67 results about "Coaxial rotors" patented technology

A contra-rotating coaxial rotor assembly relating to aerial, as well as aquatic vehicles, comprising a central member, a first and second rotor assembly disposed thereon with a contra-rotating gear assembly coaxially disposed there between. The contra-rotating gear assembly comprising at least one gear operationally coupled to the first rotor assembly, at least one gear operationally coupled to the second rotor assembly, a collar having at least one protrusion, and at least one cogwheel affixed thereto. Each rotor assembly comprising a bearing, at least one length of mast, a rotor disposed along said length of mast, and a friction-reducer operationally engaged to the contra-rotating gear assembly. The second rotor assembly further comprising at least one power translation cogwheel operationally engaged with at least one power transmission cogwheel, which is itself connected to and driven by the output shaft from the engine.

A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

The invention discloses a coaxial rotor gun firework launching unmanned aerial vehicle system which comprises a missile-borne shell, an unmanned aerial vehicle and a foldable firework guiding launching system. The missile-borne shell mainly comprises a missile body, a missile tail and a hood; the projectile body and the projectile tail are connected through a fixing mechanism, a shell ejection mechanism is arranged in the fixing mechanism, and shell ejection and separation can be achieved when a separation signal is received. An integral structure formed by the unmanned aerial vehicle and the foldable firework guide launching system is placed in the bomb body in a folded state; the unmanned aerial vehicle is composed of a foldable nose and a fuselage. The foldable firework guiding launching system is composed of a guiding firework launching device and an airborne firework launching frame, the airborne firework launching frame comprises a firework launching tube and a foldable cross-shaped connecting rod, the firework launching tube is connected with the unmanned aerial vehicle through the foldable cross-shaped connecting rod, firework projectiles and propellant powder are contained in the firework launching tube, and the unmanned aerial vehicle carries the firework launching tube to the sky. Remote control is achieved, and fireworks are ignited and launched in an electric ignition mode.

The invention discloses an iterative algorithm and equipment for evaluating the aerodynamic performance of a coaxial rotor of an eVTOL aircraft, and belongs to the field of aircraft design, and can effectively improve the precision and stability of the aerodynamic performance evaluation of the coaxial rotor, the method comprises the following steps: mapping the aerodynamic performance and wake contraction of an upper rotor to a lower rotor, calculating the inflow ratio of the lower rotor, and calculating the aerodynamic performance of the lower rotor; the method comprises the steps that the aerodynamic performance of a lower rotor wing is mapped to an upper rotor wing, meanwhile, influence factors of the upper rotor wing and the lower rotor wing are introduced, the inflow ratio of the upper rotor wing is calculated, the process is conducted in a crossed iteration mode till the convergence standard is met, and the final aerodynamic performance of the coaxial rotor wings is obtained. Meanwhile, mutual interference of upper and lower rotors is considered through iterative calculation.

This patent discloses a powerplant for an aerial vehicle comprised of Perovskite-Silicon tandem photovoltaic solar cells covering the wings and fuselage, a lithium-sulfur battery, a high-pressure unitized regenerative proton exchange membrane (“PEM”) device, and hydrogen tanks. The PEM device has a fuel-cell mode and an electrolysis mode. During level flight, the PEM device operates in fuel-cell mode, converting hydrogen into electricity. The electricity is used to run a plurality of pairs of permanent magnet synchronous motors, coupled to propellers, and mounted in a coaxial rotor configuration. During level flight, the array of solar cells re-charges the Li—S battery pack. During takeoff and landing, the Li—S battery pack supplements the electricity generated by the PEM device in fuel-cell mode. On the ground, the solar cells provides electricity to the PEM device, which operates in electrolysis mode, converting water into hydrogen gas, which is then stored in the hydrogen tanks.

