132 results about "Rotary wing" patented technology

Disclosed herein are spinning wing decoys for hunting, birdwatching, photographing, and other outdoor activities. In a specific embodiment, the spinning wing decoy includes: an axle, axle hub, drive shaft, motor, motor housing, motor door, retainer ring, remote controller, receiver, transmitter, computer, switch, main control box, bottom door, bearing housing lids, bearing housing, protect plate peg, blade, wing, frame, battery, battery lid, battery housing, housing unit, attachment member, mounting member, and support member.

A folding wingtip aircraft includes a wing that includes a primary portion and a wingtip. The folding wingtip aircraft includes a folding wingtip system configured to rotate the wingtip relative to the primary portion. The folding wingtip aircraft also includes a flight control computer. The flight control computer is configured to, in response to a first determination that a wingtip position of the wingtip is not in a folded position when a second determination indicates that a last completed command by the folding wingtip system was a fold command, set error codes for the folding wingtip system. The flight control computer is also configured to change a setting to indicate that the folding wingtip aircraft is grounded based on the error codes.

A mobile object 1 according to the present disclosure includes a body 10 provided as a first polyhedron, and rotary-wing modules 20 attached to the body 10 at all vertices of the first polyhedron. The rotary-wing modules 20 each include a rotary wing 21 and a drive unit 22. The drive unit 22 is configured to drive the rotary wing 21. The rotary wings 21 are located outside the body 10 and each have a rotation axis that is a straight line connecting a reference point PO and a corresponding one of the vertices of the first polyhedron. The reference point PO is defined inside the body 10.

The utility model provides a water inlet flow fine adjustment structure of a rotary wing type water meter, and belongs to the technical field of water meters. The ball bowl and the limiting grooves communicated with the ball bowl are arranged on the head portion of the fixing screw, each limiting groove is arranged in the radial direction of the fixing screw, the ball head at one end of the adjusting rod is installed in the ball bowl, the adjusting rod is selectively clamped into one limiting groove, and therefore the adjusting rod can serve as a handle for screwing the fixing screw. The adjusting rod is matched with different limiting grooves, interference of structures such as the meter head and the water inlet on rotation of the adjusting rod is effectively avoided, continuous screwing of the fixing screw is maintained, the other end of the adjusting rod is a matching head, the end of the adjusting screw is provided with a matching hole matched with the ball head, the adjusting screw can be directly screwed through the adjusting rod, and the adjusting rod is convenient to use. The water inlet flow can be adjusted without additional tools, and operation is more convenient and faster.

To provide a rotary wing aircraft having improved safety with a simple structure.SOLUTION: This rotary wing aircraft 1 has a body surrounded by a cage side 3A, and includes an aerodynamic parts side 3A composed of a plate-shaped body inclined to the outside of the cage side 3A, and arranged so as to surround an upper surface, in the edge of the upper surface for constituting the cage side 4A.SELECTED DRAWING: Figure 1

The invention provides an aircraft control method and a rotorcraft. The method comprises the steps that the current attack angle of a high lift wing is obtained through an angle-of-attack device; calculating a target included angle between the high lift wing and the rotor wing according to the relation between the current attack angle and a set angle; the set angle relation is an incidence relation between an included angle between the high lift wing and the rotor wing and the attack angle; adjusting the included angle between a high lift wing and a rotor wing of the rotor craft to be the target included angle through the angle adjuster; when the included angle between the high lift wing and the target included angle is the target included angle, the attack angle of the high lift wing is correspondingly adjusted to be the optimal attack angle. The current attack angle of the high-lift wing is measured through the angle-of-attack device, the relative angle between the high-lift wing and the rotor wing is adjusted accordingly, the optimal lift-drag ratio working condition of the high-lift wing is achieved, power consumption of the rotor wing is reduced, and the loading capacity, the endurance time and the endurance mileage of the rotorcraft are improved.

