603 results about "Tail rotor" patented technology

An electric rotary machine is disclosed which can adjust relative angles of sub-rotors continuously and regardless of torque direction without generating an attractive force between the field magnets of the sub-rotors. The electric rotary machine includes: a stator having a winding; a dual rotor which is rotatably disposed with a gap from the stator and divided axially along a shaft into a first rotor and a second rotor each having field magnets with different polarities arranged alternately in a rotation direction; a mechanism for varying the axial position of the second rotor relative to the first rotor continuously; and a non-magnetic member located between the first rotor and the second rotor.

Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.

A coaxial helicopter, comprising a first rotor carried by a first shaft and a second rotor carried by a second shaft; wherein one of the first and second rotors has cyclic pitch control and the other rotor does not have cyclic pitch control, at least pitch and roll control being implemented by cyclic blade pitch control of only one rotor of the coaxial rotor set. Provisions for yaw control can include differential collective control of the first and second rotors, providing yaw paddles and/or a tail rotor, ducted fan, or an air jet configured for yawing the coaxial helicopter.

The invention relates to a miniature electric ducted propeller type intelligent unmanned aerial vehicle, which consists of a ducted casing, a bracket, a coaxial counter propeller, a fairing, a battery, a motor, a driving control circuit and a microcontroller. The machine body has a dish-shaped appearance; and the ducted casing is arranged outside a rotor wing to eliminate flight safety threat caused by the traditional structure of the exposed rotor wing and improve the working efficiency of the propeller. The aerial vehicle adopts a design of the coaxial counter double-rotor wing, cancels the inertial rotation of the machine body without a tail rotor wing, saves materials and expands the operating space. The propeller is driven by the motor; the motor is under the servo control of the driving control circuit; and the horizontal motion of the aerial vehicle in the air is implemented by a deflectable guide plate below the propeller in a matching mode. In addition, a multi-azimuth convenient slot is formed inside the ducted casing of the aerial vehicle for mounting and detaching various sensors at any time; and the microcontroller comprehensively processes information fed back by each sensor and performs autonomous flight control according to a task.

The invention relates to a tilt rotor aircraft adopting parallel coaxial dual rotors, which comprises a fuselage, wings, an empennage, a pitch control scull system, a landing gear, a power and fuel system, a transmission system, a rotor system, a rotor nacelle and a tilt system, wherein the wings are arranged at the center section of the fuselage; the empennage and the pitch control scull system are arranged at the tail of the fuselage; the landing gear is positioned at the belly of the fuselage; the power and fuel system is arranged inside the center section of the fuselage and is connected with the rotor system and the pitch control scull system through the wings and the transmission system in the fuselage; the rotor system is arranged on the rotor nacelle at the tip of the wings; partial wing which is fixedly connected with the rotor nacelle and simultaneously can tilt is arranged at the inner side of the rotor nacelle; and the tilt system is arranged in the wings and is connected with the rotor nacelle and the partial wing which can tilt. The tilt rotor aircraft is mainly characterized by adopting the pitch control scull system, the parallel coaxial dual rotors and the partialwing which can tilt to realize flight status transformation and conventional taxiing and landing, thereby improving the forward speed and the propulsive efficiency.

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.

A spoiler attached to helicopter main rotor blades, tail rotor blades, propellers, aircraft wings, and machined into turbine blades, that reduces vibration and silences their operation. Also, when added to a substantial part of the trailing edges of its rotor blades, the spoiler eliminates the repetitive pop-pop sound common to current helicopter flight. Preferably, the spoiler is made from durable resilient materials that bend with resistance for high speed oscillation and it is secured on the top or bottom side, or both, of the trailing edge of a blade or wing. Further, the free edge of the spoiler exhibits a non-repeating pattern of feather-like projections that collectively break up vortex formation so that the next wing or blade traveling through the same location has clean air/fluid in which to move. In addition to noise reduction, the spoiler increases blade efficiency and wing lift.

