高超声速火箭弹舵翼气动热烧蚀预测

Research on Aerodynamic Thermal Ablation Prediction of Hypersonic Rocket Projectile

使用有限元方法对某型号高超声速火箭弹舵翼真实飞行工况进行气动热仿真,结合动网格和生死单元法进行舵翼烧蚀过程仿真,通过编写数据映射程序实现流体场与固体场之间的数据映射。计算了采用D6AC钢作为舵翼主要材料时,舵翼的烧蚀过程和最终烧蚀形貌。仿真结果表明D6AC钢舵翼的前缘区域被烧蚀,中后部区域基本完整。通过对比电弧加热风洞试验结果可知,仿真烧蚀结果的误差在工程应用允许误差范围内,未来可使用此方法预测不同材料舵翼的动态烧蚀过程与烧蚀区域。

The ablation of the rudder was obtained by combining dynamic grid and birth-death element method. By compiling data mapper,it can implement data mapping between fluid and solid. By using this method,the ablation process and the ablation morphology of the D6 AC rudder were calculated. The results of simulation and experiment showed that the front edge of D6 AC rudder was ablated while the middle and rear regions remain intact. The experimental verification was carried out in the arc heating wind tunnel to simulate the aerodynamic heat environment of the rudder. Finally,by comparing the experimental and simulation results,it can be seem that the error of the simulation result is within the allowed error range in engineering application. In the future,this simulation method can be used to obtain the dynamic ablation process and the ablation area of the rudder with different materials