1765results about "Rotocraft" patented technology

A wind energy plant with a nacelle, a rotor, which features at least one rotor blade adjustable in its blade pitch angle, a central control device for controlling the wind energy plant and a control unit disposed in the rotor for controlling the blade pitch angle of the at least one rotor blade, wherein the central control device and the control unit in the rotor can exchange data with each other via a data link, which comprises at least one first sending and receiving device at the nacelle side and at least one second sending and receiving device at the rotor side, wherein a wireless network connection with a safety-oriented communication protocol is provided between the at least one first sending and receiving device and the at least one second sending and receiving device, and that one monitoring- and communication device at a time is associated to the first and / or the second sending and receiving device, which can monitor the function of the sending and receiving device and initiate a predetermined action in the case of an error.

An undercarriage, a middle large rotor and a middle large motor are connected to the lower portion of a fuselage body and sequentially connected to the top of a middle small tower, and the right front portion, the left front portion, the left rear portion and the right rear portion of the fuselage body are correspondingly connected with a right front fuselage arm, a left front fuselage arm, a left rear fuselage arm, a right rear fuselage arm and a power assembly. The connecting line of the rotating centers of the rotors of the four power assemblies is square or rectangular, the rotating directions of the rotors of the power assemblies at the same opposite angles are the same, the rotating directions of the rotors of the power assemblies at different opposite angles are opposite, and the rotating faces of the two rotors opposite to the middle large rotor in rotating direction incline around the axes of the respective arms. The included angle between the rotating surfaces of the two rotors and the horizontal plane is an acute angle beta, the rotating surfaces of the two rotors with the same rotating direction as the middle large rotor incline around respective arm axes, the included angle between the rotating surfaces of the two rotors and the horizontal plane is an acute angle theta, beta is larger than theta, the reaction torque and the horizontal component torque of the rotors jointly drive the aircraft to steer, and the aircraft has the advantages of being long in endurance time, large in load and high in wind resistance. And a universal flight platform is formed.

A vertical take-off or landing (VTOL) aircraft is disclosed that includes a propulsion system comprising at least four tilting propulsion assemblies and two or more lifting propulsion assemblies. Actuation of the tilting mechanisms can convert the aircraft from a hover configuration, in which all propellers produce thrust generally upward to counteract the aircraft's weight, to a forward flight configuration, in which the four or more tilting propellers produce thrust generally in a forward direction parallel to the fuselage to overcome drag in cruise flight and the lifting propellers produce no thrust or a level of thrust generally less than that required in the hover configuration.

The invention belongs to the technical field of aircraft design, and particularly relates to an integrated tilting power system integrated with hydrogen fuel cell motor electric control and an aircraft. Comprising a tilting mechanism connected with a machine body; the integrated motor and controller is fixedly connected with the tilting mechanism and located at the end, close to the upstream of the incoming flow, of the tilting mechanism; the tilting rotor wing is mounted at one end, close to the incoming flow upstream, of the integrated motor and controller; the hydrogen fuel cell is fixedly connected with the tilting mechanism and is positioned at one end, close to the downstream of the incoming flow, of the tilting mechanism; the nacelle shell wraps the tilting mechanism, the integrated motor, the controller and the hydrogen fuel cell; the nacelle outer heat dissipation fins wrap the nacelle in the circumferential direction; and the tilting mechanism, the integrated motor and controller and the liquid cooling radiating pipeline of the hydrogen fuel cell exchange heat with the radiating fins outside the nacelle.

The invention relates to an electric engine, a power device and an aircraft, and belongs to the technical field of aircraft power equipment.The electric engine comprises a power motor and a liquid cooling flow path arranged in the power motor and comprises a stator support; the heat dissipation system comprises a fan, a radiator and a heat dissipation motor, an outlet of the radiator is connected with an inlet of the liquid cooling flow path, an inlet of the radiator is communicated with an outlet of the liquid cooling flow path, and the fan is used for cooling the radiator and / or the power motor; the motor rear cover is fixedly connected with the stator bracket; and the two direct-current converters are both mounted on the motor rear cover and are both electrically connected with the heat dissipation motor. The two direct-current converters convert high-voltage direct current accessed by the electric engine into low-voltage direct current capable of being used by the heat dissipation motor, and the electricity utilization requirement of the heat dissipation motor is met. Due to the redundancy design of the two direct-current converters, when one path of low-voltage power supply breaks down, the other path of low-voltage power supply can still supply power to the heat dissipation motor in a low-voltage mode, and enough fault handling time can be provided for the whole power supply system.