A rotary wing aircraft (1) provided with a main lift rotor (2), a tail rotor (5), and a power plant (4) driving a main gearbox (3) that co-operates with said main rotor (2), said tail rotor (5) being provided with a plurality of blades (10) of variable pitch (I) and with a pitch modification device (20), and said aircraft (1) having control means (30) for controlling said pitch modification device (20). The aircraft (1) includes an electric motor (9) for rotating said tail rotor (5) and regulator means (TRCU) connected to the control means (30) and also to the electric motor (9) and to the pitch modification device (20). The regulator means (TRCU) generate a first setpoint concerning pitch that is transmitted to the pitch modification device (20), and a second setpoint for controlling a motor parameter that is transmitted to the electric motor (9).

A toy radio-controlled helicopter includes: a main rotor, attached on the top of a fuselage and driven by a motor incorporated in the fuselage; a tail rotor that is driven by the motor and is attached to a tail unit provided at the end of a horizontally elongated boom that is extended from the rear of the fuselage; right and left movable wings, attached to the right and left sides of the fuselage below the main rotor, that can be rotated by respective actuators incorporated in the fuselage; and a receiver incorporated in the fuselage to control the operations of the motor and the actuators.

The invention discloses a ducted coaxial multi-rotor type aircraft and belongs to the field of special aircrafts. The multi-rotor type aircraft comprises an airframe structure, a power system and a control system. The airframe structure comprises a central duct, a main rotor and a plurality of assistant rotors evenly distributed at the peripheral of the central duct. The main rotor comprises an upper propeller and a lower propeller. The upper and lower propellers are fixed in the central duct. The centers of the upper and lower propellers are at the same vertical axis and the directions of the upper and lower propellers are opposite. A rotation device is connected to the outside of a supporting structure. The assistant rotors are connected to the rotation device through retractable rocker arms. The rotation device controls the rocker arms to drive the assistant rotors to rotate around connection points of the assistant rotors and the supporting structure. The assistant rotors can rotate and move freely, and therefore the aircraft can change the lift force distribution of the aircraft according to flight needs and a good maneuvering characteristic of the aircraft is achieved. The assistant rotors can be retracted into the inside of the central duct so as to reduce the size of the aircraft, thus facilitating flight in narrow spaces.

The invention discloses a composite type multi-mode multi-purpose aircraft, and belongs to the technical field of overall design of aviation flight vehicles. The aircraft comprises a body of a fixed wing aircraft, a driving/autorotation rotor wing system, an expelling aero-engine and a flying control system, wherein the driving/autorotation rotor wing system comprises paddle hubs and paddles; the paddles are hollow, and guide tubes B are communicated with the inner parts of the paddles; an H2O2 catalysis decomposition engine is mounted at the tail end of each paddle; the H2O2 catalysis decomposition engines are connected with the guide tubes; the guide tubes are communicated with guide tubes A; the guide tubes A are connected with an H2O2 storage box. The aircraft disclosed by the invention has the property of vertical/short-distance lifting and suspension, or even can achieve certain back flying and side flying, and can also fly forwards at a high speed; due to adoption of paddle tip air injection driving/autorotation wings, no reaction torque is generated in any mode, and thus a tail rotor as well as a speed reduction transmission and control mechanism of an ordinary helicopter are canceled; the differential thrust for thrusting an aero-engine is adopted to control to achieve steadiness and control in flying direction at a low speed, the waste weight and the energy consumption are reduced, the cost is lowered, the complexity is alleviated, and the flying security in a complex environment is effectively improved.

The invention discloses a pilotless helicopter, comprising a main rotor system, a swash plate device, a drive system, a starting device, an engine, a body frame, a tail rotor device, a landing device and at least one auxiliary lift, anti-twisting force and cooling functional device, wherein the auxiliary lift, anti-twisting force and cooling functional device comprises ducts and a lift fan, the lift fan is annularly embraced in the ducts, and the ducts are arranged symmetrical about a central axis which is the advancing direction of the pilotless helicopter; the ducts are fixed above the engine, and an air guide passage is designed below the ducts and guides air to a cylinder of the engine; and the swash plate device is a four-channel hybrid control swash plate device. A part of additional lift and anti-twisting force are provided for the pilotless helicopter by using the power of the cooling engine, so that the pilotless helicopter has larger effective load and higher efficiency. Four steering engines of the four-channel hybrid control swash plate device are arranged in a manner of backing up each other, so that the stability is improved.

