1127 results about "Pitch control" patented technology

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

There is provided a music editing apparatus for remix reproducing a plurality of sound materials, each formed from part or the entirety of a music piece, in combination, including a reproduction pattern control section, a reproduction speed control section; and a pitch control section.

Systems and methods are provided for positioning a therapy device, such as an ultrasound transducer, using a tilt sensor carried by the transducer and a positioner coupled to the transducer. The positioner provides roll and pitch control as well as translating the transducer in lateral and longitudinal directions. A processor receives signals from the tilt sensor corresponding to the actual rotational orientation of the transducer and controls the positioner to adjust the orientation of the therapy device until a desired position is achieved.

A rotor for use on an aircraft has a plurality (N) of rotor blades mounted on a plurality (N) of concentric masts. Each of the rotor blades has a rounded leading edge and a tapered trailing edge. The plurality (N) of concentric masts each operably mount one of the plurality of rotor blades at N different elevations. A locking element selectively locks or unlocks the concentric masts together in a plane of rotation, enabling the angle between any two rotor blades to be variable from 0-360 degrees during flight. A feathering hinge is operably attached to each blade for changing the pitch of each blade with respect to the plane of rotation as controlled by a pitch control mechanism.

A wind turbine system is provided with a wind turbine rotor, a pitch control mechanism, and an emergency power supply mechanism. The wind turbine rotor includes a blade having a variable pitch angle. The pitch control mechanism drives the blade to control the pitch angle. The emergency power supply mechanism generates electric power from rotation of the wind turbine rotor and feeds the electric power to the pitch control mechanism, in response to occurrence of an accidental drop of a system voltage of a power grid.

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.

A variable speed wind turbine having a passive grid side rectifier using scalar power control and dependent pitch control is disclosed. The variable speed turbine may include an electrical generator to provide power for a power grid and a power conversion system coupled to the electrical generator. The power conversion system may include at least one passive grid side rectifier. The power conversion system may provide power to the electrical generator using the passive grid side rectifier. The variable speed wind turbine may also use scaler power control to provide more precise control of electrical quantities on the power grid. The variable speed wind turbine may further use dependent pitch control to improve responsiveness of the wind turbine.

A road/air vehicle is able to quickly and easily convert between two configurations, air configuration and road configuration, to facilitate practical operation as both an aircraft and as an automobile. In air configuration the craft includes two laterally symmetrically flight surfaces; a smaller forward canard wing, generally horizontally disposed and a larger rearward main wing generally horizontally disposed with fin surfaces, generally vertically disposed, at each tip. Control surfaces on the main wing, the canard wing and the tip fins severally provide roll control, pitch control and yaw control in flight. The wheels/undercarriage are of a laterally symmetrical rectangular pattern, with the lateral distance between the two forward wheels and the two rearward wheels being similar. The forward wheels are steerable for ground operations. A suitable powerplant drives the rear wheels for ground operations. A second suitable powerplant provides direct atmospheric thrust for flight operations. In road configuration all flight surfaces and avionics sensors are folded and stored inside compartments within the body of the craft. Controls to facilitate both ground and flight operations are available for a single operator to perform the functions of both driver in road configuration and pilot in air configuration.

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 vehicle attitude controller capable of improving turning operability, steering stability, and ride quality of a vehicle. In a normal-operation region, a pitch control unit for calculating a target pitch rate in accordance with a roll rate performs control in priority to a roll suppression section. In this case, a target damping force calculated in the pitch control unit is weighed to control a damping-force characteristic of the dampers so that a pitch rate becomes equal to the target pitch rate. In a critical region in which a road-surface gripping state of the vehicle tires is bad, the roll suppression section performs control in priority to the pitch control unit so as to weigh a target damping force calculated in the roll suppression section. As a result, the damping-force characteristic of the dampers is controlled so as to increase the amount of roll suppression control.