The invention relates to an electric propulsion heat dissipation system, a power device and an aircraft, and relates to the technical field of aircrafts. The electric propulsion cooling system comprises propellers, arms, power motors and radiators, the electric propulsion cooling system is fixedly connected to an aircraft body structure of the aircraft through the arms, the propellers are arranged at the output ends of the power motors, and the power motors are installed on the arms and can drive the propellers to rotate around the axes of the power motors. The radiator dissipates heat of the power motor through cooling liquid circulation, the vehicle arms are provided with heat dissipation grooves and air outlets, the radiator is installed in the heat dissipation grooves, and orthographic projections of blades of the propeller on the corresponding surfaces of the vehicle arms at least partially cover the radiator, so that airflow generated by the propeller can penetrate through the radiator and then enter the external space through the air outlets. According to the electric propulsion heat dissipation system, the power device and the aircraft, the problem that the lightweight design of the aircraft is affected due to the fact that a current cooling system is large in size and weight is solved.

The utility model relates to a seesaw type propeller hub structure which comprises a base, a propeller clamp and a propeller blade, a main shaft and an amplitude limiting shaft are arranged in the middle of the propeller clamp, the main shaft penetrates through the amplitude limiting shaft, a main propeller bolt is arranged between the propeller clamp and the propeller blade, a gasket is arranged on the outer wall of the main propeller bolt, a balance weight is arranged on the outer surface of the upper end of the propeller clamp, and a balance weight bolt is arranged in the middle of the balance weight. Paddle bushings are arranged in the middles of the paddles, nuts are in threaded connection with the outer walls of the main paddle bolts, cotter pins are arranged in the middles of the main paddle bolts, and power bolts are arranged at the bottom of the base. According to the utility model, the flapping amplitude relative to the rotor propeller shaft is reduced through the variable pitch-flapping coupling, the transient flapping and the steady flapping relative to the propeller shaft are reduced, the flapping function and the variable pitch function are integrated at one hinge point, the number of parts is reduced, and the overall structure is simplified; due to the fact that parts are reduced, the overall weight is lighter, manufacturing is easy, meanwhile, the number of movable parts is smaller, and the reliability and maintainability of a system can be improved.

The invention is a flying object equipped with a loading part holding a delivery payload, and the loading part or the delivery payload is attached to an airframe so that the loading part or the delivery payload is tilted backward in the forward and backward direction in a landing state or hovering state. The loading part or delivery payload is attached to the airframe so that the loading part or delivery payload is substantially horizontal during cruising.

The invention discloses a composite blade electroforming metal wrapping sheet and a production device thereof, and relates to the technical field of blade metal wrapping sheets, the composite blade electroforming metal wrapping sheet comprises a plurality of wrapping sheet sections, one side surface of each wrapping sheet section is provided with a fixing slot, a reinforcing assembly is arranged in each wrapping sheet section, and the reinforcing assembly comprises an additional side plate arranged on one side surface of each wrapping sheet section, the multiple wrapping sheet sections and the additional side plates are combined into a wrapping sheet finished product piece, a fixed side block is arranged at one end of the wrapping sheet finished product piece, the surface of one side of the fixed side block is connected with the surface of one side of the additional side plate at one tail end of the wrapping sheet finished product piece, a connecting shaft rod is arranged on the upper surface of the fixed side block, and a turnover anchoring plate is arranged on the surface of one side of the connecting shaft rod. And a plurality of anchoring screws are arranged on the upper surface of the overturning anchoring plate, and in the scheme, by arranging the reinforcing assembly and the machining mechanism, the stability of the wrapping piece in the using process and the production efficiency are improved.

Systems and methods involving aircraft are provided. In some embodiments, a rotorcraft (drone) made up of one or more ducted blade enclosures is provided.

A convertiplane (1) is described, which comprises a fuselage (2) extending along a first axis (A), a pair of half-wings (3) projecting cantilevered from respective sides of the fuselage (2), a pair of nacelles (4) housing respective engines and operatively connected to the half-wings (3); and a pair of rotors (5) associated with the half-wings (3), rotatable around respective second axes (B) and tiltable so as to arrange the convertiplane (1) in an airplane configuration or in a helicopter configuration. Each half-wing (3) further comprises a wingbox (20) and an appendage (21) articulated on the wingbox (20) and selectively movable between a relative first neutral operating position taken when the convertiplane (1) is in the airplane configuration and in which it defines an extension of the wingbox (20) and a relative second position taken when the convertiplane (1) is in the helicopter configuration and in which it defines with the wingbox (20) a compartment (50) through which the air flow generated by the respective rotor (5) can pass. The convertiplane (1) comprises a closing system (60) configured to elastically preload each appendage (21) towards the respective first neutral operating position.

