51 results about "Counter rotating" patented technology

The invention provides a flying wing layout multi-rotor vertical take-off and landing aircraft, and belongs to the technical field of aircrafts. The front coaxial reversal dual-rotor power system comprises a ducted upper rotor and a ducted lower rotor, the ducted upper rotor and the ducted lower rotor are coaxially arranged and are opposite in rotating direction, and the ducted upper rotor and the ducted lower rotor are arranged at the front part of the wing body fusion machine body; the rear thrust tiltable rotor wing system comprises a left rotor wing and a right rotor wing which are symmetrically arranged on the left side and the right side of the rear part of the wing body fusion machine body. The ducted upper rotor and the ducted lower rotor which are coaxially arranged and opposite in rotating direction are arranged, the upper rotor and the lower rotor rotate in opposite directions, reaction torques of the upper rotor and the lower rotor are counteracted, an additional anti-torque device is not needed, the structure is simplified, and the layout space of the front portion of the aircraft body is greatly saved.

Turbomachine (10) for an aircraft, said turbomachine (10) comprising a gas generator having at least one compressor (1a, 1b), a combustion chamber (1c) and at least one turbine (1d, 1e), said at least one turbine (1d, 1e) having a shaft (3) connected by a mechanical reduction gear (6) to a propulsion propeller (S), the shaft (3) being coupled to the solar element (11) by a reverse-rotating gearbox (20) with the same rotational speed such that a rotation of the shaft (3) about its axis (X) at a given speed causes a rotation in the opposite direction of the solar element (11) about the same axis (X) at the same speed. Figure for the abbreviation: Figure 3

Each turbomachine (1, 100) comprises an output shaft (3, 103), an input shaft (5, 105), and a reduction gear, one (104) of which is an epicyclic gear and the other (4) a planetary gear. Each reduction gear has a sun gear (15, 115), a ring gear (13, 113), a planet carrier (16, 116), bearings (22, 122) mounted on said planet carrier, and two-stage planets (14, 114) rotatably mounted on said bearings, with their first stage (18, 118) meshing with the sun gear and their second stage (19, 119) meshing with the ring gear. The planet carriers (16, 116) are identical. (See Figure 2 for abbreviations.)

To provide a hull direct connection type propulsion device for a reciprocal rotation propeller greatly improving propulsion efficiency of an electric propulsion vessel by being composed so that the reciprocal rotation propeller loaded on the electric propulsion vessel is directly coupled to a hull, and a manufacturing method of the same.SOLUTION: A hull direct coupling propulsion device includes: a relative rotation propeller composed of a front propeller and a rear propeller; a double rotor electric motor generating respective rotational directions in a front propeller and a rear propeller; and a double shaft coupling the relative rotation propeller and the double rotor electric motor.SELECTED DRAWING: Figure 1

The utility model relates to a kind of aircraft double-rotor structure, comprising: an aircraft body, with two shaft poles in front and back;Two groups of the rotor set of upper and lower settings are arranged on each shaft pole, and the rotor set comprises the rotor blade corresponding to each other and being arranged on the two sides of shaft pole, and two propulsion modules vertically opposite with two rotor blades respectively, the rotor blade of the rotor set of same shaft pole is misaligned and is set to same direction rotation, and the rotor blade on two different shaft poles is opposite reverse rotation;Propulsion module includes a track seat, a duct fan is installed in track seat, and one side of duct fan is equipped with a return spring, and a connecting piece is arranged between duct fan and shaft pole, and connecting piece can drive rotor blade to change angle.Therefore, the utility model directly drives rotor blade to generate ascending buoyancy using propulsion module, so as to drive aircraft body to ascend and descend;And flight is stable and comfortable, easy to control, structure is simple, reduce failure, and reduce production working hours and material cost, enhance flight safety.

