38 results about "Counter rotating" patented technology

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.)

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 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.

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.

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 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.

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.

According to the invention, each turbomachine (1, 100) comprises an output shaft (3, 103), an input shaft (5, 105) and a reduction gear set, one (104) of said reduction gear sets being an epicyclic gear set and the other (4) being a planetary gear set, each reduction gear set having a sun gear (15, 115), a ring gear (13, 113), a planet carrier (16, 116), bearings (22, 122) mounted on the planet carrier, and two-stage planet gears (14, 114) rotatably mounted on the bearings, wherein the first stage (18, 118) of the planet gears meshes with the sun gear and the second stage (19, 119) of the planet gears meshes with the ring gear, the planet carriers (16, 116) being identical.

The present invention relates to a dual-rotating high-torque motor comprising a rotor and a stator, and allowing the stator to freely rotate without fixing same to a support frame, such that an inner rotor corresponding to the rotor and an outer rotor corresponding to the stator respectively rotate in opposite directions, or each of the inner rotor corresponding to the rotor and the outer rotor corresponding to the other rotor on the outer surface of the stator generates rotational force. According the present invention, torque generated in opposite directions by the inner rotor and the outer rotor is used such that lightweight and high-efficiency characteristics can be achieved and a propeller capable of high-torque and low-speed rotation can be designed and manufactured, thereby reducing power consumption for generating the same thrust, directly driving the propellers attached to the inner rotor and the outer rotor, and maximizing cooling efficiency and obtaining high continuous thrust by means of a cooling device provided in the propeller.

The method of obtaining both, lifting force and thrust, required for horizontal flight of the vertical take-off and landing flying machine while maintaining horizontal flight stability of the machine which is realized due to suction atmospheric air to the inner cavity formed between coaxial mounted, multi-blade turbines (2, 18), the top and the bottom, which are counter-rotating relatively to each other, and remove the air outside under the machine; the conical turbines are mounted with the direction of wider, circular bases facing in front of them and which are mounted on the double-sided fixed bearings (4, 16) alongside the contour edge of the external ring (12), which is mounted using the distance spacers (13) form the inner side to the central housing (6) which is formed with the conical shape and which is the base where the both turbines (2, 18) are mounted using linear drives from the side of their smaller bases. The air which is accumulated under the pressure at such inner cavity is removed outside of the external ring (12) using drive nozzles (15A, 15B, 15C, 15D), which are installed circumferentially at the inner ring, to achieve thrust required for the horizontal flight or stabilization nozzles (14A, 14B), which are used to maintain required rotational stabilization of the central ring (6). The subject of the invention is also the machine used to achieve this way.

The utility model relates to the field of aircraft technology discloses a kind of wing-body fusion aircraft, including wing-body fusion body of fuselage and wing fusion, multiple rotor propellers and propelling propeller, the end of wing is provided with winglet, the tail of wing-body fusion body is equipped with flat tail on both sides, tail top middle is equipped with vertical tail;Multiple rotor propellers include two front rotor propellers embedded in two mounting holes of wing and two rear rotor propellers symmetrically arranged at the front end of flat tail, two rear rotor propeller outer is equipped with surrounding baffle ring;Propelling propeller includes two propeller blades coaxially arranged in front and back and motor for driving two propeller blades to rotate respectively, and the rotating direction of two propeller blades is opposite to offset counter torque.The utility model uses wing-body fusion body, rotor propeller, the aerodynamic layout of double-shaft common propeller reverse-rotation type propelling propeller, reduces air resistance, improves aerodynamic efficiency, improves flight stability.

The invention relates to a symmetrical reverse rotation double-rotor shaftless propeller which comprises a body, hydrofoils, an energy storage part, a propelling part and a grabbing part. A motor is installed on the inner side of the motor shell, the output end penetrates through the mechanical sealing mechanism to be connected with a first straight gear, a second gear is in meshing transmission with the outer side of the first gear, and a gear is arranged on one side of the second gear. A first rotating ring and a second rotating ring are rotationally arranged on the inner side of the first shell and the inner side of the second shell, a motor drives the two rotating rings provided with gear rings to rotate reversely through a gear set, aquatic sundries cannot be wound, the double rotating rings are symmetrically arranged to generate balance thrust, single-shaft torque is offset, operation is stable, and vibration and energy loss are reduced. The left outer tooth impeller and the right outer tooth impeller are symmetrically arranged, the angles and the rotation directions of the impellers are opposite, thrust is the same, an exposed shaft system is eliminated, sundries such as aquatic plants and fishing nets cannot be wound, balance thrust is generated, single-shaft torque is effectively offset, control is easy, and vibration and energy loss are reduced. Meanwhile, the propeller can be provided with hydrofoils, so that people can stand on the hydrofoils to run.