The utility model relates to the technical field of measuring instruments, in particular to a high-precision rotary wing type water meter which comprises a shell and an impeller rotationally arranged in the shell, the shell comprises a hollow mounting cavity and a water inlet pipe and a water outlet pipe which are located at the two ends of the mounting cavity respectively, and an impeller box provided with a plurality of through holes in the circumferential direction is arranged in the mounting cavity; the impeller is installed in the impeller box, a gear set is connected to the installation cavity, the gear set is in transmission connection with a counter used for counting, a check block capable of sealing the water inlet pipe is arranged at the position, close to the water inlet pipe, in the installation cavity in a sliding mode, the check block is connected with a compression spring, and the impeller comprises a middle shaft and a plurality of rotating blades arranged on the side wall of the middle shaft at intervals in the circumferential direction. The middle shaft is slidably sleeved with a locking assembly capable of locking rotation of the impeller, the locking assembly is in transmission connection with the check block, when no water flow exists in the water inlet pipe, the check block seals the water inlet pipe, and the locking assembly limits rotation of the impeller. The water meter impeller can be locked when no water flow exists, and the situation that the impeller rotates under the inertia effect, and counting errors are generated is avoided.

The invention belongs to an aircraft structure, and provides a rotor aircraft and a control method thereof in order to solve the technical problem that in an existing rotor aircraft, the prior art still cannot meet the high-performance requirements for main rotor adjustment and power transmission, and the rotor aircraft comprises a fuselage, a tilting assembly, a rotor assembly, a driving assembly and a transmission shaft assembly in the driving assembly. The inner surface of the outer shaft and the outer surface of the inner shaft are each provided with the two spiral grooves with the phase difference of 90 degrees, the multiple rolling pieces are installed at the intersection points of the inner spiral grooves and the outer spiral grooves, and through the structure that the rolling pieces are installed in the spiral grooves, the transmission gap is reduced, and the response speed and the control precision are improved. Due to the design of the two spiral grooves with the phase difference of 90 degrees, transmission between the outer shaft and the inner shaft is stable, and disengagement is avoided. Therefore, the transmission shaft assembly is stable and smooth in transmission, not prone to abrasion and high in transmission precision.

The present invention describes a detachable connection between a pitch control unit arm (5) and a pitch angle piece (8) of a blade holder (7) in a tail rotor head (3) of a tail rotor (1) of a rotary wing aircraft, said detachable connection comprising a pin connecting said pitch angle piece (8) attached to the blade holder (7) with said pitch control unit arm (5) of a pitch control unit (4), thereby reducing material wear and shortening the maintenance cycle. This is achieved because said pin is designed as a sliding pin (9) protruding between the pitch angle piece (8) and the pitch control unit arm (5), which in its length direction passes through a spherical bearing in the form of a ball (6) with a central ball through hole (61), wherein the ball (6) and the part of the sliding pin (9) are surrounded by an outer ring (60) of the spherical bearing, thus allowing a sliding and pivoting movement of the sliding pin (9) inside the spherical bearing.

The utility model relates to the technical field of water meters, in particular to a rotary wing type water meter convenient to observe, which comprises a character wheel box, the character wheel box comprises a box body and a character wheel metering mechanism, the box body is provided with an inner cavity, the character wheel metering mechanism is arranged in the inner cavity, the character wheel metering mechanism comprises a rotatable character wheel set, the side wall of the character wheel set is provided with numbers, and the number of the character wheel set is larger than the number of the character wheel set. The character wheel box further comprises a cover body, a glass sealing cover and a turning cover, the cover body is provided with a reading face, a set of numbers on the side wall of the character wheel set are exposed on the reading face, the reading face is arranged in an inclined mode, the glass sealing cover seals a cavity opening of the inner cavity, the turning cover is installed on the box body in a rotating mode, and after the turning cover rotates by a preset angle, the turning cover covers or exposes the glass sealing cover. According to the utility model, the reading surface is arranged in an inclined manner, and the flip cover covers the glass sealing cover in a normal state, so that the advantages of reading in a side-looking manner and effectively preventing dust and stains from blocking the reading area are realized.