The invention relates to a turbine engine (10) for an aircraft, this turbine engine (10) comprising a gas generator which has at least one compressor (1a, 1b), a combustion chamber (1c) and at least one turbine (1d, 1e), the at least one turbine (1d, 1e) having a shaft (3) connected to a propeller (S) via a mechanical reduction gear (6), the shaft (3) being coupled to the sun gear (11) via a gearbox (20) rotating in the opposite direction and at the same speed of rotation such that a rotation of the shaft (3) about its axis (X) at a given speed causes the sun gear (11) to rotate in the opposite direction about the same axis (X) at the same speed.

This invention discloses a top-opening aircraft overhead luggage lock and a top-opening aircraft overhead luggage compartment. The lock mainly consists of a rotary lock assembly and a latch. The rotary lock assembly includes a lock base, a first rotating shaft, a second rotating shaft, a first cam, a second cam, and a latch. The first and second rotating shafts are rotatably mounted on the lock base, with the first rotating shaft located below the second rotating shaft. The first cam is fixed to the outer surface of the first rotating shaft, and the second cam is fixed to the second rotating shaft. The first and second cams are offset and have openings at their opposite ends, allowing them to rotate in opposite directions through interlocking openings. The latch is located at the end of the second cam opposite to the first cam. The latch is located within the rotation area of ​​the latch. The first rotating shaft acts as a drive shaft, with the first cam driving the second cam to rotate in the opposite direction until the latch engages with the latch. This invention employs a concealed latch design, preventing interference with the protruding latch when passengers are placing luggage. The entire lock structure is simple and reliable.

The application discloses a flying car wing and rotor hybrid type folding and unfolding system and a flying car, which comprises a car body, two side wings, a wing rotating mechanism, a rotor support, a rotor support rotating mechanism and a rotor assembly; the wings are movably connected to the car body; the wings and the wing rotating mechanism are symmetrically arranged on the car body, and the wing rotating mechanism drives the wings to rotate and unfold to the two sides of the car body or reversely rotate and fold to the inner side of the car body, so that the wings do not exceed the wing edges, and the conversion between the automobile working state and the flying working state of the wings can be completed; the rotor support is movably connected to the wings, and the rotor support is rotated by starting the rotor support rotating mechanism, so that the rotation of the rotor support on the wing surface is realized. The flying car can realize super-short distance take-off and landing and stable flight in the air. In addition, when driving on the ground, the wings and the rotor can be folded and placed in the inner side of the car body, space is saved, the appearance is beautiful, and the ground automobile use requirements are met.

An aircraft includes a body defining an interior compartment configured to hold at least one of a passenger and a payload, a battery system, a plurality of arms coupled to and extending from the body, and a plurality of propulsion devices configured to provide thrust to fly the aircraft. Each of the plurality of propulsion devices is coupled to a respective one of the plurality of arms. The plurality of propulsion devices are powered by the battery system. Each of the plurality of propulsion devices is selectively pivotable about at least one axis. The plurality of propulsion devices include at least one of (i) counter rotating ducted fans and (ii) ionizing electrode engines.

HIGH-STABILITY, HIGH-AGILITY THREE-SAILING SURFACE AIRCRAFT The three-sail aircraft (1), (2), and (3) is equipped with movable flaps (6), (7), and (8) on each of the lifting surfaces. The flaps of the upstream lifting surface (6) are connected to the flaps of the main wing (7) by a rigid linkage with a deflection angle ratio of 50%. The forces on the downstream lifting surface (horizontal tail) (3) reverse between takeoff (negative lift) and cruise (positive lift). Stabilizing fins (5) are positioned at the rear of the fuselage in the lower section at an angle of 30° to the aircraft's centerline. A weighted control rod (22) located in the vertical tail (4) provides stabilization for the aircraft in the presence of severe turbulence.The propulsion system is located at the rear of the fuselage and consists of either a piston engine driving a multi-bladed propeller, one or two turboshaft engines driving a multi-bladed propeller or two contra-rotating propellers, a turbojet engine, or one or two electric motors driving a multi-bladed propeller or two contra-rotating propellers. This aircraft can be piloted either by a human pilot on board or by an electronic computer controlled from the ground or autonomously.