This invention discloses a coaxial rotor artillery-launched fireworks drone system, comprising an onboard shell, a drone, and a foldable fireworks guiding and launching system. The onboard shell mainly includes a projectile body, a tail, and a wind cap. The projectile body and tail are connected by a fixing mechanism, which includes a shell ejection mechanism that can eject and separate the shell upon receiving a separation signal. The drone and the foldable fireworks guiding and launching system are arranged in a folded state and placed inside the projectile body. The drone consists of a foldable nose and a fuselage. The foldable fireworks guiding and launching system consists of a guideable fireworks launching device and an airborne fireworks launching frame. The airborne fireworks launching frame includes a fireworks launching tube and a foldable cross connecting rod. The fireworks launching tube is connected to the drone through the foldable cross connecting rod and contains fireworks projectiles and propellant. The drone carries the fireworks into the air, which are remotely controlled and ignited and launched using electric ignition.

The invention discloses a fully-driven coaxial rotor UAV based on rudder surface control and a control method thereof. The UAV comprises a battery, a flight control system, an onboard computer and two coaxial power units, the two power units are respectively arranged at the upper part and the lower part of the UAV, each power unit comprises a motor, a rotor, two rudder surfaces and two steering gears, the battery is an energy source for the flight control system, the onboard computer and the power unit, the output end of the onboard computer is electrically connected to the input end of the flight control system, the output end of the flight control system is connected to the motor and the steering gear, the motor is connected to the rotor, the steering gear is connected to the rudder surface, and then the rotor and the rudder surface are driven to rotate; the rotor of the motor is used to provide translation and rotation of the UAV along the Z axis of the body, and the rudder surface is used to provide translation and rotation of the UAV along the X axis and Y axis of the body, thereby realizing full driving of the UAV.

The present invention discloses an iterative algorithm and device for evaluating the aerodynamic performance of the coaxial rotor of an eVTOL aircraft, which belongs to the field of aircraft design and can effectively improve the accuracy and stability of the aerodynamic performance evaluation of the coaxial rotor. The method is as follows: the aerodynamic performance and wake contraction of the upper rotor are mapped to the lower rotor, the inflow ratio of the lower rotor is calculated, and the aerodynamic performance of the lower rotor is mapped to the upper rotor. At the same time, the upper and lower rotor influencing factors are introduced to calculate the inflow ratio of the upper rotor. The above process is cross-iterated until the convergence standard is met to obtain the final aerodynamic performance of the coaxial rotor. The present invention can effectively consider the influence of the spacing between the upper and lower rotors, and at the same time consider the mutual interference of the upper and lower rotors through iterative calculation.

The application provides a four-rudder control coaxial rotor system, which comprises a rotor shaft, an upper rotor and a lower rotor installed on the rotor shaft, a gear box arranged on the rotor shaft, the gear box being located below the lower rotor, a first control mechanism for controlling the movement of the upper rotor to make the aircraft produce pitching movement and a second control mechanism for controlling the movement of the lower rotor to make the aircraft produce aileron movement, the first control mechanism being located between the gear box and the aircraft, the second control mechanism being located between the gear box and the lower rotor, and the first control mechanism comprising an upper tilt disc, a first rudder set and an upper variable-pitch pull rod. The application has the functions of using two sets of rudders to make the aircraft achieve elevator, forward flight and left-right steering, the rotor control functions are distinct and do not interfere with each other, the rotor control efficiency is improved, the structural complexity is reduced, the overall reliability of the device is improved, and the device is easy to maintain.

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.

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 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.

A coaxial rotor mechanism for a washing device relates to the technical field of coaxial rotor mechanisms for washing devices in the textile industry, and solves the technical deficiencies that the sprockets and chains of the coaxial rotor mechanisms of the existing washing devices are installed in the box of the washing devices, which are difficult to maintain and have poor reliability. The solution adopted is as follows: an inner sealing sleeve is sleeved on the driving shaft, and a first waterproof sealing ring and a first bearing mechanism are arranged between the driving shaft and the inner sealing sleeve; the inner sealing sleeve is tightly connected to the outer cylinder; a shaft sleeve is sleeved on the inner sealing sleeve, and a second waterproof sealing ring and a second bearing mechanism are arranged between the inner sealing sleeve and the shaft sleeve, and a synchronous pulley is arranged on the outer end of the shaft sleeve on the inner sealing sleeve, and the synchronous pulley is connected to the outer cylinder synchronous driving mechanism through a synchronous belt. The problem of difficulty in installation, debugging and maintenance of the existing built-in link structure of the box is effectively solved; the use of synchronous pulleys and synchronous belts at the same time can effectively improve the running speed of the washing device and achieve the result of improving production efficiency.

