30results about "Rotocraft" patented technology

A reinforcing sheet for wind power generator blades includes a resin layer and a restricting layer laminated on the resin layer.

The invention discloses an amphibious power propulsion device suitable for sea and air, comprising a frame type retainer, a tilting motor, a power motor fixedly arranged at the middle part of the retainer, as well as propellers for air and propellers for sea, which are coaxially and rotatably arranged at a certain interval, wherein the propellers for air are in driving connection with the power motor through a unidirectional rotation mechanism, the propellers for sea are in driving connection with the power motor, a rotating shaft of the tilting motor is fixed at the outer side of the retainer through a connecting plate, and the rotating axis of the tilting motor is perpendicular to the rotating axis of the propellers for air and the propellers for sea. The invention also provides an amphibious multi-axis aircraft suitable for sea and air. According to the amphibious power propulsion device and the amphibious multi-axis aircraft, the same motor is adopted to simultaneously adapt to two different working environments, namely in the air and under the water, thereby reducing the weight of the amphibious aircraft for sea and air and simplifying the structure of the aircraft; and meanwhile, the tilting motor is used for controlling the direction of power output, thereby increasing the maneuverability of the amphibious aircraft and strengthening the capability of the amphibious aircraft for finishing complex tasks.

The invention relates to a control method and a system of a helicopter rotor, which belongs to the technical field of helicopter operation. The control method is characterized in that the distance changing of a blade is realized by adopting an actuator positioned on the stinger of each propeller boss to drive a flap positioned at the rear edge of the blade, so as to realize the control of a rotor system. The system comprises a demountable flap (1) installed at rear edge of the blade, torque soft propeller bosses (14), an actuator (13) installed on the stinger of torque soft propeller bosses, a flap control mechanism (1) with one end being connected with actuator (13) and the other end thereof being connected with the flap (1), and a test control system (59). The control method and the system have the advantages that the screw piston of each blade can be independently controlled, the structure is simple, the weight is light, the controllability is good, and the reliability and the security are high.

A radial compressor rotor is provided for stabilizing the flow behavior of a delivery gas, consisting of a wheel disc and blades arranged uniformly in the circumferential direction, wherein the generatrix of the surface of the blades is designed as a curved line at least in a curved section, such that the surface is curved in two directions in this section.

An aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades. The main rotor blades are connected to a first annular gear that rotates in a first direction and the counter-rotation blades rotate are connected to a second annular gear that rotates in a second direction that is opposite the first direction for anti-torque. Planetary gears simultaneously drive the first and second annular gear at about the same speed.

The invention discloses a layout and control method of a distributed power tilt-wing aircraft. A canard-configuration aircraft is selected. Channels are disposed inside a front canard wing and a mainwing for mounting a plurality of engines to realize distributed power. For a vertical take-off state, the front canard wing and the main wing are tilted to be vertical, eight engines generate a pulling force to enable engine bodies off from the ground, and meanwhile, a differential operation is performed for correcting the attitude of the engine bodies. Upon reaching a certain height, the front canard wing and the main wing gradually tilt, and an angle is dynamically adjusted according to an accelerator. When a current forward speed is sufficient to make a lifting force generated by the frontcanard wing and the main wing balanced against gravity, the front canard wing and the main wing completely turn to be horizontal, and enter a high-speed flat flying state, such that the transition from vertical take-off to hovering to flat flying is realized. The transition process from flat flying to hovering to vertical landing is just opposite. The power system of the invention is disposed simply and a latching mechanism is disposed. The control of the invention is direct and reliable and isolates a tilting mechanism from attitude control, thereby avoiding the problem of causing failure ofa plurality of functions by a system fault.

The present invention discloses a multi-shaft power source unmanned flight equipment, and belongs to the technical field of unmanned aerial vehicles. The multi-shaft power source unmanned flight equipment comprises a frame (1), a plurality of rotor sets (2) and a power device (3). The plurality of rotor sets (2) are rotatably fixed on the frame (1), and the power device (3) is correspondingly movably connected with each rotor set (2) respectively. Power is provided for flight of the unmanned flight equipment by the power device (3) with oil drive characteristics, mechanical kinetic energy is generated by burning a combustion material pre-injected in the power device (3), and rotors (21) in each rotor set (2) correspondingly connected with the power device are driven to rotate, thereby replacing the traditional electric multi-rotor unmanned aerial vehicle structure adopting electric modes such as batteries, electronic speed controllers and the like to supply power and provide power for the rotation of the rotors (21); and the unmanned flight equipment has the characteristics of long duration and strong loading capacity.

An electric power generation system employs a thermoelectric generator placed between an aircraft inner skin and an aircraft outer skin. The thermoelectric generator is configured to utilize a thermal differential between the inner and outer skin to generate an electric current. An electrical interface is provided for access to the electric current generated by said thermoelectric generator.

