一种高升力系统位置控制方法
By adding fine-tuning parameters and constructing a velocity control law in the high-lift system, the problem of insufficient position control accuracy in the high-lift system is solved, enabling precise airfoil angle adjustment and fault detection. This method is applicable to different load conditions and mechanical clearances, avoiding the shortcomings of traditional methods.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- QINGAN GROUP CO LTD
- Filing Date
- 2023-10-20
- Publication Date
- 2026-07-17
AI Technical Summary
Existing position control methods for high-lift systems suffer from insufficient accuracy, especially due to issues such as excessive contraction or expansion of the flap and slat angles under the influence of system inertia. Furthermore, traditional methods place high demands on the system's braking capacity, making them prone to malfunctions.
A high-lift system position control method is adopted. By adding fine-tuning to the ideal position control law, the speed and position control law is constructed using the ratio of the drive shaft stroke to the airfoil angle and the motion time. Combined with SIGN and MIN functions, precise control is achieved, which can adapt to different load conditions and mechanical clearances and avoid overtravel failures.
It improves the position control accuracy of the high-lift system, reduces the requirements for the system's braking capacity, avoids damage to the wing structure, and enables precise adjustment and fault detection of wing motion.
Smart Images
Figure CN117644970B_ABST