotor about a rotor axis of rotation.

Abstract: A vertical stabilizer (38) is supported by and projects upwardly and rearwardly from the tail portion (14) of a helicopter fuselage (12). A tail rotor (TSR) is mounted on the vertical stabilizer (38) for rotation about a horizontal axis (C). The tail rotor (TSR) is positioned laterally outwardly from one side of the vertical stabilizer (38). The vertical stabilizer (38) has an upper end, a lower end and a rear edge recess (44) located between the upper end and the lower end. The recess (44) has a laterally convex rear edge (50). The tail portion (14) of fuselage (12) has a rear end extension (40) that extends rearwardly from the vertical stabilizer (38) and narrows in width as it extends rearwardly. The rear end extension (40) of the fuselage (12) provides vertical area to replace vertical area that was removed by placement of the recess (44) in the vertical stabilizer (38).

Abstract: To achieve the required optional conformability and navigability of the hovering motion of the hovering body in a free liquid environment, the hovering body is equipped with a suitable created mechanism for optional control of direction and/or the position of the hovering motion in the form of the basic jacket suitably equipped with at least one slot jet where the basic jacket is suitably connected to the elongated jacket mechanism for the optional stabilization of the direction and/or the position of the hovering motion suitably equipped with at least one uplift component.

Abstract: A propeller related vehicle in accordance with one embodiment of the present invention is described as a helicopter having an airframe housing a pneumatic motor mechanism for powering a main propeller attached to a main drive shaft. The helicopter further includes a horizontal stabilizing means attached between the main propeller and the main drive shaft, which permits the main propeller to freely pivot about the main drive shaft independently from the airframe. As such when the main propeller is rotating and the main propeller begins to pitch, the rotating main propeller has a centrifugal force created by the rotation thereof and will tend to pivot about the horizontal stabilizing means in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position.

Abstract: A preferred embodiment of a rotary-wing aircraft comprises a main rotor, a tail boom extending through an area of downwash from the main rotor, and a linear nozzle fixedly coupled to the tail boom and having an opening extending along the tail boom for discharging a sheet of fluid in a direction substantially tangential to an outer surface of the tail boom. A preferred embodiment also comprises a yaw-control device movably coupled to the tail boom and having an opening formed therein for discharging fluid in a direction away from the yaw-control device and into the area of downwash from the main rotor.

Abstract: An anti-torque thruster system implemented onboard an aircraft comprising a propulsion means coupled to the aircraft, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the aircraft, a fuel storage container coupled to the propulsion means via a fuel delivery conduit, wherein the fuel storage container is capable of storing an appropriate fuel for the propulsion means, a valve means disposed between the fuel storage container and the propulsion means, wherein the valve means may be useable to regulate the flow of fuel from the fuel storage container to the propulsion means, and a controller for controlling the valve means to regulate the flow of fuel from the fuel storage container to the propulsion means, wherein the controller is capable of receiving input from at least one input device.