Positionable and retractable aircraft rotor mechanism

By designing a retractable and positionable aircraft rotor mechanism, and adopting a mechanical linkage structure of shaft, rotor, stator and cam, the problems of large structural space occupation and insufficient control precision in existing blade retraction and deployment technologies are solved, realizing efficient and safe blade retraction and deployment, which is suitable for distributed propulsion aircraft.

CN122126441APending Publication Date: 2026-06-02COMMERCIAL AIRCRAFT CORP OF CHINA LTD +1
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
COMMERCIAL AIRCRAFT CORP OF CHINA LTD
Filing Date
2026-04-29
Publication Date
2026-06-02

AI Technical Summary

Technical Problem

Existing propeller retraction and deployment technologies suffer from problems such as large structural space occupation and insufficient control precision and reliability, making it difficult to meet the requirements of efficient, safe, and controllable propeller retraction and deployment functions for distributed propulsion aircraft.

Method used

A retractable and positionable aircraft rotor mechanism was designed, which adopts a mechanical linkage structure of shaft, rotor, stator and cam. The precise positioning and retraction of the blades are achieved through the cooperation of cam and stator. The blade rotation is guided by slide rail and roller, and the aerodynamic shape is optimized by fairing.

Benefits of technology

It achieves high-precision and reliable blade deployment and retraction, reduces wind resistance, is suitable for dynamic environments during flight, has a compact structure and high integration, and meets the needs of distributed propulsion aircraft.

✦ Generated by Eureka AI based on patent content.

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Abstract

This invention provides a retractable aircraft rotor mechanism, comprising: multiple slide rails at the top of a rotating shaft; a rotor mounted on the rotating shaft and moving axially along the shaft, with blades rotatably connected to the sides of the rotor; a stator fixedly mounted on the outside of the rotor, with at least one positioning groove on the stator to restrict rotor rotation; a cam mounted on the rotating shaft, moving up and down along the shaft under external force and constrained by the stator; when the cam is in a first position, the rotor falls into the positioning groove of the stator, locking the rotor; when the cam is in a second position, the cam lifts the rotor, disengaging it from the positioning groove of the stator and engaging it with the rotating shaft, placing the rotor in its position and driving the blades to rotate along the slide rails to extend or retract. This invention employs an axial retraction design, facilitating blade retraction into the nacelle, and when retracted, it can conform to the shape of the outer shell to form a more aerodynamic shape, reducing drag.
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