一种扑旋翼飞行器
By designing a flapping rotorcraft, utilizing a power source to drive the wing to swing back and forth and optimizing the control surface structure, combined with a high-performance control unit, the instability problem of micro aircraft under wind field interference was solved, achieving stable flight in complex wind fields.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- WENZHOU UNIV
- Filing Date
- 2026-06-15
- Publication Date
- 2026-07-17
AI Technical Summary
Micro aircraft are unstable in flight under wind interference and are prone to tipping over, especially when wind speed changes drastically or wind direction is unstable, the control effectiveness of traditional control surface systems is significantly reduced.
It adopts a flapping rotor design, including wings, drive mechanism and control mechanism. The wings are driven to swing back and forth by a power source. Combined with control unit and servo motor, the structure and aerodynamic performance of the control surface are optimized to achieve the ability to adapt to changes in wind field. The high-performance flight control board and MPU9250 module are used for real-time attitude adjustment.
It improves the safety and reliability of aircraft under complex weather conditions, reduces the interference of wind fields on the aircraft's attitude, ensures stable flight under various wind speeds and directions, and enhances the stability of takeoff, landing, and flight.
Smart Images
Figure CN122402822A_ABST