The present invention relates to a vertical take-off and landing (VTOL) aircraft featuring a central fuselage and at least two power units. Each power unit is connected to at least two separate lifting rotors via transmission lines, ensuring that each power unit is linked to at least two rotors diametrically opposed relative to the centre of gravity of the aircraft. The lifting rotors might be driven by power transmission lines of hydrostatic type. The power units on either side might be housed in separate pods which might be incorporated into the main fuselage or arranged as separate pods. These separate pods might also function as floats / pontoons for the aircraft to land, take-off and manoeuvre on water.

The present invention provides landing gear that reduces the effects of wind from a predetermined direction on the landing gear during flight, thereby improving fuel efficiency and stability, and reducing the impact during landing. [Solution] The aircraft in the present invention is equipped with landing gear having a contact surface, wherein the contact surface has a shape that reduces drag during travel compared to when landing. The shape of the contact surface is substantially airfoil in the longitudinal direction of the aircraft, and the angle of attack of the contact surface decreases during travel compared to when landing. The shape of the contact surface is inverted airfoil in the longitudinal direction of the aircraft, and the angle of attack of the contact surface decreases during travel compared to when landing. Multiple landing gears are provided, and the contact surface of the above shape is provided only on the landing gear on the front side of the aircraft. The landing gear is connected to the contact surface and is equipped with an intermediate member that extends at least vertically, and the structure of the contact surface is more fragile than the intermediate member.

A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. Some of the rotors are forward canted, while some of the rotors are forward facing. The forward canted rotors are tilted forward slightly from vertical and provide some forward propulsion during horizontal flight. The forward facing rotors may be fixed in a forward facing configuration. Forward swept wings allow for rotor placement which brings efficiency during hover operations.

Aircraft capable of hovering comprising a fuselage at least one rotor that is rotatable with respect to the fuselage, electrical drive means adapted to rotate the rotor and electrically powered by a battery, and a cooling system of the battery. Said cooling system comprises, in turn, a first opening for the air to enter, second openings for the air to escape and a passage which places the first opening in fluidic communication with the second openings and within which the battery is placed. The cooling system further comprises a fan adapted to increase the kinetic energy of the air contained in the passage and which is operated when the forward speed of the aircraft with respect to the ground is lower than a speed threshold value and / or when the temperature of the battery exceeds a temperature threshold value.

The invention relates to the field of aircrafts, and discloses a sandwich-structured composite material mute paddle, which comprises a paddle blade, and the paddle blade is a sandwich carbon fiber laminated structure composed of an upper layer prepreg laying layer unit, a foam sandwich layer and a lower layer prepreg laying layer unit; the upper-layer prepreg laying unit and the lower-layer prepreg laying unit are each of a bionic spiral structure formed by stacking multiple layers of composite material prepreg sheets in a bionic spiral laying sequence. The invention further discloses the preparation method of the composite material mute paddle of the sandwich structure. Load can be effectively transmitted and dispersed along fiber paths in different directions in the outer-layer prepreg bionic spiral structure, so that the comprehensive rigidity, the torsional property and the damage tolerance of the paddle are improved, the material characteristics are optimized, a three-section type pressurization method is adopted, a stable external pressure environment is established in the early stage of paddle foaming, and the mechanical performance of the paddle is improved. And dynamic balance and collaborative forming of internal and external pressure in the paddle forming process are achieved.

The invention discloses a propeller hub for a helicopter, a rotor system and the helicopter, and relates to the technical field of aircrafts, the propeller hub comprises a variable pitch hinge mounting seat, an inner propeller hub center body, an elastic device and at least three force transmission devices, and the inner propeller hub center body is arranged in an inner cavity of the variable pitch hinge mounting seat; the elastic device is connected with the inner propeller hub center body and the variable pitch hinge mounting seat; each force transmission device is movably connected with the inner propeller hub center body, each force transmission device is connected with the inner side wall of the variable-pitch hinge mounting seat, and the variable-pitch hinge mounting seat can rotate relative to the force transmission devices so as to generate tilting rotation relative to the radial plane of the rotor shaft; when the rotor shaft rotates, the rotor shaft can drive the inner propeller hub center body, the force transmission devices and the pitch-variable hinge mounting base to rotate. And when the variable-pitch hinge mounting seat tilts relative to the radial plane of the rotor shaft, the elastic device can be compressed or stretched, and the variable-pitch hinge mounting seat can be reset under the action of restoring force of the elastic device. Flight flexibility and stability can be ensured, and the flight quality of the helicopter is effectively improved.