A deicing system includes dual deice system components to provide a redundant deice system. Each redundant portion of the system generally includes a controller, an air data computer, an ice rate controller, and an ice rate probe. The controller communicating a heating cycle which defines a multiple of electric pulse trains to sequentially provides power to a multiple of heating elements in a designated blade set. Each electric pulse train is defined by an element on-time, a null time between the element on-time for this element and the next element, and an off-time between repetition of the heating cycle for the first heater element. The element on-time is a function of outside air temperature (OAT). The off-time is a function of liquid water content. The tail rotor heating cycle is a more straightforward version of the main rotor heating cycle as each of the tail rotor blade are activated simultaneously and there is only a single heating element on each tail rotor blade.

A helicopter has a main rotor with propeller blades which is driven by a rotor shaft and which is hinge-mounted to this rotor shaft. The angle between the surface of rotation of the main rotor and the rotor shaft may vary. A swinging manner on an oscillatory shaft is essentially transverse to the rotor shaft of the main rotor and is directed transversally to the longitudinal axis of the vanes. The main rotor and the auxiliary rotor are connected to each other by a mechanical link. The swinging motions of the auxiliary rotor controls the angle of incidence (A) of at least one of the propeller blades of the main rotor. There are wings from the body and a stabilizer at the tail.

A collision avoidance and warning system for a helicopter uses a type of emitted energy, for example radio frequency radar, from a transceiver positioned to cover a selected field of view for detecting an object or pedestrian in the vicinity of the helicopter. For helicopters that include a tail rotor assembly, the selected field of view can include a region around the tail rotor assembly so that when the helicopter is running on the ground, an alarm can be issued to persons approaching the tail rotor assembly. When the helicopter is in flight, the collision avoidance and warning system can alert the pilot when a portion of the helicopter outside of the pilot's field of view is in danger of a collision with an object.

The invention discloses a driving mechanism of a hybrid power helicopter. The driving mechanism of the hybrid power helicopter comprises a fuel tank, an engine, a clutch, a first locker, a planetary gear mechanism, an energy storage device, a generator/electric motor, a second locker, a second generator/electric motor, a torque coupler, a tail end gear box, a tail rotor subsystem, an swashplate and a rotor wing subsystem, wherein the clutch and the first locker are mounted between the engine and the planetary gear mechanism, and the second locker is mounted between the generator/electric motor and the planetary gear mechanism. Two power sources comprising a basic power source and an auxiliary power source are utilized, the two power sources are reasonably matched and selected when driving the helicopter, accordingly, the problems that the power source of a conventional helicopter is single, a drive system is complicated, a drive device is heavy, mechanical failure easily happens and the like are solved, and the safety and the maneuverability of the helicopter are improved.

A helicopter capable of preventing an increase in size of an airframe and achieving high-speed flight is provided. Provided is an airframe for supporting a main rotor so as to be rotatable, a propeller having a plane of rotation intersecting a plane of rotation of the main rotor, a propeller supporting portion that supports the propeller so as to be movable between positions behind and at the side of the airframe, and a tail disposed on the airframe, having a surface intersecting the plane of rotation of the main rotor.

A helicopter auxilary anti-torque system for efficiently supplying thrust and control at the tail of a helicopter during failure of the helicopter tail rotor. The helicopter auxilary anti-torque system generally includes a fluid thrust assembly selectively engageable onboard the helicopter, an auxiliary tail rotor selectively engageable onboard the helicopter, and at least one controller to operate the fluid thrust assembly and the auxiliary tail rotor to effect a controlled anti-torque force of the tail boom during failure of the conventional helicopter tail rotor. The fluid thrust assembly projects a non flammable fluid from the tail boom of the helicopter. The auxiliary tail rotor is collapsible within the tail boom of the helicopter when not in use. The fluid thrust assembly and the auxiliary tail rotor may be automatically activated in the case of the primary tail rotor failure, or activated by the pilot of the helicopter via one or more switches.