18 results about "Coaxial rotors" patented technology

The application discloses a kind of based on interference speed model's coaxial dual-rotor hover aerodynamic characteristic analysis method, belong to helicopter aerodynamics field.The application is by establishing the speed model of mutual interference of upper and lower rotors, the iteration procedure is used to solve the spanwise distribution of interference speed.For the interference of upper rotor to lower rotor, the non-uniform interference speed is calculated using improved Landgrebe slipstream model;For the interference of lower rotor to upper rotor, the uniform interference speed is calculated using McAlister slipstream model.The application is by comparing slipstream radius and rotor radius, determines interference range, and utilizes piecewise function to describe the non-uniformity of interference speed, can simultaneously process equal radius and unequal radius coaxial dual-rotor configuration, fully considers the mutual aerodynamic interference between upper and lower rotors, overcomes the limitations of existing theoretical analysis method in slipstream model and interference speed calculation, realizes the fast, accurate analysis of coaxial dual-rotor hover aerodynamic characteristics.

The present application belongs to the technical field of electromagnetic signal interference troubleshooting, and particularly relates to a coaxial rotor electromagnetic signal interference troubleshooting system and method with a foldable launching cylinder. The electromagnetic signal interference troubleshooting system adopts a coaxial rotor unmanned aerial vehicle carrying a foldable direction-finding antenna array. The aerial part is foldable as a whole and can be accommodated in a launching cylinder after folding. The system can be launched by the launching cylinder, facilitating portability and rapid deployment, and meeting the application requirements of special occasions such as in-vehicle launching or airborne dropping. The coaxial rotor unmanned aerial vehicle carries a multi-antenna monitoring and direction-finding load. The coaxial rotor unmanned aerial vehicle flies in a tilted rotor disc mode. Compared with a multi-rotor unmanned aerial vehicle, the attitude changes little during flight, and the influence on the antenna array attitude is small. The unmanned aerial vehicle can continuously direction-find electromagnetic targets during flight. The system is provided with an antenna control mechanism, which can adaptively adjust the antenna array spacing in the air according to the required frequency range, expand the direction-finding frequency range of the system, avoid ambiguity, and improve the working efficiency of the system.

The present application relates to an operating device for operating an impeller (1) of a pump (10) for recirculating a coolant fluid of a vehicle, comprising: a driven shaft (2) arranged to support and rotate the impeller (1) of the pump (10); a fixed pump body (11); a motion receiving element (31a) for receiving a rotational motion; an electromagnetic clutch comprising an electromagnet (22) and an armature (40) rotating integrally with the driven shaft (2) and axially movable with respect to said shaft, these devices cooperating to drive the driven shaft at a first rotational speed, so as to transmit the rotational motion taken from the motion receiving element (31a); an eddy current or Foucault coupling arranged to transmit to the shaft (2) a rotational motion proportional and reduced with respect to the rotational motion of the motion receiving element (31a). The motion receiving element is formed on a coaxial rotor (30) having a front friction surface (32a) arranged between the electromagnet (22) and the armature (40); the pump body (11) is rigidly connected to an intermediate bearing (20b) of a multi-stage bearing unit (20) which further comprises: an inner race (20a) to which the driven shaft is keyed; and an outer race (20c) on which the coaxial rotor is supported. The driving portion of the Foucault coupling rotates integrally with the rotor, the driven portion (61) rotating integrally with the shaft (2).

The application discloses a coaxial rotor linear variable-pitch motor servo system and a low-altitude aircraft, relates to the field of servo motor driving, and aims to solve the problem of low power density and torque density of a driving motor in the existing low-altitude aircraft servo system. The motor servo system comprises a double-rotor driving unit, which has the functions of a rotor and variable pitch at the same time, and improves the power density and torque density; a linear variable-pitch transmission unit, which adopts a reverse planetary roller screw assembly to realize efficient linear variable-pitch movement and has self-locking performance; and a closed circulation heat dissipation unit, which contacts the motor and the transmission unit through internal circulation lubricating oil to improve the heat dissipation efficiency. The application can be used for the servo system of a low-altitude aircraft.

