65 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.

The disclosure provides a pod propulsion system including first and second counter rotating propellers for providing thrust to propel a marine vessel. The pod propulsion system includes a first electric motor (i) for rotating the first propeller and (ii) electrically coupled to a first drive, the first drive being configured to control the first motor and a second electric motor (i) for rotating the second propeller and (ii) electrically coupled to a second drive, the second drive being configured to control the second motor. The first and second drives respectively control the first and second motors interdependently.

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

An aircraft engine is provided. The aircraft engine includes a compressor section having a compressor. A turbine section is downstream of the compressor section. The turbine section includes a turbine having turbine blades arranged in counter rotating stages. The aircraft engine further includes one or more fluid supply lines and a fuel cell assembly fluidly coupled to the one or more fluid supply lines for receiving one or more input fluids. The fuel cell assembly is in fluid communication with the turbine section to provide one or more output products to the turbine section. The aircraft engine further includes a heat exchanger in fluid communication with the turbine downstream of the counter rotating stages of turbine blades to receive exhaust gases from the turbine. The heat exchanger is thermally coupled to the one or more fluid supply lines of the fuel cell assembly.

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.

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.

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 ice paddle milling protection device comprises a connecting cylinder, one end of the connecting cylinder is connected with a pod propeller body, the other end of the connecting cylinder is rotationally connected with a propeller hub, a plurality of paddles are arranged on the propeller hub in the circumferential direction, a protective cover is arranged on the connecting cylinder in a sliding mode, and the protective cover is connected with the connecting cylinder in a sliding mode. The protective cover can reciprocate in the axial direction of the connecting cylinder, a cutting assembly is arranged on the side, away from the connecting cylinder, of the propeller hub, the cutting assembly is connected with the inner wall of the protective cover, and the cutting assembly and the propeller hub rotate in the opposite direction. According to the pod propeller, impact of crushed ice in the advancing direction of the pod propeller on the propeller blades can be blocked through the protective cover, meanwhile, impact force generated by ice blocks can be relieved through axial movement of the protective cover relative to the connecting cylinder, and the service life of the propeller is prolonged; and meanwhile, the cutting assembly can crush part of ice blocks sucked into the protective cover from the opening of the protective cover due to the suction principle.

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.

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 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 invention provides a shear screw type fairing separating mechanism, an assembling method and a separating method.The shear screw type fairing separating mechanism comprises at least two cover bodies, and the cover bodies are spliced in the radial direction and provided with connecting and separating structures which are fixedly connected with each other; the connecting and separating structures are arranged at intervals along the splicing positions between the cover bodies, and the connecting and separating structures form weakening positions and are fractured in the splicing direction between the cover bodies. Hinges connected to the aircraft are arranged at the rear ends of the cover bodies respectively, guide grooves with openings facing the outer side are formed in the aircraft, and the hinges are rotatably and slidably connected into the guide grooves; an ignition actuating cylinder for driving the connecting and separating structure to break is arranged between the cover bodies in the splicing direction, the opposite cover bodies rotate reversely along the hinges, and the hinges slide along the guide grooves respectively and are separated from the aircraft. The structure has good manufacturability and easy assembly, and the whole structure has the effects of good strength and rigidity while the requirements of small-size space application and structure light weight are met.

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.

Provided is a pod propulsion system including first and second counter rotating propellers for propelling a marine vessel first and second propeller modules, each including an electric motor having a driving-end configured to rotate the first and second propellers, respectively. Also included are first and second gondolas, each (i) for housing a respective one of the first and second electric motors and (ii) including a boltable interface formed along a lengthwise direction of an extremity of the gondola. A strut (i) connects the first and second gondolas to a hull of the marine vessel (ii) including first and second boltable interfaces. Each of the boltable interfaces of the strut is configured to form a bolted joint interface with a corresponding one of boltable interfaces of the first and second gondolas.

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.