The invention relates to an electric coaxial rotor aircraft. The electric coaxial rotor aircraft is characterized by comprising two rigid structures which are connected through a hinge mechanism. Wherein the upper structure is provided with an outer rotor motor, two rotor wings, a set of reverse rotating device and an air guide plate; the lower structure bears a load cabin and / or a cockpit, a flight control system and an energy storage system.

A multi-rotor unmanned aerial vehicle comprises a fuselage and a plurality of rotor mechanisms arranged on the fuselage, and each rotor mechanism comprises a rotor and a connecting mechanism. Wherein the connecting mechanism comprises first rotating shafts, the multiple rotor mechanisms can rotate around the corresponding first rotating shafts according to a set sequence and are mutually overlapped to form a coaxial rotor mechanism assembly, and the axis of the coaxial rotor mechanism assembly is roughly perpendicular to the course axis of the multi-rotor unmanned aerial vehicle. According to the multi-rotor unmanned aerial vehicle, the folding of the multi-rotor unmanned aerial vehicle is realized, the multi-rotor unmanned aerial vehicle is convenient to carry, and the size of the folded multi-rotor unmanned aerial vehicle is greatly reduced due to the fact that the rotor mechanisms are mutually overlapped to form the rotor mechanism assembly.

The application discloses a kind of artillery launch coaxial rotor unmanned aerial vehicle airborne fireworks launching system, including artillery projectile platform, unmanned aerial vehicle and folding guided fireworks launching system;Folding guided fireworks launching system and unmanned aerial vehicle constitute integral system, folding is placed in shell cabin, and after being launched to a certain height in the air by air cannon, unmanned aerial vehicle and folding guided fireworks launching system are released by completing separation and dehulling, the launch timing and direction of fireworks are changed by remote control of remote control rudder, various different complex fireworks patterns are formed, and large-scale fireworks show performance is completed.Compared with traditional fireworks unmanned aerial vehicle, the application can better guarantee the flight stability of unmanned aerial vehicle during flight, and improve the safety of fireworks unmanned aerial vehicle performance.

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 invention relates to a coaxial rotor arrangement for an unmanned aerial vehicle (100) comprising: at least two rotor units (1), each comprising: at least one rotatable rotor blade mount (2) on which at least one rotor blade (3) is mounted; and wherein an angle of attack (4) of the rotor blade (3) relative to the rotor blade mount (2) is constant; and at least one, in particular electric, drive motor (5) for driving the at least one rotor blade (3); which can rotate about a pivot point (8); and wherein the pivot points (8) of the rotor units (2) are coaxial on an axis of symmetry (9); and wherein the rotor blades (3) of the rotor units (1) rotate in opposite directions; and at least one wobble mechanism (10) for tilting a rotor blade mount (2) of a rotor unit (1) relative to the axis of symmetry (11).At least one further wobble mechanism (12) is provided for the inclination of the rotor blade mounting (2) of the further rotor unit (2) relative to the axis of symmetry (11).

An aerial vehicle includes a wing body, a first wingtip, a second wingtip, a first edge, and a second edge. The aerial vehicle includes a pair of coaxial rotors configured to rotate in opposite rotational directions about a vehicle axis and a drive assembly configured to rotate the coaxial rotors. A controller is configured to selectively control thrust produced by the coaxial rotors. Selective control of the thrust produced by the coaxial rotors induces a pitch motion of the aerial vehicle to transition between a horizontal flight state and a vertical flight state. In the horizontal flight state, a collective thrust from the coaxial rotors is directed forward. In the vertical flight state, the collective thrust from the coaxial rotors is directed upward.