The utility model discloses a welding positioning assistor, which relates to the technical field of welding, and comprises a fixed wing, the end part of the fixed wing is rotatably connected with a rotary wing, the fixed wing and the rotary wing are consistent in structure, and detachable structures are arranged on the outer sides and the inner sides of the fixed wing and the rotary wing. The detachable structure comprises installation clamping grooves located in the inner sides of the fixed wing and the rotating wing. According to the welding positioning assist device, when the magnetic force of the inner magnetic strip and the outer magnetic strip is weakened or damaged, the inner magnetic strip needs to exchange heat, the outer magnetic strip needs to be replaced, and when the cover plate is separated from the end of the fixed wing and the end of the rotating wing, the clamping block can be separated from the inner magnetic strip; and meanwhile, the cover plate is separated from the end parts of the fixed wing and the rotating wing, so that one end of the mounting sliding groove is in an open state, the inner magnetic strip can be taken out from the interior of the mounting clamping groove, and the outer magnetic strip can be taken out from the interior of the mounting sliding groove, so that the inner magnetic strip and the outer magnetic strip can be conveniently replaced, and the service life of the assist device is prolonged.

A rotor assembly for a rotary wing aircraft includes a rotor hub including a hub arm and a central opening. The rotor assembly further includes a hydraulic actuation cylinder positioned in the central opening, a pitch change shaft assembly including a pitch change shaft positioned partially within the hydraulic actuation cylinder, a pitch beam coupled to a distal end of the pitch change shaft and configured to be coupled to a rotor blade rotatably mounted to the hub arm. The rotor assembly additionally includes at least one guide rod coupled to the rotor hub and slidably coupled to an opening in the pitch change shaft.

A rotary wing drone communicates its altitude (determined by an onboard GPS receiver) and an air pressure (from multiple onboard barometers) to a ground station which has a known height above sea leve

A method for controlling an aircraft with a rotary wing provided with a power plant comprising a plurality of engines, the aircraft comprising a human-machine interface controlling a control member capable of acting on a longitudinal acceleration of the aircraft. During the economy operating mode during which one of the engines does not supply power, the method comprises measuring a forward speed of the aircraft, and adjusting an authority of the human-machine interface over the longitudinal acceleration with a flight control computer as a function of the forward speed.

The invention discloses a shape-preserving and resistance-reducing design method for a rotating mechanism under rotor / fuselage coupling, which comprises the following steps of: setting the slenderness ratio of a streamline shaft sleeve based on a shape resistance coefficient formula, and verifying the surface pressure distribution and the separation area of the shaft sleeve through numerical simulation to ensure that the shape resistance coefficient meets a resistance-reducing target; setting the area ratio of an outlet to an inlet of the seam based on a Venturi effect formula, so that a low-pressure area is formed in the seam to suck a wing root boundary layer and delay airflow separation; establishing an aerodynamic load and motion parameter coupling model based on an instantaneous resistance formula, analyzing flow fields under different rotation angular velocities and oblique angles through numerical simulation, and optimizing a rotation track to reduce a resistance peak value and aerodynamic torque fluctuation; the invention aims to solve the problems of airflow vortex interference, large shape resistance, high resistance peak and poor aerodynamic stability by optimizing the shape of the rotating shaft sleeve, the fuselage-wing gap structure and the wing rotating track, and improves the cruise fuel efficiency and flight stability of the aircraft.

An adaptive navigation light system is provided for a rotary wing air vehicle having at least a main body and a plurality of arms, where the main body includes a front end and a tail end disposed opposite the front end, and each arm of the plurality of arms extends from the main body. The adaptive navigation light system includes a plurality of circular light arrays and a processing system. Each circular light array is operable to emit light of a plurality of different colors, and each circular light array includes a plurality of individual light sources. The processing system is configured to track error data to determine which one of the different colors each circular light array should emit, determine which of the individual light sources in each in each circular light array should be energized, and energize the individual light sources that are determined should be energized.