A method and system for a helicopter blade emergency detachment system that has an activator in the cockpit to initiate the system, an ignition train to provide the detonation signal, a transfer system at the base of the main rotor shaft to move the signal from the stationary helicopter to the rotating blades, and explosive charges located at the root of each main bearing-less rotor blade to separate the composite blade from the main rotor. These four components interact in the way described to enable the blades of the helicopter to be detached during an emergency, thus increasing the stability of the aircraft during a hard landing and/or allowing for the use of an occupant ejection seat or parachute while the helicopter is still in flight.

The invention discloses a multi-rotor unmanned plane, and belongs to the technical field of an unmanned plane. The multi-rotor unmanned plane comprises a plane body, a plane arm, a motor, a rotor wing, and a foot stool; the plane arm is connected to the plane body, and the motor is installed on the plane arm; the rotor wing is connected to a rotary shaft of the motor, and the foot stool is arranged beneath the plane body; besides, a suspending rod is further arranged on the plane body, the upper end of the suspending rod is provided with a magnetic absorbing head; a suspending hook is further arranged on the suspending rod. In use, the multi-rotor unmanned plane can be absorbed and suspended on an iron object at a high place through the magnetic absorbing head on the suspending rod, or suspended on an electric wire in the air, branches and other objects through the suspending hook. The lifting force of the multi-rotor unmanned machine in a hanging state is not provided by power energy of the battery, thus the working time of an onboard working device can be prolonged greatly in a rising and landing process. The multi-rotor unmanned plane can be widely applied to overhead monitoring at a fixed point, monitoring, live telecast, environmental protection monitoring, case detection, urban administration, courtyard safeguard, vehicle anti-theft, express delivery, and other domains.

Provided is a six-rotor-wing agricultural plant protection unmanned aerial vehicle with propellers distributed in a cambered mode. An inner co-pole reversing-propeller part and an outer co-pole reversing-propeller part are formed by two pairs of rotor wings, the four rotor wings are distributed in a cambered mode and in mirror symmetry, and the rotating axes of the rotor wings are coplanar; a co-shaft reversing-propeller part is composed of a pair of rotor wings; a six-rotor-wing unmanned aerial vehicle structure with the left and right sides being in mirror symmetry and the front and rear sides being asymmetrical is formed through several carbon fiber pipes and connecting and fixing components, and rods are perpendicular to shafts; the direction of downwash airflow is regarded as the outward normal direction of cambered surfaces. Compared with a six-rotor-wing unmanned aerial vehicle with propellers distributed on a plane and arranged in a central symmetry structure in the market, the flow speed of the downwash airflow is effectively reduced, the area of the downwash airflow is enlarged, crops are protected, and operation efficiency is improved.

The invention discloses a multi-rotor aircraft with an electric wire supplying power and application of the multi-rotor aircraft, belongs to the technical field of aviation, and particularly relates to a combined-type aircraft. The combined-type aircraft comprises a fixed wing aircraft, the multi-rotor aircraft and a ground power supply device; the structure of the fixed wing aircraft is similar to that of a regular fixed wing aircraft, and the fixed wing aircraft is further provided with a connecting end; the multi-rotor aircraft comprises a machine body, a connecting device, a radar detecting device and a power supply distributor; the ground power supply device comprises a controller, an electric wire collecting and putting implement and the electric wire; one end of the electric wire is fixedly connected to the power supply distributor, the other end of the electric wire is connected to a power source and is twined on the electric wire collecting and putting implement, and the electric wire transmits power supply for the multi-rotor aircraft; the multi-rotor aircraft flies in the sky with the electric wire, and the connecting device joints the connecting end so as to make the multi-rotor aircraft and the fixed wing aircraft connected and combined to load or carry the fixed wing aircraft. According to the multi-rotor aircraft with the electric wire supplying power and the application of the multi-rotor aircraft, the power source is provided for the multi-rotor aircraft through the electric wire, the combination of the multi-rotor aircraft and the fixed wing aircraft is utilized, and a new scheme is provided for the taking off and landing of the fixed wing aircraft.

The invention discloses a helicopter rotor system with a flexible beam structure. The helicopter rotor system comprises a blade (1), and further comprises a shimmy torsion beam device (5) and a swing torsion beam device (7). The swing torsion beam device (7) is fixedly connected with the shimmy torsion beam device (5) through side plates (6). The swing torsion beam device (7) is rotatably connected with the blade (1) through a socket device. The helicopter rotor system has the advantages of being simple in structure and the like, the swing, shimmy and torsion and coupling effects of the swing, shimmy and torsion can by fully used, and the dynamic characteristics of the helicopter rotor system are greatly improved. Meanwhile, the helicopter rotor system has the characteristic of high adaptability, and is suitable for rotor structures of various helicopters, such as inarticulate helicopters.

