The embodiment of the invention discloses a hybrid electric control rotor wing, relates to the technical field of helicopter control, and can reduce the limitation degree of volume and weight on an actuator in the electric control rotor wing and improve the safety redundancy degree of the electric control rotor wing at the same time. The method has the advantages that an automatic inclinator and a mechanical/hydraulic operating lever system are not used any more, the size and weight of the actuator and related mechanisms can be reduced, and therefore the limitation degree of the size and weight to the actuator in the electric control rotor wing is reduced; the two different rotor control technologies are used at the same time, independent control over the total pitch and the periodic variable pitch of the rotor is achieved, the requirement for an actuator is lowered, implementation is easier, under the special condition, control over the rotor can be achieved through any one control technology, rotor control has multiple redundancy, and the control efficiency is improved. Therefore, the safety redundancy degree of the electric control rotor wing is improved.
本发明实施例公开了一种混合式电控旋翼,涉及直升机操控技术领域,能够降低电控旋翼中作动器受到体积和重量限制程度,并还同时提升电控旋翼的安全冗余程度。本发明包括:不再使用自动倾斜器、机械/液压操纵杆系,可以减轻作动器以及相关机构的体积和重量,从而降低电控旋翼中作动器受到体积和重量限制程度;同时使用两种不同的旋翼操纵技术,实现旋翼总距和周期变距的独立操纵控制,不仅对作动器的要求降低,更容易实现,在特殊情况下,可依靠其中任意一种操纵技术实现旋翼的控制,使得旋翼操纵具有多重冗余度,从而提升电控旋翼的安全冗余程度。
Hybrid electric control rotor wing
一种混合式电控旋翼
2024-05-07
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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