A vortex inducer is applied to the pressure face of a propulsion rotor blade. The vortex inducer defines an aft face located forward of the trailing edge of the blade. In operation, the vortex inducer generates a primary vortex behind its apex, which induces a counterrotating secondary vortex through viscous coupling at the trailing edge. The secondary vortex accelerates and deflects the suction face wake, enhancing overall blade performance. The system is applicable to propellers, helicopter rotors, prop-rotors, fan blades, and marine propellers.

The utility model provides a video acquisition device for determining the boundary of a river ecological corridor, which comprises a ship body with an opening at the top, an open chamber and a closed chamber are sequentially arranged in the ship body along the front-back direction, the top of the open chamber is provided with an overturning cover, and the overturning cover can rotate along the front-back direction relative to the closed chamber; the vertical propellers are arranged on the two sides of the ship body and can rotate forwards and backwards; the horizontal propeller is arranged at the bottom of the ship body and can rotate forwards and backwards; the lifting rod is arranged in the open cavity, and a camera is arranged at the top of the lifting rod and used for collecting live videos on the two banks of the river; a power supply module and a storage module for storing videos are arranged in the closed cavity; the power supply module is used for supplying power to the vertical propeller, the horizontal propeller and the lifting rod; and when the turnover cover covers the open chamber, the lifting rod is in a contraction state, and the lifting rod and the camera are located in the open chamber in the state that the turnover cover covers the open chamber. According to the acquisition device provided by the utility model, live video acquisition on both sides of a river can be realized.

The embodiment of the utility model discloses an underwater manpower propeller which comprises a power structure, a propeller body and a propeller body. The driving structure comprises a first impeller, a second impeller and a transmission structure, the first impeller and the second impeller are arranged at the same axial position, and the first impeller and the second impeller have opposite blade deviations; the power structure drives the first impeller and the second impeller to rotate in the opposite directions through the transmission structure, so that the first impeller and the second impeller generate thrust in the same direction. Compared with the prior art, manual driving is adopted, the problems of battery capacity, volume, charging and the like of an existing electric driving device do not need to be considered, the two impellers rotate in the opposite directions, the inclination angles of the blades on the two impellers are opposite, torque generated by rotation of the two impellers can be offset, and the service life of the impeller is prolonged. And the propeller is more stable during operation.

The application relates to the technical field of flying saucers, and provides a three-dimensional integrated magnetic fluid driving flying saucer flying device, which comprises a central stationary cabin section serving as an internal core support and carrying platform of the flying saucer, an upper power assembly arranged above the central stationary cabin section, the upper power assembly comprising an upper saucer shell, an upper disc ultra-thin motor and an upper disc screw type disc driven to rotate by the upper disc ultra-thin motor, and a lower power assembly arranged below the central stationary cabin section. The coaxial reverse rotation design of the upper and lower power assemblies effectively offsets the spin torque generated by the rotor, realizes the balance of the body yaw without a tail rotor, and ensures the stability and safety of the central stationary cabin section during flight. In combination with the spiral flow tidal inlet groove on the upper disc surface and the lower central exhaust outlet, the overall aerodynamic layout is optimized, and the vortex lift and vertical reverse thrust of the flying saucer are obviously improved.

A hybrid foldable system of wings and rotors of a flying vehicle, and a flying vehicle. The flying vehicle includes a vehicle body, two wings, wing rotating mechanisms, rotor supports, rotor support rotating mechanisms, and rotor assemblies. The wings are movably connected to the vehicle body and the wing rotating mechanisms drive the wings to rotate to expand or retract. The rotor assemblies expand to two sides of each wing, or reversely rotate to retract to inner sides of each wing. Vertical taking-off and landing and stable flight in the air of the flying vehicle can be realized. In addition, when running on the ground, the wing and the rotor assemblies can be rotationally folded and placed on the inner sides of the vehicle body, so that space is reduced, and the limit requirements of urban roads regarding the size of the vehicle are satisfied.

