9 results about "Rotary wing" patented technology

The respective motors of the drone (10) can be controlled to rotate at different speeds in order to pilot the drone both in attitude and speed. A remote control appliance produces a command to turn along a curvilinear path, this command comprising a left or right turning direction parameter and a parameter that defines the radius of curvature of the turn. The drone receives said command and acquires instantaneous measurements of linear velocity components, of angles of inclination, and of angular speeds of the drone. On the basis of the received command and the acquired measurements, setpoint values are generated for a control loop for controlling motors of the drone, these setpoint values controlling horizontal linear speed and inclination of the drone relative to a frame of reference associated with the ground so as to cause the drone to follow curvilinear path (C) at predetermined tangential speed (u).

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.

The invention provides a four-shaft rotary-wing aircraft. A power device of the four-shaft rotary-wing aircraft is four symmetrically-distributed cycloidal propellers, and each cycloidal propeller isdriven by a separate motor. The rotation direction of the four cycloidal propellers is shown in the figure, and the center of gravity of the four-shaft rotary-wing aircraft is located in the same horizontal plane as the center of the four cycloidal propellers. The four-shaft rotary-wing aircraft a novel aircraft which can vertically take-off and landing and fly forward at a high speed, in addition, the four-shaft rotary-wing aircraft further has the characteristics of high efficiency, high mobility, low noise and so on.

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 invention relates to a method for piloting a rotary wing drone, the method being implemented by an electronic apparatus for piloting the drone, the drone being configured to have an on board camera. The method comprises calculating different types of navigation setpoint(s) of the drone, based on different types of piloting instructions for the movement of the drone, a type of piloting instruction being capable of modifying at least an attitude angle of the drone and/or the movement speed of the drone, each type of piloting instruction respectively being associated with a type of navigation setpoints, the calculation comprising, for at least one type of piloting instructions: determining the sighting axis of the camera; obtaining at least one navigation setpoint associated with at least one type of piloting instructions based on the sighting axis of the camera.

The invention discloses a novel tilting-wing hybrid search and rescue unmanned aerial vehicle, and belongs to the technical field of maritime unmanned aerial vehicle search and rescue. The novel tilting-wing hybrid search and rescue unmanned aerial vehicle aims to solve the problems of short cruising time, small acting radius, poor load capacity and single working form of a maritime search and rescue unmanned aerial vehicle in the prior art. The novel unmanned aerial vehicle comprises a stabilizing machine frame, four rotor wing tilting mechanisms, a rescue throwing mechanism, a plurality of self-unfolding type life rings, a control unit and a power conversion and energy supply structure; the four rotor wing tilting mechanisms are symmetrically arranged at the upper end of the stabilizingmachine frame; the rescue throwing mechanism is arranged on the stabilizing machine frame, the rescue throwing mechanism at least comprises a storage bin connected to the stabilizing machine frame, and the storage bin is of a cube structure with the lower end capable of being opened and closed; the plurality of self-unfolding type life rings are arranged in a plurality of accommodating lattices ofa bin body of the rescue throwing mechanism; the control unit is arranged on the stabilizing machine frame, and the control unit at least comprises a battery and a controller; and the power conversion and energy supply structure is arranged on the stabilizing machine frame through a damping structure, the power conversion and energy supply structure is in electric connection with the battery, andthe power conversion and energy supply structure is connected with the rotary wing tilting mechanisms to supply power.

The invention discloses a rotary wing type water meter which comprises a meter shell (1) and a meter core (2), wherein a cup-shaped meter core base is arranged inside the bottom of the meter shell (1); a water inlet (5) and a water outlet (6) are respectively formed on two sides of the meter core base; an O-shaped slot (4) is encircled and arranged inside the meter core base; the O-shaped slot (4) is arranged above the water inlet (5) and under the water outlet (6); and an O-shaped sealing gasket (3) which is matched with the meter core base is arranged outside the meter core. The rotary wing type water meter is simple, reasonable and compact in structure, overcomes the defects of the prior art and has the advantages of high working efficiency, convenience in mounting and maintaining and stable product quality.