火箭弹卷弧尾翼的轻量化研究

Lightweight Research of Wrap-around Fins of Rocket

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。

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.