Proposed are a jet nozzle, and a combustor and a gas turbine including the jet nozzle. The jet nozzle is formed on an inner surface of a combustor to supply fluid into an interior of a liner of the combustor in a direction intersecting with a progress direction of combustion gases primarily combusted in a combustion chamber in the interior of the liner. The jet nozzle includes a body section provided with a fluid inlet on a first end, through which fluid is introduced, and a fluid outlet on a second end, through which the fluid introduced through the fluid inlet is discharged while generating a vortex, and a baffle section formed on an inner peripheral surface of the second end of the body section and configured to enhance the generation of a counter-rotary shear layer vortex in the fluid discharged out of the fluid outlet through the body section.

This application provides an automatic evaluation method for engine blade profile and torsion angle based on 3D point cloud, comprising: acquiring 3D point cloud data and a theoretical design model of the blade to be evaluated, the theoretical design model including an accumulation axis; planning multiple measurement sections on the theoretical design model along the accumulation axis direction, and extracting the section point cloud at each measurement section position from the 3D point cloud data; performing local registration of each section point cloud with the theoretical section profile of the corresponding measurement section to obtain the rotation amount of each section in its plane; establishing a torsion deviation curve based on the rotation amount of all sections, and performing a reverse rotation transformation on each point of the 3D point cloud data according to the torsion deviation curve; comparing the corrected 3D point cloud data with the theoretical design model to obtain the profile deviation; and simultaneously obtaining the torsion angle deviation according to the torsion deviation curve. The evaluation method provided by this application solves the problem of the coupling between profile and torsion angle, realizing the separate evaluation of the two parameters, and the results are accurate and reliable.

The utility model discloses a self-locking device of a folding arm of an aircraft and the aircraft. According to the self-locking device, a gear transmission mechanism is arranged to be in transmission connection with a folding arm, the gear transmission mechanism is provided with an unfolding locking hole and a folding locking hole, a locking structure comprises an electromagnet and a ferromagnetic locking pin capable of being attracted by the electromagnet to move back and forth, and the output end of a driving motor is in transmission connection with the gear transmission mechanism. The power of the driving motor can be transmitted to the folding arm through the gear transmission mechanism, so that the folding arm is driven to rotate, the locking pin made of the ferromagnetic material is controlled to be inserted into the unfolding locking hole to be locked when the folding arm rotates to the position of the unfolding locking hole in the first direction by arranging an electromagnet to be powered on and powered off, and otherwise, the locking pin is inserted into the unfolding locking hole to be locked. When the folding arm reversely rotates to the position of the folding locking hole in the first direction, the folding arm is inserted into the folding locking hole to be unlocked, automatic locking and unlocking are achieved, manual intervention is not needed, operation is easy and convenient, the error probability is reduced, reliability is improved, and safety accidents are avoided.

An aerostat tether, anchorage, and tether spool system which extends the “On Station” uninterrupted intervals of service for which a “Lighter Than Air” (LTA) aerostat may stay aloft at its designated altitude without requiring retrieval for ground service. Anchoring vessels are provided at both the aerostat and ground control ends of the tethered system which enables remote control of varying choices for bi-directional gas flow patterns within the tether which better facilitate continuous lift gas maintenance and emergency control. The gas routing is selectively controlled per best practice toward the constant filtering and scrubbing of the lift gas within both the aerostat and the tether restraining the aerostat. The system uniquely provides for a very rapid switch-out of tethers by having a full “replacement tether spool” on the ground at the ready which is pre-wound, pre-filled, and sealed with fresh lift gas where it is available at all times for rapid changeout. Quick tether replacement is accomplished by interchangeable quick disconnect fittings at both ends of a hollow tether with a hollow piston valve stem to provide a simple process of unplugging the tether at both the aerostat to close the valves and ground terminal ends and then plugging in the replacement tether to open the valves and reinstituting deployment facilitated by the unique tether spool and anchoring system. The system also enables the effective prevention and dissipation of damage due to torque forces being applied to the tether by a weathervaning aerostat. This is accomplished through counter rotation being applied to the tether at the most advantageous and effective source of tether / aerostat union, at its point of attachment at the aerostat end since the tether attachment point (TAP) is where damage to the tether is most likely to occur. Also favorable to the longevity of service, the aerostat system provides improvements of electrical strike / static build-up dissipation as well as superior tether terminal end preparation, interconnection speed, and short turnaround repair times. The entire aerostat system is designed for plug and play usage and versatility.