The invention relates to the field of aeronautical manufacturing, and discloses a tandem type unmanned helicopter which comprises an unmanned helicopter shell, a camera is fixedly connected to the bottom end of the unmanned helicopter shell, and an unmanned helicopter support is arranged on the inner wall of the unmanned helicopter shell. The bottom end of the unmanned helicopter support is fixedly connected with an unmanned helicopter undercarriage. By adopting the double-main-rotor structure which is arranged in the front-back longitudinal row and rotates reversely, the front rotor and the rear rotor counteract reaction torque in the flight process, stable flight can be achieved without arranging a tail rotor, potential safety hazards caused by high-speed rotation of the tail rotor are effectively eliminated, extra consumption of the tail rotor to engine power is avoided, and the service life of the tail rotor is prolonged. The hovering efficiency and the effective load capacity of the whole aircraft are improved, the aircraft body is longitudinally supported through the front rotor wing and the rear rotor wing, the application range of the load gravity center is expanded, the flight attitude stability and the task adaptability are enhanced, and the aircraft is suitable for safe and efficient operation under the working conditions such as the large-load and low-altitude complex environment and the plateau.

This invention relates to the field of electric vertical takeoff and landing (EVTOL) aircraft propulsion, specifically a distributed array of vortex-enhanced ducted fans based on lip rotation. The array includes a support structure and at least three vortex-enhanced ducted fans mounted on the support structure. Each vortex-enhanced ducted fan aerodynamic structure comprises an integrally rotating ducted fan shell and blades. One vortex-enhanced ducted fan aerodynamic structure is located at the center, while the remaining vortex-enhanced ducted fan aerodynamic structures are arranged equidistantly around the periphery. All peripheral vortex-enhanced ducted fan aerodynamic structures rotate in the same direction, while the central vortex-enhanced ducted fan aerodynamic structure rotates in the opposite direction. The vortices generated by the vortex-enhanced ducted fan aerodynamic structure, the vortices generated by outer ring coupling, the centrally enhanced reverse vortex, and the vortex core generated by vortex reconnection are all located on the intake side of the entire propulsion system, constituting the net pressure differential force driving forward. This constructs a high-power, quiet propulsion system with multi-scale vortex flow field coordination.

The large lift and thrust enable stable flight, allowing for continued flight or a safe landing if one propeller stops rotating during flight, enabling the vehicle to land on a road with traffic and drive away, and stabilizing the lateral attitude even in the face of sudden crosswinds. [Solution] The amphibious mobile vehicle 1 comprises a mobile vehicle body 10, front wheels 31, 32 and rear wheels 33, 34 for driving, located in front of and behind the crew compartment 11 of the mobile vehicle body, and a pair of upper front propellers 421 and lower front propellers 441, and a pair of upper rear propellers 461 and lower rear propellers 481 for flight, located in the front and rear arrangement spaces of the mobile vehicle body. The front wheels, which are driven by electric motors, and the inner rotation shafts 411, 451 and outer rotation shafts 431, 471 of the propellers, which rotate in opposite directions to generate lift and thrust by electric motors 231, 241, 251, 261, are arranged parallel and coaxially with the mobile vehicle body in the vertical direction.

To start a motorcycle engine more efficiently and at a lower cost. [Solution] An engine starting method is provided for an engine starting system comprising a controller, a power supply device, and an ISG connected to the controller and the power supply device. The method includes the steps of: using the controller to rotate the ISG in the reverse direction with a constant reverse torque value within a reversal time; using the controller to control the power supply device to output a constant forward rotation current to the ISG, thereby rotating the ISG in the forward direction; and, while the ISG is rotating in the forward direction, if the forward rotation angular velocity of the engine due to the ISG exceeds an expected value, the engine is started by the ISG, characterized in that the reverse torque of the ISG due to the constant reverse torque value is greater than the friction resistance value and less than the maximum value of the valve spring resistance, and the forward rotation torque of the ISG due to the constant forward rotation current is greater than the sum of the current values ​​of the friction resistance value and the valve spring resistance.