基于姿态角和过载反馈的面对称飞行器在线主动滚动减载方法
By using an online active rolling load reduction method based on attitude angle and overload feedback, the control force and aerodynamic force matching of a symmetrical aircraft are optimized, which solves the problem of asymmetric control force and load under wind field deviation and improves wind field adaptability and maneuverability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING INST OF ASTRONAUTICAL SYST ENG
- Filing Date
- 2025-09-29
- Publication Date
- 2026-07-17
AI Technical Summary
When a symmetrical aircraft is subjected to wind field deviations, the control force and load-bearing capacity are asymmetrical, resulting in insufficient control force or load exceeding the load-bearing capacity, which affects the aircraft's wind field adaptability and launch release probability.
By using an online active roll load reduction method based on attitude angle and overload feedback, the current attitude angle and overload information of the aircraft are obtained, the roll program angle and yaw angle commands are calculated, the matching of control force and aerodynamic force is optimized, and the aircraft attitude is actively adjusted to the dominant plane.
It improves the aircraft's maneuverability, reduces the aerodynamic and control requirements of the disadvantageous side, releases control margin, and enhances wind field adaptability.
Smart Images
Figure CN121325934B_ABST