The present invention is directed to axial-centrifugal contra-rotating compressor system comprising combination of contra-rotating axial compressor stage with a back end centrifugal compressor stage, eliminating stator blades, an inter-stage connecting duct at the entry of the centrifugal compressor and an discharge diffuser at the exit of centrifugal compressor rotor characterized by radial to axial turning annular passage as per the gas turbine engine requirement, favouring reduction in engine size, weight, number of parts, overall engine length and produces a higher-pressure rise and swirl-free discharge towards the combustion chamber. The first low-pressure rotor having at least one axial blading assembly rotates in the direction opposite to the second high-pressure rotor blading assembly comprising of at least one axial rotor and one centrifugal rotor. The blades for axial compressor are adopted of low-aspect ratio configuration for reliable high load stall free operation. The inter-stage connecting duct minimizes total pressure loss. The discharge diffuser recovers higher exit velocity and hence higher kinetic energy.

The application discloses a propeller hub cap fin energy test mechanism and relates to the technical field of propeller test.The test mechanism comprises a frame, a moving device installed on the frame, a fixing frame installed on the moving end of the moving device and a moving frame in sliding connection with the inside of the fixing frame.The application is provided with a counter-torque assembly, which generates centrifugal counter torque by reverse rotation of a transmission cylinder and a connecting shaft, and a torsion sensor installed between the fixing frame and the moving frame detects residual circumferential force in real time, changes the radial working radius of a weight block, dynamically tunes the amplitude of the counter torque, ensures that the counter torque generated by the propeller is counteracted before being transmitted to the moving frame, enables the thrust sensor to bear axial hydrodynamic thrust, reduces the eccentric load error caused by torsion coupling and significantly improves the measurement accuracy of the small energy saving gain of the hub cap fin.

A vertical take-off and landing aircraft of the tail-sitting type comprises a cockpit integrated into a body having delta wings in the rear section with respect to the cockpit and a propulsion system placed in the front section with respect to the cockpit. The propulsion system includes at least two coaxial counter-rotating propellers put into rotation by at least two electric engines powered by rechargeable batteries.

A watercraft operating system includes a marine propulsion device and a watercraft operating controller. In a compass direction keeping control to keep a watercraft oriented in a target compass direction, the watercraft operating controller is configured or programmed to turn a propeller between a first steering position and a second steering position at a predetermined time interval. The first steering position is where the thrust is applied to the watercraft in a back-and-forth direction and a right-and-left direction. The second steering position is obtained by reversing the first steering position in either the back-and-forth direction or the right-and-left direction. The watercraft operating controller is configured or programmed to control the magnitude of the thrust and a rotational direction of the propeller such that the watercraft performs bow turning toward the target compass direction when the propeller is located in each of the first and second steering positions.