The application discloses a rotating wing type variable cross-section crack blade fault characterization and dynamics analysis method, belongs to the field of rotating wing type variable cross-section crack blade fault characterization and dynamics analysis, and comprises the following steps: according to the finite element theory and the plate shell theory, based on centrifugal rigidification, rotation softening and the coriolis force effect, a motion differential equation of the wing type variable cross-section blade is established; according to the motion differential equation of the wing type variable cross-section blade, based on the crack existing in the blade, the breathing effect between crack surfaces is equivalent by adopting a spring unit, a rotating wing type variable cross-section crack blade dynamics model containing the breathing effect is established, vibration energy theory is adopted to convert the displacement response into energy response, based on the rotating crack blade crack diagnosis index with the breathing effect, the crack characteristics of the blade are obtained, and the application is more effective and accurate in analyzing the rotating crack blade fault, and can provide theoretical guidance for detection and diagnosis of the rotating crack blade.

A rotating airfoil includes a body and a damper located within the body. The body has a root end and a tip end. The rotating airfoil has a natural frequency, and the damper has a natural frequency. The natural frequency of the damper is different than the natural frequency of the rotating airfoil.

A blade for a rotary wing able to rotate about an axis of rotation, the blade extending along the pitch axis from a first end to a second end, the blade comprising a blade body having, from the first end to the second end, a succession of sections substantially perpendicular to the pitch axis. Along its pitch axis, the blade has sections having: increasing and then decreasing chords, a relative thickness that decreases from an initial section to a final section, twist angles that continuously increase from the origin section to an initial section and then decrease, and a changing offset relative to the pitch axis.

An unducted airfoil assembly includes an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges. The airfoil defines a forward-most axial point and is arranged around a longitudinal axis and rotates about the longitudinal axis in a rotational direction. A tip leading edge of the airfoil is circumferentially offset in a direction opposite the rotational direction relative to a circumferential location of the forward-most axial point.

To improve safety during charging of an electric flight vehicle.SOLUTION: An electric flight vehicle 10, which flies by rotating a rotary wing 13 by electric power supplied from a battery 14, comprises output equipment 15 that performs output for calling attention outward from the electric flight vehicle 10 during the charging of the battery 14 from an external power source 20.SELECTED DRAWING: Figure 1

The invention relates to the technical field of aircraft power generation, and discloses a power generation system of an unlimited continuous underwater aircraft, which comprises a main body frame, a wave energy capturing unit, a solar power generation unit, a transmission and power generation unit and a control and energy storage unit, the main body frame adopts a corrosion-resistant steel structure, a latticed photovoltaic mounting area is arranged at the top of the main body frame, and reinforcing ribs and connecting seats connected with the rotary wings are arranged below the main body frame; the wave energy capturing unit comprises rotary wing modules symmetrically arranged on the two sides of the main body frame. A wave energy capturing unit and a solar power generation unit are compositely integrated, an impeller type capturing piece and a permanent magnet synchronous generator are driven by reciprocating swing of rotary wings on the two sides to operate cooperatively, and meanwhile flexible solar cell modules are arranged on the top of a main body frame and the surfaces of the two wings. Parallel collection and complementary power supply of wave energy and solar energy on the same carrier are realized, and all-weather and multi-mode energy capture and continuous power supply of an underwater vehicle in a complex marine environment are realized.

The disclosure relates to a technique for controlling an electric flight vehicle having a rotary wing driven by electric power of a battery. In the technique, a temperature of the battery is acquired as a battery temperature. Restriction is placed on take-off of the electric flight vehicle when the battery temperature is lower than a take-off permitting temperature that is a temperature for permitting take-off of the electric flight vehicle. The restriction placed on take-off of the electric flight vehicle may be terminated when the battery temperature exceeds a restriction terminating temperature and the battery temperature raising processing is performed. The restriction terminating temperature is higher than the take-off permitting temperature.