The present invention relates to a balancing body (1) for fastening to a ring (4, 5) of a continuous blade arrangement of a compressor or turbine stage of a gas turbine, wherein the balancing body has a first stop (11) for the form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder (6; 7) of the ring.

The invention discloses a six-shaft rotating device of an aircraft. The six-shaft rotating device comprises a fixing disk, connecting columns and rotating seats, wherein a wind guiding plate is arranged on the surface of the fixing disk; six fixing seats are connected to the side surface of the fixing disk; one end of each connecting column is integrally hinged to the corresponding fixing disk through a corresponding hinge; a plurality of hydraulic rods are connected to the side surface of the fixing disk; each hydraulic rod is integrally hinged to the corresponding fixing disk through a corresponding hinge joint; the other end of the corresponding connecting column is integrally connected with the corresponding rotating seat; a motor seat is arranged in each rotating seat; a micro motor is mounted in each motor seat; a rotating shaft is connected to an output shaft of each micro motor; a clamping disk is mounted on the side surface of the top end of each rotating shaft; rotating blades are arranged in each clamping disk; a plurality of blade grooves are respectively formed in the surfaces of the rotating seats; and an adjusting screw is connected to the bottom end of each motor seat. According to the six-shaft rotating device disclosed by the invention, a relative angle between the rotating seats can be adjusted, so that balance among different flying angles is realized; and when the six-shaft rotating device is not used, the six-shaft rotating device is convenient to retract, not liable to damage, long in service life and worth popularizing.

A lock apparatus securing a blade to a hub, the lock apparatus comprising a planar element having a spring actuable between an expanded position and a compressed position without deviation from the plane of the element, wherein in the expanded position of the spring the planar element is partly located in a slot provided in the blade, the spring being compressible to its compressed position to disengage the planar element from the slot.

The invention discloses an aircraft fuselage assembly and the aircraft. The fuselage assembly comprises a fuselage, a plurality of vehicle arms and a plurality of supporting arms. The multiple vehiclearms are distributed in the circumferential direction of the vehicle body, each vehicle arm comprises a first arm section and a second arm section, one end of each first arm section is connected withthe vehicle body and fixed relative to the vehicle body, the other end of each first arm section is rotatably connected with the corresponding second arm section, the number of the supporting arms isthe same as that of the vehicle arms, and the supporting arms correspond to the vehicle arms in a one-to-one mode, and each supporting arm is adjacent to the corresponding vehicle arm. One end of each supporting arm is rotatably connected with the vehicle body, the other end of each supporting arm is detachably connected with the second arm section, when the vehicle arms are in the unfolded state, the second arm sections are located on the axial sides of the first arm sections, the second arm sections are connected with the corresponding supporting arms, and when the vehicle arms are in the folded state, the second arm sections are separated from the corresponding supporting arms. The second arm section is located on the radial side of the first arm section. According to the fuselage assembly, the vehicle arms can be folded, and the folding structure is reliable.

The invention discloses a control method and device of an unmanned aerial vehicle system, the unmanned aerial vehicle system and a storage medium. The unmanned aerial vehicle system comprises an unmanned aerial vehicle and a parachute installed on the unmanned aerial vehicle, and the unmanned aerial vehicle comprises propellers used for providing flight power; the control method comprises the steps of obtaining a propeller locking instruction of the unmanned aerial vehicle; in response to the propeller locking instruction, controlling the propeller to stop and lock the propeller; and opening the parachute. According to the technical scheme provided by the embodiment, the propeller locking instruction of the unmanned aerial vehicle is obtained, the propeller is controlled to stop and locked based on the propeller locking instruction, and then the parachute is opened, so that the purpose that the parachute is opened after the unmanned aerial vehicle controls the propeller to stop and locks the propeller is effectively achieved; in this way, the situation that a propeller on the unmanned aerial vehicle and a parachute cord on the parachute are wound is effectively avoided, the protection effect of the parachute on the unmanned aerial vehicle can be guaranteed, and the safety and reliability of operation of an unmanned aerial vehicle system are guaranteed.

The invention discloses an aircraft and a control method of the aircraft, the aircraft comprises a fuselage, a first rotor mechanism and a second rotor mechanism, the first rotor mechanism is connected to the fuselage through a first connecting mechanism, the second rotor mechanism is connected to the fuselage through a second connecting mechanism, and the first rotor mechanism and the second rotor mechanism are spaced and arranged diagonally. The control method of the aircraft comprises the steps that the rotating speeds of the first propeller and the second propeller are controlled to be the same, and the first rotor wing mechanism and the second rotor wing mechanism incline towards the flight direction of the aircraft or the axial directions of the first propeller and the second propeller are parallel to the gravity direction. The aircraft adopts a diagonal asymmetric two-rotor layout, so that the effects of higher efficiency, large rotor size, high cruising ability and no need of changing a propeller pitch and a variable pitch mechanism are realized, and the aircraft has the advantages of simple structure, higher reliability and the like. Flight actions can move independently, decoupling between executing mechanisms is achieved, the aircraft is easy to control, and the difficulty of flight control program writing is reduced.

