Novel rotor wing electric folding and unfolding control system and method
A control system and control method technology, applied in the directions of rotorcraft, motor vehicles, aircraft, etc., can solve the problems of hydraulic oil leakage and combustion, slow response, heavy weight, etc., to avoid leakage and combustion, improve reliability, and reduce weight. Effect
Pending Publication Date: 2021-01-05
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology
[0002] The domestic helicopter rotor folding system mainly adopts hydraulic rotor folding, resulting in complex system design, large volume and heavy weight
At the same time, the control of the hydraulic folding system is complicated, the control accuracy is low, the maintainability and testability are poor, and there is no pure electric rotor folding system at present.
[0003] The hydraulic actuating mechanism has disadvantages such as heavy weight, slow response, and difficult maintenance, and the failure of hydraulic components is not easy to monitor and there are risks such as hydraulic oil leakage and combustion, which affects the safety of the aircraft
Method used
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Embodiment Construction
[0043] The embodiment of the present invention provides a new control system for electric folding and unfolding of the rotor, such as figure 1 As shown, the control system includes: a folding controller, a main propeller collector ring, a disc propeller controller, four folding actuators, five arm limit locks, and a disc propeller mechanism; There is an angular displacement sensor;
[0044] The folding controller is connected with the main propeller collector ring and disc propeller controller through CAN bus respectively, the main propeller collector ring is respectively connected with four folding actuators and five arm limit locks through CAN bus, and the disc propeller controller It is connected with the propeller mechanism through the CAN bus.
[0045] (1) The control system also includes: a folding power distribution box, a main propeller distributor, and a folding transformer rectifier;
[0046] Folding power distribution box, used to provide working power for main pr...
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The invention belongs to the technical field of helicopter rotor folding, and discloses a novel rotor electric folding and unfolding control system and method, and the control system comprises a folding controller, a main propeller collector ring, a disc propeller controller, four folding actuator cylinders, five support arm limiting locks, and a disc propeller mechanism. An angular displacement sensor is arranged in the main paddle collector ring; wherein the folding controller is respectively connected with the main paddle collector ring and the disc paddle controller through CAN buses, themain paddle collector ring is respectively connected with the four folding actuating cylinders and the five support arm stop locks through CAN buses, and the disc paddle controller is connected with the disc paddle mechanism through a CAN bus. A rotor wing electric folding mode is adopted, a rotor wing disc paddle, a locking mode and a paddle driving mode are all driven by a permanent magnet synchronous servo controller, and all actuators are controlled and monitored by an upper computer electromechanical management computer.
Description
technical field [0001] The invention belongs to the technical field of helicopter rotor folding, and in particular relates to a control system and method for electric folding and unfolding of a novel rotor. Background technique [0002] The domestic helicopter rotor folding system mainly adopts hydraulic rotor folding, resulting in complex system design, large volume and heavy weight. At the same time, the control of the hydraulic folding system is complicated, the control accuracy is low, and the maintainability and testability are poor. At present, there is no pure electric rotor folding system. [0003] The hydraulic actuating mechanism has the disadvantages of heavy weight, slow response and difficult maintenance, and the failure of hydraulic components is not easy to monitor and there are risks such as hydraulic oil leakage and combustion, which affects the safety of the aircraft. With the development of helicopter technology, the requirements for the helicopter rotor ...
Claims
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Login to View More IPC IPC(8): B64C27/52
CPCB64C27/52
Inventor 赖耀祖石文求汪智超谢定祥许国平齐从生孙青青
Owner CHINA HELICOPTER RES & DEV INST