An aircraft with a rotary wing, provided with a tail boom carrying a tail fin. The aircraft comprises a pitch stabilization system that is provided with at least one pitch stabilizer comprising a first aerodynamic segment and a second aerodynamic segment. The first aerodynamic segment extends from the tail boom, from a first root section to a first end section, and the second aerodynamic segment extends from the tail fin, from a second root section to a second end section, the first end section being connected directly to the second end section or via a connecting segment.

Reducing aeroelastic flutter in a wing tip 404 comprises providing at an end of a fixed wing 402 a rotatable wing tip rotatable a first distance to lower the centre of gravity of the wing tip, i.e. a

The utility model relates to the technical field of helicopters, in particular to a vertical take-off and landing electric helicopter with composite wings. The vertical take-off and landing electric helicopter comprises a helicopter body, multiple sets of lift propellers are arranged on the front side and the rear side of the helicopter body correspondingly, multiple sets of lift propellers are arranged on the left side and the right side of the helicopter body correspondingly, a front push propeller is arranged on the rear side of the helicopter body, and the front push propeller and the lift propellers are driven by motors; rotary wings are arranged at the top of the aircraft body and controlled through a wing rotating mechanism. The foldable lift propellers are arranged on the left side and the right side of the helicopter body, so that the propeller pitch of the helicopter is increased, the crosswind resistance of the helicopter is improved, and the safety performance of the helicopter is improved; the rotating direction of the wings is controlled through the wing rotating mechanism, and the wings are locked and positioned. After the folding type lifting force paddles and the rotary type wings are folded, the helicopter can be parked in a single parking space and can take off and land on a single lane and the roadside of a road; when the wings are unfolded, the wings generate lift force, and the front propellers provide thrust.

The present invention relates to a method for simulating an engine failure on a rotorcraft (1) comprising several engines (10) for setting a rotary wing (6) in motion. The method includes a training mode comprising control with a governor (30) for each engine (10) to simulate an engine failure, this control including a limitation of the power of each engine (10) to a respective control limit. The training mode comprises the following steps: i) determining, with the governor (30), on the one hand, a maximum mass based on at least external conditions and, on the other hand, an initial mass of the rotorcraft (1) based on at least the empty mass of the rotorcraft (1), the mass of a crew present in the rotorcraft (1), and an estimated mass of fuel on board; ii) comparing, with the governor (30), the initial mass to the maximum mass; iii) determining, with the governor (30), each control limit based on said comparison.Abbreviated figure: figure 1.

To provide means for obtaining lifting force and thrust and performing flight in a conventional flight body such as drone, rotary wing aircraft and so on without installing a propeller and a rotor so as to be exposed to the outside.SOLUTION: A fixed wing 2 is fixedly installed in a body 1 of drone and flight body. A propeller 4, which is driven by a motor 3, is arranged in the front of the fixed wing 2, and generates air stream 5 by air taken in from an intake port A. By flowing the air stream 5 horizontally to the fixed wing 2 at a high speed, lifting force 6 is generated in the fixed wing 2. By the lifting force 6 generated in the fixed wing 2, the body 1 of the drone and flight body ascends. The air stream 5 is discharged from an exhaust port B after passing the fixed wing 2, and becomes thrust for flying the body 1 of the drone and flight body, and navigation is performed in such a manner that a direction is controlled by a rudder 7.SELECTED DRAWING: Figure 2

The invention discloses an electromagnetic coupling energy induction transmission system, belongs to the technical field of wireless charging, and particularly relates to a wireless charging system for a rotor unmanned aerial vehicle with a lightweight receiving end. The problems that an existing wireless charging system for the unmanned rotorcraft and a magnetic coupling mechanism of the wireless charging system are poor in anti-offset performance, the weight of a receiving end is large, the structure is complex, and the transmission efficiency is low are solved. The system comprises a transmitting end, a receiving end and a magnetic coupling mechanism, and the transmitting end inductor and the receiving end inductor are used for sending the alternating current with the given frequency to the receiving end in an alternating magnetic field mode through electromagnetic induction. The electromagnetic coupling energy induction transmission system is suitable for wireless charging of the rotor unmanned aerial vehicle.