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an electric power inspection unmanned aerial vehicle image acquisition and recognition device which comprises an unmanned aerial vehicle body, a fixed partition plate, a plugging mechanism, a traction mechanism, a replacement assembly, an electric push rod and a storage battery pack. The fixing partition plate divides the interior of the unmanned aerial vehicle body into a first cavity and a second cavity, the plugging mechanism is arranged in the second cavity, the two ends of the traction mechanism are fixedly connected with the plugging mechanism, the replacement assembly is fixedly connected with one side of the image acquisition assembly, and the output end of the electric push rod is fixedly connected with one side of the image acquisition assembly. The storage battery pack is electrically connected with the traction mechanism through the replacement assembly. According to the unmanned aerial vehicle, the image acquisition assembly can be stored in the unmanned aerial vehicle body after the unmanned aerial vehicle body executes a task, and external dust can be prevented from being attached to the outer surface of the image acquisition assembly in combination with the effect of the blocking assembly.

The invention discloses a single-wing self-rotating landing device which can enable blades to generate lifting force through rotation in the falling process of a load thrown from the air, so that thefalling speed is decreased, and the load falls to the ground safely. The single-wing self-rotating landing device comprises a storage box, a leading edge balance weight and blades. According to actualengineering application conditions, an effective load needing to be decelerated can be placed in the storage box to be jointly regarded as a wing root balance weight, and the mass and the position ofthe front edge balance weight and the size and the shape of the blades are reasonably arranged respectively to achieve overall normal operation. The device is specially designed for air-drop objectsand air-drop loads with special requirements. The principle of the device is similar to that of maple seeds in the nature. The blades are pushed by air during falling, so that the whole device rotatesto generate lifting force and slow down the falling speed; and the device has the characteristics of simple structure, effectiveness and reliability.

The embodiment of the invention provides a four-rotor aircraft convergence control method, device and system and four-rotor aircrafts. The method comprises the steps that the position state information of all the four-rotor aircrafts in a second four-rotor aircraft set is received; and the thrust of four engines of a first four-rotor aircraft is determined according to the preset relational information of the thrust and the ground reactive force of the four engines of the first four-rotor aircraft and the position state information of the first four-rotor aircraft, and the position state information of all the four-rotor aircrafts in the second four-rotor aircraft set, so that the first four-rotor aircraft tends to the first space position range corresponding to the second four-rotor aircraft set. By the adoption of the four-rotor aircraft convergence control method, device and system and the four-rotor aircrafts, the purpose that the first four-rotor aircraft tends to each four-rotor aircraft in the second four-rotor aircraft set can be achieved.

The invention relates to the technical field of unmanned aerial vehicle seeding, in particular to an unmanned aerial vehicle with a spiral feeding and seeding mechanism and a using method thereof.The unmanned aerial vehicle comprises an unmanned aerial vehicle body, connecting arms are symmetrically arranged at the left end and the right end of the unmanned aerial vehicle body front and back, and wings are arranged at the ends, away from the unmanned aerial vehicle body, of the four connecting arms; supports are fixedly connected to the four corners of the bottom of the unmanned aerial vehicle body, a bearing plate is horizontally and fixedly connected to the middle positions of the four supports, a through hole is formed in the center of the bearing plate, a storage mechanism is fixedly connected to the upper surface of the bearing plate, and a discharging mechanism is fixedly connected to the lower surface of the bearing plate; the invention has the following beneficial effects: the device is small in size and convenient to transport and carry, is not affected by ground hardness, effectively solves the problem of sowing through agricultural machinery such as a sowing machine and the like in the prior art, and has a better use effect.

The invention discloses a ducted aircraft. The aircraft comprises an aircraft body, an undercarriage movably installed on the outer side of the aircraft body, an oil tank, an engine arranged on the aircraft body, a three-blade propeller fixedly connected to the output end of the engine, and four sets of steering engine installation positions arranged on the aircraft body in a penetrating mode. The movable control surface structures are fixedly mounted on the corresponding steering engine mounting positions; and the bonding sheets are bonded and fixed on the aircraft body through carbon cloth. The machine body comprises a shell, a laminate reinforcing ring fixedly installed at the top of the shell and reverse twisting blades fixedly installed in the shell. And the shell and the laminate reinforcing ring are combined to form an arc-shaped barrel-shaped structure. And the oil tank is embedded and fixed in the inner side of the laminate reinforcing ring. The aircraft has the advantages of being relatively small in size, large in effective load, high in cruising ability, high in integration degree, free of folding transportation and convenient to use, and the popularization prospect is excellent.