97 results about "Rigid rotor" patented technology

A high speed centrifugal compressor for compressing fluids includes a permanent magnet synchronous motor (PMSM) having a hollow shaft, the being supported on its ends by ball bearing comprising supports. A permanent magnet core is embedded inside the shaft. A stator with a winding is located radially outward of the shaft. The PMSM includes a rotor including at least one impeller secured to the shaft or integrated with the shaft as a single piece. The rotor is a high rigidity rotor providing a bending mode speed of at least 100,000 RPM which advantageously permits implementation of relatively low-cost ball bearing comprising supports.

Rotorcraft wings disposed between tilt-rotor nacelles have particularly high aspect ratios for tilt-rotor rotorcraft, including for example at least 6, 7, 8, or higher. The increase in wing span and aspect ratio is possible because of the use of rigid and semi-rigid rotors, and/or higher modulus of elasticity materials allows increases the stiffness of the wings to the level required for avoiding whirl flutter. Tilt-rotor aircraft having high aspect ratio wings can advantageously further include a controller that provides reduced RPM in a forward flight relative to hover, and/or a controller that provides variable speed, (a so-called “Optimum Speed Tilt Rotor”) as set forth in U.S. Pat. No. 6,641,365 to Karem (November 2003).

The invention provides a coaxial rigid rotor coupling pneumatic elastic response analysis method, and belongs to a helicopter kinetic analysis technology. The method is characterized in that according to the operation and control characteristics of a coaxial rigid rotor helicopter, a balance equation optimization solution method is built, and an optimization solution is found according to the given target and constraint conditions. According to the characteristic of complicated coaxial rigid rotor flow field environment, a rotor flow field is calculated by using a computational fluid dynamic method based on an Euler/N-S equation; and then, the coupling pneumatic elastic response is calculated by using a computational fluid dynamic/computational structural dynamic loose coupling analysis method. The coaxial rigid rotor coupling pneumatic elastic analysis method has the advantage that when the analysis method is used, balance operation and control parameters, blade response, rotor loads and the like of the coaxial rigid rotor helicopter can be calculated. The method has good analysis precision and engineering applicability; the relying of the development process on the test can be reduced; and the design period and the development cost can be greatly reduced.

The invention relates to a stator for an eccentric screw pump or an eccentric worm motor having a stator, including an outer tube that is provided with a lining of rubber or a rubber-like material and has a hollow space, in the shape of a double or multiple spiral, for accommodating a rigid rotor that is also in the form of a spiral, whereby the spiral of the stator has one spiral more than does the motor. To provide a stator that also remains functional under conditions where the fixed connection between the lining and the outer tube would be destroyed, e.g. due to chemical influences or high temperatures, the invention proposes that an inner tube provided with apertures is disposed in the lining, and that spacing strips are disposed between outer tube and inner tube.

A method of counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes sensing angular velocity and angular acceleration of a helicopter during a flight maneuver. The angular velocity and angular acceleration are compared to a set of control parameters and one or more control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment. A control system for counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes one or more sensors configured to sense angular velocity and angular acceleration of a helicopter during a flight maneuver. A computer is operably connected to the one or more sensors and configured to compare sensor data to a set of control parameters. A plurality of control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment.

An upper rotor control system is contained within an upper rotor shaft and upper hub assembly of a contra-rotating rigid rotor system. A collective servo assembly includes a hydraulic actuator that provides collective pitch to all blades through axial extension/retraction of the control rod relative the upper rotor shaft for collective pitch control of the rotor blades. The collective servo assembly includes a spherical bearing for attachment of the control rod to aircraft structure. An X-Y positioner assembly includes a bearing arrangement which allows the shaft to rotate, while the X-Y positioner assembly remains non-rotational therein. The X-Y positioner assembly includes a multitude of hydraulic actuators, orthogonally positioned, to tilt the control rod about the spherical bearing off the axis of rotation of the upper rotor shaft for cyclic pitch control of the rotor blades.

The invention discloses a transverse rigid rotor blade helicopter, which comprises a fuselage, wings disposed at two sides of the fuselage, wing piers disposed on the wings, a main driving device disposed inside the fuselage, power transmission shafts disposed in the wings, rotor driving shafts disposed in the wing piers; propeller hubs, and blades; the invention is characterized in that: universal joints are disposed between the rotor driving shafts and the propeller hubs, and the blades are hinged to the propeller hubs in an axial direction. According to the invention, the position of the rotor rotating plane is not changed by complicated cyclic pitch control of routine rotor helicopters; the propeller hubs have simple structures; the rotor is simple in dynamics, and simple in operation, has high flying aerodynamic efficiency, good maneuverability, and low power dissipation.

