A rotary aircraft

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

Application Number
CN202311084835.5
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2023-08-28
Publication Date
2026-07-07
Estimated Expiration
2043-08-28

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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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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Citation Information

Patent Citations

  • Active systems and methods for controlling an airfoil vortex

    CN101134504A

  • Pneumatic gurney flap based on plasma wall surface jet flow

    CN102756803A

  • A drag reduction method for hypersonic vehicles based on the leading edge shock attenuation of synthetic jet wings

    CN109250074A

  • Wingtip device for an aircraft

    US20220024564A1