The invention discloses a coaxial rotor linear variable pitch motor servo system and a low-altitude aircraft, relates to the field of servo motor driving, and aims to solve the problems of low power density and low torque density of a driving motor in an existing low-altitude aircraft servo system. The motor servo system of the present invention comprises: a dual-rotor driving unit which has rotor and variable pitch functions at the same time and improves power density and torque density; the linear variable-pitch transmission unit adopts a reverse planetary roller screw assembly to realize efficient linear variable-pitch movement and has self-locking performance; the closed circulation heat dissipation unit makes contact with the motor and the transmission unit through internal circulation lubricating oil, and the heat dissipation efficiency is improved. The method can be used for a servo system of a low-altitude aircraft.

The application provides a water pipeline power generation device with flow and voltage adjusting functions, which comprises a tubular generator shell, a stator assembly in the generator shell, and a coaxial rotor assembly. The stator assembly comprises fixed coil windings uniformly distributed on the outer circumferential surface of the rotor assembly and adjustable coil windings which can move axially along the rotor assembly and adjust the axial position to change the magnetic flux. The rotor assembly comprises a tubular rotor shell for accommodating water flow. The inner circumferential surface of the rotor shell is provided with a plurality of groups of rotor blades distributed in a spiral shape. The outer circumferential surface of the rotor shell is provided with a permanent magnet group which is inductive cooperation with the fixed coil windings and the adjustable coil windings. The rotor assembly rotates coaxially relative to the stator assembly to generate power under the pushing action of the water flow on the rotor blades. The traditional water power design is improved. The tubular design can be directly connected to the water pipeline, thereby reducing the higher requirements of traditional open generator sets for water flow and stability. Moreover, the structure can convert the potential energy of the water flow, thereby achieving the flow and voltage adjusting effects.

A coaxial rotor pair assembly, e.g., for a flight vehicle or drone, with a fixed-pitch rotor and a variable-pitch rotor that are axially spaced relative to one another on a rotor axis for rotation via rotor shafts. A first motor and a second motor are provided for the rotors to drive the respective rotor about the rotor axis. The first and second motors are each controlled by a speed controller, and speed controllers are controlled by a vehicle flight controller. A collective pitch of the plurality of blades of the variable-pitch rotor is configured to be selectively varied by the vehicle flight controller during rotation of both the fixed-pitch rotor and the variable-pitch rotor about the rotor axis. The plurality of blades of the fixed-pitch rotor are maintained a constant, fixed pitch, e.g., during operation of the flight vehicle.

An ultra-high-speed helicopter with stowed single-blade coaxial rotors is provided and relates to the technical field of aircrafts. The ultra-high-speed helicopter includes a fuselage. Wings and tails can be arranged on the fuselage, respectively. Tail blades can be arranged at a tail end of the fuselage. A rotor mechanism can be arranged on a top of the fuselage. The rotor mechanism includes rotors. The rotor mechanism can drive the rotors to be stored in a rotor storage cabin of the fuselage. When the helicopter flies at high speed, the rotors stop working, and tail blades provide propulsive force and the wings provide lift force, so that the defects in the aerodynamic characteristics of the rotors are avoided during high-speed flight. In addition, the rotors can be retracted and stowed in a fuselage to further reduce drag and increase the maximum flight speed.

The application discloses a three-axis symmetrical multi-rotor frame. The three-axis symmetrical multi-rotor frame comprises a fuselage, a control module and a battery are arranged on the fuselage, a landing gear is arranged below the fuselage, a rotor arm is arranged on a side wall of the fuselage, a power system is fixed to an outer end of the rotor arm, and the battery is electrically connected with the power system. The application adopts a symmetrical design mode of upper and lower layers of a three-axis machine type, and provides power for six rotors through two independent motors respectively, so that the purpose that the non-coaxial rotors can still stably fly when damaged is achieved, technical effects of power redundancy and safety are realized, and the technical problem of unmanned aerial vehicle falling and being damaged due to rotor damage is solved.