The present invention provides a wind tunnel test platform inclined angle mechanism. The mechanism comprises a rotor wing installation frame (12), a torque motor (15), a slide rail (16) and a slide block (17). The rotor wing installation frame (12) is movably connected on a stand (1), the slide rail (16) is fixedly connected with the stand (1), and the slide block (17) is fixedly connected with the rotor wing installation frame (12); and when the torque motor (15) controls the rotor wing installation frame (12) to rotate or stop relative to the stand (1), the slide block (17) performs synchronous movement or stop with the rotor wing installation frame (12) relative to the slide rail (16) in the limited range of the slid rail (16). The wind tunnel test platform inclined angle mechanism can easily realize the inclined angle changing of a rotor wing so as to conveniently perform research of the aerodynamic characteristics of a rigid rotor in the condition of different rotor wing principal axis inclined angles, and can assist in development of the aerodynamic characteristic research of the coaxial rigid rotor and the aerodynamic performance contrastive study of different fixed principal axis inclined angles in the maneuvering flight condition of a helicopter; and moreover, the wind tunnel test platform inclined angle mechanism is simple in structure and low in making cost, etc.

The invention discloses a device and a method for automatic balancing for unbalance faults of a large rigid rotor, and belongs to the field of rotor balancing. The device for automatic balancing comprises a rotor and track mechanisms, wherein the rotor is arranged between two bearing brackets; the track mechanisms are respectively arranged at the vertical surfaces of both ends of the rotor; two counterweight trolleys are arranged in each track mechanism; a motor in each counterweight trolley is used for driving the corresponding counterweight trolley to rotate along the corresponding track mechanism; a vibration signal and a rotation speed signal detected by a sensor are transferred to a balance tester; the processed signals are transferred to a control system in each counterweight trolleyby a signal generator; the control system is used for sending a pulse signal to each motor, so as to control each counterweight trolley to move in the corresponding track mechanism. The device has the advantages that by arranging a vertical circular track for moving each counterweight trolley, the position of a balance block can be automatically obtained according to the fault conditions, and theautomatic balancing can be realized in the running process of the rotor; the time is shortened, and the benefit is improved.

The invention relates to a gas flotation high-speed motorized spindle which comprises a shell body, a bearing mechanism, a cylinder mechanism and a rotor mechanism. The rotor mechanism comprises a shaft core, a rotor, a pull rod, a pull rod sensing nut, an elastic component and a pull claw component, the elastic component is composed of a plurality of spiral belleville springs sleeve the pull rod,the shell body is provided with a sensing mechanism which is provided with a plurality of proximity switches sequentially from top to bottom, and the proximity switches respectively sense different positions of the pull rod sensing nut. The gas flotation high-speed motorized spindle has the advantages that an air bearing of the gas flotation spindle is integrated, thereby being higher in processing accuracy, large in size and large in number of gas throttling holes, and the rotor is large enough in size, so that compared with conventional spindles, the gas flotation spindle has higher radialbearing capacity and rigidity; the spiral Belleville springs are used to form a shaft core of the rotor, so that elasticity is more stable, service life is longer, convenience is brought to demountingand mounting, and the spindle is enabled to have higher stability and high adaptability and practicability.

The invention discloses a method for measuring unbalance amount of a rigid rotor by using static balance. The method comprises the steps of detecting an unbalanced direction of the rigid rotor on a statically-balanced rack, detecting a swinging period of the rigid rotor on the statically-balanced rack and determining the unbalance amount of the rigid rotor. A simple and reliable static balance measurement method for measuring the unbalance amount of the rigid rotor and evaluating the balance quality is provided. By the method, the unbalance amount and the unbalance direction of the rigid rotor can be determined effectively; the problem that the measurement on the unbalance amount of the rigid rotor by using the static balance measurement method cannot be evaluated quantitatively is solved, so the one-time correcting rate during the balance correction of the rigid rotor is more than 90 percent; the requirement on the balance correction of the rotor by using the static balance measurement method is to ensure the rest unbalance amount of the rotor is less than the available unbalance amount of the rotor rather than ensure the arbitrary balance of the whole balance system; and therefore, the time for the balance correction of the rotor is greatly shortened from two aspects and the efficiency and effectiveness of the balance correction of the rotor are improved.

The invention belongs to the technical field of rotor design, and provides a rigid rotor dynamic balance obtaining method. The method includes the following steps: (1) an entity model of a rotor part is divided into grids and decomposed into a limited number of unit entities, (2) quality characteristic data of each grid unit are extracted, (3) a dynamic unbalance value of a rotor is obtained, and (4) a dynamic balance result of the rigid rotor is obtained. The method effectively overcomes the defect that obtaining of rigid rotor dynamic balance is not accurate, dynamic balance obtained in the method plays a significant role in the rotor design, vibration of machines can be effectively reduced, so service life of the machines is prolonged, work efficiency is improved, and operation is safe.

