一种带锁定功能的无人机侧翼展开驱动机构
By integrating a locking function module and a parallel structure of two torsion springs into the wing deployment drive mechanism of the UAV, the problem of increased aerodynamic drag caused by excessive space occupation of the wing deployment drive mechanism is solved, realizing efficient deployment and locking of the UAV, and improving the lift-to-drag ratio and endurance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
- Filing Date
- 2025-10-10
- Publication Date
- 2026-07-17
AI Technical Summary
The wing deployment drive mechanism of large-wingspan lifting body UAVs occupies too much space, which increases aerodynamic drag, reduces lift-to-drag ratio, and limits endurance.
Design a side wing deployment drive mechanism for a UAV with locking function. By integrating a locking function module into the deployment function module, the rotational deployment of the side wing and the position locking after deployment are realized. A double torsion spring parallel structure is adopted to improve the output torque and realize the locking function in a limited space.
The deployment and locking of the wing were achieved within a limited space, reducing aerodynamic drag, increasing lift-to-drag ratio, extending flight time, and improving the reliability of the locking function.
Smart Images
Figure CN121573231B_ABST