The invention discloses a fixed wing type cross-domain aircraft capable of realizing self-adaptive load replacement, belongs to the technical field of cross-domain aircrafts, and is used for a water-air double-domain operation cross-domain aircraft. Comprising an aircraft body, a main wing, an aileron, a tail assembly, a vertical take-off and landing support, a vertical take-off and landing rotor wing, a fixed wing propeller, an underwater propeller, a load replacement device and a control module. The control module comprises a decision making system, a telemetering communication system, a state sensing system, an underwater water surface load replacement system, a water surface four-rotor vertical take-off and landing control system, an air fixed-wing cruise control system and an underwater vehicle control system. According to the fixed wing type cross-domain aircraft, through collaborative innovation of a multi-mode power system and self-adaptive buoyancy control, the dynamic characteristic adaptation problem in cross-domain navigation is solved, and the fixed wing type cross-domain aircraft has the vertical take-off and landing capacity, the air cruising capacity and the underwater maneuvering capacity.

Systems and methods include a tilt device for an aircraft vehicle. The tilt device is configured to rotate a rotor assembly between first and second positions. The tilt device comprises a linear actuator disposed within an aircraft fairing; a sleeve having a slot defined therein; and a piston coupled to the linear actuator configured to translate axially within the sleeve. A method includes actuating the linear actuator to translate the piston, wherein the rotor assembly is coupled to an end of the piston and comprises a motor and one or more rotor blades. The method further includes rotating the piston within the sleeve as the piston translates axially along the sleeve via a pin disposed within a slot defined in the sleeve, wherein the pin extends from the piston and through the slot. The method further includes actuating the motor to operate the one or more rotor blades.

A method of operating an automated fiber placement system includes supplying a plurality of tows to a tow deposition assembly of an automated fiber placement head, cutting a first tow into a first upstream and downstream tow portions, continuing to supply the first tow through a compaction roller to apply the first tow to a substrate such that a trailing edge of the first upstream tow portion substantially aligns with a leading edge of the first downstream tow portion at a first interface, cutting a second tow into a second upstream and downstream tow portions, and continuing to supply the second tow through the compaction roller to apply the second tow the substrate such that a trailing edge of the second upstream tow portion substantially aligns with a leading edge of the second downstream tow portion at a second interface that is offset from the first interface.

Embodiments of the invention are directed to systems and methods for reducing drag on an aircraft. The aircraft can include at least one propulsion system with rotor blades configured to reduce aerodynamic drag when the propulsion system is deactivated. To reduce the amount of drag, the rotor blades can be locked into an aerodynamic position, and prevented from passively spinning. Additionally, the rotor blades can be configured to have angular positions that reduce drag. For example, the rotor blades as a group may be configured to generally point toward and / or away from an airflow current.

The invention discloses a tilt rotor aircraft depending on aerodynamic force, and relates to the technical field of aircrafts. The four-axis unmanned aerial vehicle comprises a fuselage, wing assemblies, four-axis unmanned aerial vehicle modules and empennage assemblies. The wing assembly comprises a left wing, a right wing and a wing cross beam which are all provided with ailerons; the four-axis unmanned aerial vehicle module is I-shaped, is hinged to a wing cross beam through a bearing, and can tilt bidirectionally; the empennage assembly comprises a tail support, a horizontal electric variable pitch propeller, a horizontal empennage with a control surface and a vertical empennage. The four-axis unmanned aerial vehicle module serves as a tilting unit, and the structure is simplified; attitude control is realized by virtue of aerodynamic difference, and the efficiency is improved; the tail horizontal electric variable-pitch propeller realizes rapid pitching adjustment; vertical take-off and landing, low-altitude maneuvering and high-speed cruising capabilities are integrated, the application scene is wide, and safe forced landing can be achieved when faults occur.

A VTOL aircraft (300, 600) includes a lift propeller (312, 612) configured to provide lift during take-off, landing, and hover operations. The lift propellers (312, 612) are configured to stow close to the boom surface (323, 623) when not in use, for example, during a cruise flight, to minimize drag around the surface of the propellers (312, 612). The lift propellers (312, 612) are vertically displaceable relative to the booms (322, 622) when switched to a lift configuration to provide a greater spacing from the booms (322, 622) to improve lift efficiency and reduce unwanted vibrations. The lift propeller (312, 612) may have a fail-safe configuration that allows the propeller (312, 612) to passively move between a lift configuration and a stowed configuration, and to fully rotate even when fully retracted.

