A rotary aircraft

CN117262209BActive Publication Date: 2026-07-07BEIHANG UNIV +1
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
BEIHANG UNIV
Filing Date
2023-08-28
Publication Date
2026-07-07

AI Technical Summary

Technical Problem

Existing rotary aircraft suffer from control failure at high angles of attack, large machining errors in the slanted tail fins, resulting in a limited flight envelope, and insufficient research on aerodynamic characteristics.

Method used

Multiple vortex generators are arranged on the tail fin of the rotating aircraft. By adjusting the parameters and position of the vortex generators, a rolling torque parallel to the aircraft axis is generated, thereby controlling the direction and magnitude of the rolling torque. Real-time regulation is achieved using methods such as jets and plasmas.

Benefits of technology

It improves the aerodynamic and flight performance of rotating aircraft, expands the flight angle-of-attack envelope, and enhances stability and maneuverability, especially at high angles of attack.

✦ Generated by Eureka AI based on patent content.

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    Figure CN117262209B_ABST
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Abstract

The application discloses a rotary aircraft and relates to the technical field of aircraft design, and comprises an aircraft body and a plurality of tail wings which are uniformly arranged on the tail of the aircraft body in the circumferential direction; the trailing edge of the tail wing is provided with a stationary vortex generator; the stationary vortex generator is located on one side of the airfoil of the tail wing; and the stationary vortex generator can hinder the airflow of the airfoil to form a stationary vortex; the rotary aircraft designed based on the stationary vortex lift principle can be designed and controlled on the basis of the vertical tail wing; a plurality of stationary vortex generators are arranged along the tail wing of the rotary aircraft, so that a rolling moment parallel to the axis direction of the aircraft is generated; the direction and size of the vortex lift can be adjusted by adjusting the parameters and positions of the stationary vortex generators, so that the direction and size of the rolling moment can be controlled.
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