The invention relates to a rotary machine comprising coaxial rotor (20) and stator (30), the rotor (20) being free to rotate about an axis of rotation X, the machine comprising a bearing (10) for guiding the rotation of the rotor (20), the bearing (10) being in contact with a surface (200) of the rotor (20), the bearing (10) comprising a roller bearing arrangement (100) around the rotor (20) and a detection arrangement (110), the detection arrangement (110) comprising a first element (110 ') and a second element (110' '), the first element (110 ') extends around the rotor (20) and the second element (110' ') is rigidly connected to the stator (30), the detection device (110) being configured to switch from a stationary configuration in which the first element (110') is remote from the rotor (20) and the second element (110 '') to a braking configuration in which the first element (110 ') is rotated by the rotor (20) and in which the second element (110' ') exerts a force on the first element (110') opposite to the rotation, the detection device (110) is configured to switch from the stationary configuration to the braking configuration when the rotation of the rotor (20) is eccentric with respect to the rotation axis X.

This invention relates to the field of unmanned aerial vehicle (UAV) control technology and discloses a method for dynamic trajectory control of aerial fireworks based on a cannon-launched coaxial rotor UAV. The system includes: collecting flight and environmental parameters from UAV launch to fireworks ignition; analyzing trajectory deviation characterization values ​​and comparing them with a preset trajectory deviation characterization threshold to determine the UAV's flight status; if the flight trajectory meets the standards, collecting the trajectory and firing parameters after fireworks ignition; analyzing the UAV trajectory dynamic adaptation characterization values; comparing the differences to determine adaptability; if unqualified, formulating a UAV flight adjustment strategy; and further correcting the preset trajectory deviation characterization threshold based on the flight adjustment strategy. This invention achieves precise adaptation between the UAV trajectory and fireworks firing by collecting parameters in stages, quantitatively analyzing characterization values, dynamically comparing thresholds, and optimizing adjustments. This improves flight stability, the visual appeal and safety of fireworks displays, adapts to different scenario requirements, and facilitates engineering applications.

The invention discloses a hollow dual-mode motor, which is made of carbon fibers and is formed by 3D printing in an imaging process. According to the functional condition, two coaxial rotors are used for determining maneuvering control and guidance. The weight is overcome by the peripheral pole lift force, and the motor is started to have the life rate.

Drone (100) for explosive gas atmospheres, comprising propulsion means (110) comprising propellers (110a) connected to coaxial rotors (110b), and a pressurized enclosure (120) connected to the propulsion means (110) and comprising polymeric material with conductive fillers, wherein the pressurized enclosure (120) comprises a first cover (130), a central ring (140) and a second cover (150), wherein a first space (A) defined between the first cover (130) and the central ring (140) houses the drone control unit (100) for controlling at least the propulsion means, wherein a second space (B) defined in the central ring (140) houses the power electronics for powering the propulsion means, and wherein a third space (C) defined between the second cover (150) and the central ring (140) houses one or more control and data acquisition sensors.

The invention discloses a data resolving method suitable for a rotor wing rotating balance, which belongs to the technical field of aviation aerodynamic force wind tunnel tests, and comprises the following steps of: statically calibrating the balance, acquiring an initial trigger phase through an azimuth angle encoder, calculating a load according to a balance formula and correcting according to a calibration shaft system; and calculating a phase angle corresponding to an acquisition point by combining an initial trigger phase and the number of acquisition points in each circle, converting a rotating coordinate load into a fixed coordinate load through rotating coordinate conversion, obtaining a fixed coordinate system load of a propeller hub through two-center distance conversion, and finally obtaining a rotor average load and a data spectrogram through filtering and Fourier transform. According to the invention, a novel coaxial rotor platform rotating balance data resolving method is constructed, triggering and acquisition phases are determined by means of a high-resolution azimuth angle encoder, high-resolution acquisition and conversion of the load are realized in combination with rotating coordinate conversion, and the accuracy of test data is effectively improved.