A revolving cathode tool and method for co-rotating electrochemical machining of an inner wall of an aero-engine casing are provided, and relates to the technical field of electrochemical machining. The co-rotating electrochemical machining revolving cathode tool comprises a power supply, a cathode shaft, an anode workpiece and a flexible cathode assembly. The cathode shaft is electrically connected with a cathode of the power supply. The anode workpiece is electrically connected with an anode of the power supply. One end of the cathode shaft is connected with the flexible cathode assembly. The problem that a non-array complex structure of the inner wall of the aero-engine casing cannot be machined through counter-rotating electrochemical machining is fundamentally solved. The diameter of the cathode tool is 1 / n of the diameter of the anode workpiece.

The application discloses a modular reconfigurable and self-adaptive control tunnel unmanned plane and belongs to the field of unmanned planes. Specifically, the application comprises a minimum module unit of a single-rotor attached to a slipstream rudder, wherein the minimum module unit comprises a fuselage, a power assembly, a control assembly, a connecting assembly and a take-off and landing assembly; two module units are spliced into a minimum flight unit through connecting rods; a plurality of flight units can be connected in a head-to-tail mode or a side-by-side mode; the self-rotation torque is offset through the reverse rotation of the rotors on the two sides of the connecting rods; the pitch of the flight unit is controlled through the differential speed of the rotors; and the lateral change of the flight unit is controlled by the slipstream rudder surface. The application can assemble, disassemble and scale the aircraft according to the weight and size requirements of the load, and has the ability to complete the reconnaissance and transportation through small windows and long and narrow tunnels.

This invention discloses an active stability control system and method for aircraft based on multi-layer rotating magnetic field coupling with airborne eddy current damping. The system employs at least two sets of counter-rotating magnetic field generating units to construct a three-dimensional alternating rotating magnetic field inside and outside the aircraft. This magnetic field, inducing eddy current damping force and attitude recovery torque, interacts with airborne metal damping components fixedly mounted on the aircraft body. Basic attitude disturbance rejection is provided by utilizing the gyro's axis-fixed property, and counter-rotating angular momentum is used to cancel out anti-torque. Precise attitude and position control is achieved by dynamically adjusting the rotational speed and phase difference of the magnetic field units. This invention decouples propulsion and attitude stabilization functions, enabling the aircraft to achieve long-term hovering in all scenarios and strong wind resistance even at low or zero propulsion power, making it suitable for various low-altitude and high-altitude aircraft.

Turbomachine (10) for an aircraft, said turbomachine (10) comprising a gas generator having at least one compressor (1a, 1b), a combustion chamber (1c) and at least one turbine (1d, 1e), said at least one turbine (1d, 1e) having a shaft (3) connected by a mechanical reduction gear (6) to a propulsion propeller (S), the shaft (3) being coupled to the solar element (11) by a reverse-rotating gearbox (20) with the same rotational speed such that a rotation of the shaft (3) about its axis (X) at a given speed causes a rotation in the opposite direction of the solar element (11) about the same axis (X) at the same speed. Figure for the abbreviation: Figure 3

The present application relates to the technical field of bird's nest impurity separation, and in particular to a bird's nest impurity separation device and method, which comprises a base cylinder, a turbulence propeller, a microporous aeration disc and a filter located above the water surface. A transmission mechanism drives the turbulence propeller and the filter to rotate in opposite directions synchronously. The filter is installed in a fixed-axle rotating manner by an outer ring body. A speed regulation assembly drives a screw by a stepping motor, changes the contact position of the homopolar wheel and the ladder-shaped wheel column, and realizes stepless adjustment of the rotation speed ratio of the filter and the turbulence propeller. The separation method comprises the steps of feeding and water injection, parameter setting, reverse synchronous rotation impurity removal and post-treatment after discharging. The present application realizes active sweeping and capturing of floating impurities by using the relative motion generated by reverse rotation, and effectively solves the problems of low impurity collection efficiency and easy mechanical damage to the bird's nest in the prior art by combining the gentle flow generated by the microporous aeration and the anchor-type turbulence propeller. The working conditions can be flexibly adjusted according to the grade of the bird's nest, and the impurity removal efficiency and the integrity of the bird's nest are taken into account.