CAJ | 학술논문

针对火箭弹卷弧尾翼在特定气动载荷下的轻量化问题，基于结构动力学理论，依托ABAQUS非线性有限元软件，建立了火箭弹卷弧尾翼的有限元模型。通过对比碳纤维复合材料（CFRP）和合金钢材料的卷弧尾翼的有限元分析，得出了碳纤维复合材料在满足强度和刚度的要求下，使卷弧尾翼减重达80%。该方法为火箭弹卷弧尾翼的轻量化设计提供了一种参考和借鉴。
침대화전탄권호미익재특정기동재하하적경양화문제，기우결구동역학이론，의탁ABAQUS비선성유한원연건，건립료화전탄권호미익적유한원모형。통과대비탄섬유복합재료（CFRP）화합금강재료적권호미익적유한원분석，득출료탄섬유복합재료재만족강도화강도적요구하，사권호미익감중체80%。해방법위화전탄권호미익적경양화설계제공료일충삼고화차감。
Based on the structural dynamics theory and the nonlinear finite element software ABAQUS,the finite element model is built to deal with the lightweight problem of wrap-around fins subjected under special aerodynamic loads. Compared with alloy steel through finite element analysis,the simulation results showed that with the mass of the Wrap-around Fins of the rocket decreasing 80%,the stiffness and structural can meet the design requirements by Carbon Fiber Reinforced Plastics(CFRP).The method can provide references for lightweight design of wrap-around fins of the rocket.