The application discloses a data solving method suitable for a rotor rotating balance, and belongs to the technical field of aviation aerodynamic wind tunnel test, and comprises the following steps: balance static calibration, obtaining an initial trigger phase through an azimuth angle encoder, calculating a load according to a balance formula and correcting according to a calibration shaft system, combining the initial trigger phase with the number of collection points per circle to calculate a corresponding phase angle of the collection points, converting the rotating coordinate load into a fixed coordinate load through rotating coordinate conversion, obtaining a hub fixed coordinate system load through two-center distance conversion, and finally filtering and Fourier transforming to obtain a rotor average load and a data spectrum diagram. The application constructs a novel coaxial rotor platform rotating balance data solving method, determines a trigger and a collection phase by relying on a high-resolution azimuth angle encoder, realizes high-resolution collection and conversion of the load by combining the rotating coordinate conversion, and effectively improves the accuracy of test data.

The present application relates to experimental device technical field, aims at solving the problem that the existing technology cannot test the lift, torque and hinge moment of coaxial rotor aircraft in different motion states, and provides a kind of rotor unmanned aerial vehicle motion characteristic testing device under multiple working conditions, including test connecting disc;Test connecting disc shaft center is detachably connected with the action control system of coaxial rotor unmanned aerial vehicle;The action control system of coaxial rotor unmanned aerial vehicle has main shaft, and main shaft is sequentially sleeved with rotor drive motor, rotor system, cross operating disc system and steering machine from top to bottom, one side of cross operating disc system is connected with rotor system, the other side of cross operating disc system is connected with steering machine, and steering machine is connected with steering machine support seat, and steering machine is fixed on main shaft through steering machine support seat, and one end of main shaft is detachably fixedly connected on test connecting disc.The beneficial effects of the present application are that the lift, torque and hinge moment of coaxial rotor unmanned aerial vehicle in different motion states can be tested.

The invention discloses an efficient feeding device of an automatic rotor paint dipping machine. The efficient feeding device comprises a rotor guiding and discharging mechanism and a rotor assembling sleeve at a to-be-fed part. According to the invention, the two rotor guiding and discharging mechanisms which are parallel to each other and have the same inclination degree are adopted, so that an assembling and feeding structure can be formed, and corresponding end parts of the rotor guiding and discharging mechanisms which are pushed and pulled to move can be combined to enter and exit between two opposite rotor assembling sleeves on an automatic paint dipping conveying chain; rotor sets can be orderly and automatically rolled to the rotor push-out grooves by means of the inclination degree, rotors to be fed can be placed right in front of the openings of the coaxial rotor assembly sleeves, the problem of frequent and repeated operation of manually taking and assembling the rotors is solved, every two rotors are used as a pair to be pushed and assembled on the corresponding rotor assembly sleeves at the same time, and the rotor assembly efficiency is improved. The feeding device is simple in structure, high in feeding speed and high in efficiency and is matched with a rotor mounting structure on an existing automatic rotor paint dipping machine to the maximum extent, and the automation level of the automatic rotor paint dipping machine is further improved.

The invention discloses a single-seat electric vertical take-off and landing aircraft, which relates to the technical field of flight and comprises an aircraft body, a rotor wing structure and a duct structure. The rotor wing structure comprises two first rotor wings, two second rotor wings and two third rotor wings. The duct structure comprises a first duct and a second duct, and the thrust directions of the first duct and the second duct are opposite. According to the scheme, the first rotor wing, the second rotor wing and the third rotor wing are deployed in a non-coaxial distributed mode, the problem of aerodynamic interference existing between coaxial rotor wings can be avoided, reduction of extra power loss is facilitated, meanwhile, through cooperation of the first duct and the second duct on the same side, when a single rotor wing or duct fails, the first duct and the second duct on the same side are matched, and the rotor wing or the third rotor wing cannot be damaged. The thrust compensation of the duct on the other side is used for quickly complementing part of lift gaps, stable yaw control torque can be output through the accurate matching of reverse thrust, and the flight stability and safety of the aircraft in a single-shot failure scene are effectively improved.