An autonomous unmanned underwater vehicle (“AUV”) includes a body, a controller, a buoyancy engine, a rotary propulsion system and pitch control surface(s). The buoyancy engine is for alternately ingesting and expelling ambient water to change the mass of the AUV and thereby cause the AUV to alternately descend and ascend in the water. The pitch control surface(s) are for causing the AUV to move forward while alternately descending and ascending in the water. The rotary propulsion system includes a motor for rotating a propeller in the water to provide thrust. The controller is operative for responsively, automatically switching between at least the glider and rotary propulsion modes. In the glider mode, the buoyancy engine and the pitch control surface(s) are cooperative for causing the AUV to move forward while alternately descending and ascending. In the rotary propulsion mode, the rotary propulsion system is operative for causing the AUV to move forward.

An articulated rotor system with a servo-flap rotor control system locates the focal point of a blade retention spherical elastomeric bearing inboard of a joint in the servo-flap pitch control tube which separates the flap hinge and supports the servo-flap pitch control tube on a single pivot bearing within a blade retention spindle. Rotor blade flapping produces relative movements between the servo-flap pitch control tube and the blade retention spindle which is converted through a servo-flap drive linkage into servo-flap pitch motions to provide flap/pitch coupling which reduces steady and transient blade flapping.

A wind turbine is presented where the operation lifetime of the main bearing is extended by relieving the main bearing by reducing the mean bending moment on the bearing by means of individual pitch control of the blades of the rotor so as to create an aerodynamic mean tilt moment on the rotor by means of aerodynamic forces on the blades, the tilt moment at least partly counteracting the bending moment caused by the overhang load forces on the main bearing from the gravitational pull on the rotor mass.

In a wind turbine, an open loop control algorithm for incrementally or positively adjusting the pitch angles of individual rotor blades may be used to increase spacing between the base of the turbine tower and an approaching blade tip. As each rotating blade passes in front of the tower base, a minimum clearance distance may be assured to avoid blade tip strikes of the base. In accordance with at least one embodiment of the control algorithm, as each blade approaches the tower base, it may be feathered to reduce its power loading, and to facilitate increased clearance beyond the normal unloading or feathering produced by the so-called tower shadow effect. To offset resultant loss of torque, the remaining blades may be correspondingly pitched toward power, i.e. into the wind, to balance and/or smooth out the overall rotor torque curve, and thus to avoid torque ripples.

The invention provides a tiltrotor controlled by a double-propeller vertical duct. The tiltrotor, using the design of parallel twin-rotor and conventional aerodynamic configuration, consists of a fuselage, straight wings, rotors, a nacelle, an aileron, a vertical empennage, a rudder, an elevator, a horizontal empennage, a duct end cover, a vertical duct, an undercarriage, a power and decelerationsystem, a propeller power input shaft, a lower propeller, an upper propeller, louver-type slipstream sheets, a propeller gearing and collective-pitch controlling device, a propeller gear box supporting structure, a duct end cover driving device, a duct end cover motion slide rail and a slipstream sheet controlling device. Compared with the cyclic pitch control mode, the tiltrotor of the inventionsimplifies the operations during the vertical flight and the flight conversion and improves the reliability by using the structure of the double-propeller vertical duct to control the vertical flightand the conversion of the flight mode, and the tiltrotor has the advantages of long control force arm, high control efficiency and simple structure. Therefore, the tiltrotor constitutes a novel aircraft with significant development potential and promising future.

The invention is an aircraft that includes a flying wing having a plurality of extendable flaps mounted on the trailing edge of the flying wing. A canard is mounted on the nose of said flying wing. A system is mounted in the flying wing for providing high pressure air over the canard and the flaps. A second system is provided for controlling the flow of air over the canard to provide pitch control of the aircraft.

A hybrid helicopter (1) includes firstly an airframe provided with a fuselage (2) and a lift-producing surface (3), together with stabilizer surfaces (30, 35, 40), and secondly with a drive system constituted by: