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| Mold Stiffness Optimization for Large-Scale Aircraft Composite Fuselage Panel |
| PENG Weibo1, NIE Jun1, LI Kelang1, Huang Bo1, XIE Zhenqing1, CAI Wenkan2 |
1. Hunan Feiyu Aviation Equipment Co., Ltd., Changsha 410205, China;
2. Shanghai Aircraft Manufacturing Co., Ltd., Shanghai 201324, China |
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Abstract Aircraft composite fuselage panel mold firmed on the horizontal automatic fiber placement (AFP) is tudied based on the theoretical mechanics. It proves that the mold weight and section inertia moment are the dominating actors influencing mold stiffness. Firstly, frame unit is constructed by topology optimization. Then, an industrialized base esign proposal is constructed according to the load transmission path among frame unites and steel structure points design rinciple. Three influencing factors which are mold profile, shaped ribs and frame unit numbers are selected based on base esign proposal, and an orthogonal experimental design and simulation analysis for these influencing factors is finished. nalysis results point out that it will realize the performance balance between the mold lightweight and stiffness when ecrease the frame unit numbers and optimize the thickness of mold profile and shaped ribs.
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2022, 