The invention relates to an electric engine, a control method thereof, an electric propulsion system and an aircraft in the technical field of aircrafts. The electric engine comprises a first motor, a first control channel and a second control channel; the first motor comprises two windings, namely a first power winding and a second power winding; when the electric engine is in an initial working state, any control channel serves as a master control channel, the other control channel serves as a slave control channel, and the master control channel is used for executing torque distribution, coordinating the slave control channel and driving the two power windings to execute a power control instruction; any control channel is used for being switched to the main control channel to maintain power output when it is monitored that the other control channel loses the capacity of driving the first motor. According to the electric engine, the double-winding motor and the corresponding double control channels are arranged, when one control channel of the electric engine breaks down, the windings of the double-winding motor can still be driven to maintain power output, and the problem that it is difficult for the engine to guarantee that power is not interrupted is solved.

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.

An aircraft seat connector for mounting an aircraft seat to a mounting rail provided at a floor of an aircraft cabin is provided. The aircraft seat connector comprises a base portion for being introduced into the mounting rail and a seat connection portion. The seat connection portion extends from the base portion and is configured for being releasably coupled to an aircraft seat. The seat connection portion allows for coupling the aircraft seat to the seat connection portion in at least two different spatial orientations.

The water-land-air triphibian variable-configuration robot comprises a robot body, a deformation wheel, a rotating wheel and a clamping jaw mechanism, and the robot body comprises a middle connecting pipe, a clamping jaw seat and two robot body deformation assemblies; the clamping jaw seat is rotatably arranged on the middle connecting pipe, and the clamping jaw mechanism is arranged on the clamping jaw seat; the two aircraft body deformation assemblies are arranged on the middle connecting pipe and connected with the deformation wheels and the rotating wheels correspondingly so that the deformation wheels and the rotating wheels can rotate around the middle connecting pipe, and then the whole aircraft can be switched among a flight mode, a ground mode and a water surface mode. And the deformation wheels are provided with paddle legs which can be embedded or opened, so that the whole machine is deformed between a wheel type state and a wheel paddle leg state. According to the invention, triphibian multi-mode movement can be realized, and a flexible operation tail end is provided.

The invention discloses a flight control device, an aircraft control method and a vertical take-off and landing aircraft, and relates to the technical field of aircraft control. A main manipulator configured to receive manipulation information input by a pilot; the backup manipulator and the main manipulator are independently arranged relatively, and the backup manipulator is configured to receive manipulation information input by a pilot; the control system is configured to identify a target manipulator from the main manipulator and the backup manipulator, generate a vector control instruction mapped with the manipulation information by using a signal corresponding to the manipulation information received from the target manipulator and combining a preset manipulation mapping relation, and control the target manipulator according to the vector control instruction. And controlling the aircraft to perform vector motion according to the vector control instruction. According to the scheme, the complexity of aircraft control can be effectively reduced, and the safety of aircraft control is improved.

The variable-configuration multi-purpose robot comprises a robot body and the wheel-claw-paddle composite mechanism, the robot body comprises a robot body, an upper cover plate and two side plates, the upper cover plate is fixed to the robot body, and the two side plates are rotatably arranged on the two sides of the cover plate through two hinges correspondingly; the hinge is a rotary damping adjustable hinge; the wheel-claw-paddle composite mechanism is allowed to be switched between a wheel-claw-paddle state and a wheel-type state, the wheel-claw-paddle composite mechanism is arranged on the side plate so that the side plate can rotate and be locked relative to the upper cover plate within a set angle range, and then the whole machine can be switched among a flight mode, a ground mode and a water surface mode. The device can adapt to water, land and air triphibian environments at the same time and is integrated with light-weight design.

The invention discloses a powerful propeller and an aircraft, and belongs to the technical field of aircrafts. The powerful propeller comprises a cover disc, a stator and a rotor, the cover disc comprises a central bearing seat, a radial support and an outer mounting frame which are sequentially connected from inside to outside, the rotor comprises a paddle mounting column, paddles and an outer ring which are sequentially connected from inside to outside, and the outer ring is provided with a permanent magnet which is in induction fit with the stator; the paddle mounting column is connected with the central bearing seat through a bearing; and the outer mounting frame is fixedly connected with the stator. Airflow loss of the blade tip can be avoided, and thrust is greatly improved. According to the invention, the coaxial contra-rotating technology can be realized. And the two coaxial fans can achieve a better superposition effect, so that the noise is reduced. The rotating directions of the two blades which are coaxially designed are opposite, the rotating torque of the propeller can be offset, and balance of the aircraft fuselage can be kept beneficially. According to the invention, a negative pressure suction air cooling technology can be designed according to needs to solve the problem of motor heat dissipation, and extra electric energy consumption is not needed.