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 present application discloses a coaxial rotor cross-medium multi-aquatic unmanned system, which includes a main body cabin and a plurality of power units symmetrically arranged relative to the main body cabin; each power unit includes a variant mechanism and a coaxial rotor assembly installed on the variant mechanism. The variant mechanism includes a fixed bracket fixedly connected to the main body cabin, a rotating bracket rotatably connected to the fixed bracket. The rotating bracket is provided with a driving motor and a power rod connected to the output shaft of the driving motor; the coaxial rotor assembly includes a propeller coaxially installed on the outer side of the axial direction of the power rod and a rolling wheel on the inner side of the axial direction of the power rod; the driving mechanism drives the rotating bracket to rotate at different angles relative to the fixed bracket in the vertical plane through a push rod, so as to place the propeller and the rolling wheel at a plurality of working positions corresponding to a plurality of motion modes of the unmanned system respectively. The present application can cope with the natural environment with diverse terrains and has the characteristics of simple structure, convenient and fast switching.

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.

The invention discloses a magnetic suspension rotor device based on magnetic repulsive force stable lift force. The magnetic suspension aircraft driving system comprises a rotor wing stator assembly and a rotor wing rotor assembly which are coaxially arranged. The rotor wing rotor assembly comprises a radial rotor iron ring and an axial iron ring; the rotor stator assembly comprises an axial / radial bearing and a bearing magnetic ring; the paddle is connected with the rotor assembly through a paddle ring, and a force transmission magnetic ring is arranged at the bottom of the paddle ring; when the lift force of the blades is increased, the distance between the force transmission magnetic ring and the bearing magnetic ring is reduced, the magnetic repulsive force is enhanced, and the lift force is transmitted to the stator assembly; meanwhile, the axial electromagnet and the rotor iron ring form closed-loop control, and a constant suspension air gap is maintained. The problem of suspension instability caused by lift fluctuation in a traditional system is solved through non-contact magnetic force transmission, and the flight reliability is improved. The device is reasonable in design, simple in structure and high in practicability.

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.

Systems and methods for a drive system are disclosed. The drive system includes: a motor (120) operably coupled to an input shaft (115) at a first end, wherein the motor is configured to cause the input shaft to rotate in a first direction at a first angular velocity; a first output shaft (105) configured to rotate in the first direction at the first angular velocity; a second output shaft (110) configured to rotate in a second direction, opposite the first direction, at the first angular velocity; a cage component (150) housing the gear assembly, wherein rotation of the cage component is configured to cause the second output shaft to rotate at a second angular velocity, rotation of the second output shaft at the second angular velocity causing an adjustment in a blade-crossing azimuth at which the first set of propeller blades crosses the second set of propeller blades.

The invention relates to a method for monitoring the distance between coaxial rotor blades in real time in a complex environment based on an MB network. The method comprises the following steps: installing an industrial camera and carrying out machine vision calibration; acquiring a blade tip image; a Mobile-Blade network model is constructed, and model training and deployment are carried out; and positioning a propeller tip reference point and calculating the propeller spacing. The method can effectively solve the problems that in an existing method, the aerodynamic characteristic influence of the blades is large, the detection precision of the blade tip mark points is low, and the detection speed is low, real-time high-precision monitoring of the coaxial rotor blade distance can be achieved in the complex environment, and data support is provided for design and improvement of a novel coaxial helicopter.

The invention discloses a coaxial dual-rotor hovering aerodynamic characteristic analysis method based on an interference speed model, and belongs to the field of helicopter aerodynamics. According to the method, the velocity model of mutual interference of the upper and lower rotors is established, and the spanwise distribution of the interference velocity is solved by adopting an iterative process. Aiming at the interference of the upper rotor wing to the lower rotor wing, an improved Landgrebe slipstream model is adopted to calculate a non-uniform interference speed; and aiming at the interference of the lower rotor wing to the upper rotor wing, a McAlister slip flow model is adopted to calculate a uniform interference speed. According to the method, the slip flow radius and the rotor radius are compared, the interference range is judged, the non-uniformity of the interference speed is described through the piecewise function, the equal-radius and unequal-radius coaxial dual-rotor configuration can be processed at the same time, mutual aerodynamic interference between the upper rotor and the lower rotor is fully considered, and the method is suitable for large-scale popularization and application. The limitation of an existing theoretical analysis method on slip flow model and interference velocity calculation is overcome, and rapid and accurate analysis of coaxial dual-rotor hovering aerodynamic characteristics is achieved.

A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

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.