飞机缝翼疲劳试验随动角度误差的分析优化方法
By constructing a kinematic model and analyzing experimental data to optimize the angle error in aircraft slat fatigue tests, the problem of long time consumption and large workload in angle error optimization in existing technologies has been solved, and efficient and accurate follow-up loading control has been achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CHINA AIRPLANT STRENGTH RES INST
- Filing Date
- 2025-10-30
- Publication Date
- 2026-07-17
AI Technical Summary
In existing aircraft slat fatigue tests, the optimization of the angle error of the follow-up loading system is time-consuming, labor-intensive, and lacks specificity, resulting in low efficiency.
By acquiring data from the drive system, the servo frame displacement system, the frame tilt sensor, and the slat surface tilt sensor, a kinematic model is constructed to optimize the angle error of the servo loading system. The angle error is used as a criterion for real-time tracking and optimization. Combined with experimental data analysis methods, the synchronization and initial state of the servo system are optimized.
This improved the accuracy and efficiency of the servo loading system, reduced testing costs and time, and achieved higher-precision angle error optimization to meet testing requirements.
Smart Images
Figure CN121516262B_ABST