The invention discloses a rigid rotor system for a helicopter. The rigid rotor system comprises a rigid rotor propeller hub, a rigid rotor pitch control mechanism and rigid rotor paddles, wherein the rigid rotor pitch control mechanism and the rigid rotor paddles are glued integrally and are connected with the rigid rotor propeller hub by virtue of bolts. According to the system disclosed by the invention, deep groove ball bearings and thrust bearings in the conventional teeterboard type propeller hub structure are replaced by joint bearings, so that a series of complex structures such as pitch change shafts, flapping hinges and vertical hinges are removed, and the problems such as complexity of the conventional teeterboard type propeller hub structure, heavy weight and short service life can be solved. Meanwhile, the problems that retreating paddleseasily enter an aerodynamic stalling state so as to reduce the aerodynamic efficiency due to swinging during high-speed forward flight and the like are solved, and the rigid rotor system has the advantages of simple structure, light weight, long service life, high maintainability and the like.

The invention relates to a dynamic balancing test device of a rigid double-disk rotor, which is characterized in that a bearing block is fixed on an elastic support; the lower end of a supporting arm is fixedly connected with the elastic support; a photoelectric displacement sensor is installed on the supporting arm and the elastic support, the bearing block, the supporting arm and the photoelectric displacement sensor combine an overall supporting block jointly; a rotating shaft is installed on the elastic support via the bearing block; one end of the rotating shaft is connected with a motor by a coupling; the motor is installed on a motor base; symmetrical left and right balancing disks are arranged on the rotating shaft; a transparent shield is capped outside the left and right balancing disks; the motor base, the transparent shield and the elastic support are bolted on a base; the lower end of the base is provided with a shock strut. The elastic support, the bearing block, the supporting arm and the photoelectric displacement sensor of the invention combine an overall supporting block jointly, thus shortening the distance between the photoelectric displacement sensor and the test point, contributing to good connection rigidity, reducing vibration disturbance and increasing measuring accuracy.

The invention relates to a rotary travelling wave ultrasonic motor adopting a brand new pre-pressure applying mode, which comprises a rigid rotor assembly. One side of the rigid rotor assembly is installed on a motor base through a bearing, and the other side of the rigid rotor assembly is sequentially provided with a stator assembly, a stator supporting frame and a pre-pressure shell; the rigid rotor assembly comprises a rigid rotor and a friction plate which are sequentially connected; the stator assembly comprises a stator, a piezoceramic plate and a flexible printed board which are sequentially connected; a waveform spring is further installed between the pre-pressure shell and the stator supporting frame; the rotary travelling wave ultrasonic motor adopting brand new pre-pressure applying mode has the advantages of a large hollow ratio, a high overload resistance, a good low-speed stability, a good low-temperature startability, etc., and the output performance consistency of the motor during the whole life is good; the application of the hollow ultrasonic motor in the large hollow ratio is expanded, such as used for a large hollow ratio optical lens to drive a lens and a waveplate.

An apparatus and method for feeding U.V.-curable inks without causing them to cure prematurely. The apparatus includes plural Moineau style pumps each with an elastomeric stator and a rigid rotor. The pumps are driven by electric motors and flexible drive shafts enabling the stator and rotor to be slight offset from one another. The ink is fed to all of the pumps at the same time from a single trough with baffles therein.

The invention discloses a wind power generation device capable of being regulated windward and a using method thereof. The wind power generation device comprises a ring-shaped base, wherein a rigid rotor, which can rotate relative to the ring-shaped base according to the wind direction and is arranged on the ring-shaped base in a radial direction, is arranged on the ring-shaped base; a blade type rotational transmission mechanism is arranged on the rigid rotor; the blade type rotational transmission mechanism comprises chain transmission mechanisms positioned at the two sides of the rigid rotor; blade mechanisms for bearing wind power are sequentially arranged between the chain transmission mechanisms; and the output ends of the chain transmission mechanisms are fixedly connected with power generators. According to the wind power generation device, the blade mechanisms are pushed by wind power to drive the chain transmission mechanisms to operate, so that the power generators generate power; the angle of the device is conveniently regulated through the rotational rigid rotor, so that the blade mechanisms and the wind direction are kept at the best stress angle, and therefore, the utilization rate of wind energy is increased; the blade mechanisms can open during windward rotation, and can be closed during headwind rotation, so that the best windward area is guaranteed, the transmission efficiency is improved, and the power generation efficiency is improved.