面向装配变形应力协同控制的飞机刚柔混合结构多层级分析方法
By performing a rigid-flexible hybrid hierarchical modeling of the aircraft assembly structure, the problem of geometric nonlinear characteristics of locally weakly rigid parts in the assembly was solved, achieving high-precision static response prediction and damage early warning, and improving the fatigue strength and analysis efficiency of the aircraft assembly structure.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
- Filing Date
- 2025-07-31
- Publication Date
- 2026-07-17
AI Technical Summary
Existing technologies for deformation stress analysis of aircraft assembly structures neglect the geometric nonlinear characteristics of locally weakly rigid parts in the assembly, resulting in low accuracy in static response prediction. Furthermore, existing modeling strategies cannot effectively handle efficient analysis and damage warning for complex structures.
A multi-level analysis method for aircraft rigid-flexible hybrid structures, oriented towards the coordinated control of assembly deformation stress, is adopted. The airframe parts are classified into rigid frames and weakly rigid thin-walled parts, and finite element models are established for each. A mapping model is established through linear and nonlinear response analysis. Combined with connection constraint relationships, the clamp holding force is optimized to achieve stress balance and deformation control.
It improves the accuracy of static response prediction for assemblies, achieves efficient stress distribution equalization and damage early warning, enhances the fatigue strength and analysis efficiency of aircraft assembly structures, and has stronger scalability and applicability.
Smart Images
Figure CN120893252B_ABST