SC型双翼末敏弹尾翼结构方案设计

为寻求SC型双翼末敏弹实现稳态扫描的最佳气动外形,运用计算流体力学方法建立了SC型末敏弹的气动特性仿真模型,基于正交试验法对SC型尾翼末敏弹的翼片结构参数进行了优化设计。分析了尾翼面积、弯折角对SC型末敏弹气动特性的影响规律,得到了尾翼参数对双翼末敏弹阻力系数和极转动力矩系数影响的主次关系。在此基础上分析得到一种可以同时满足大阻力系数和大极转动力矩系数的末敏弹气动外形结构。优化结果显示,优化模型阻力系数较优化前增加5.14%,极转动力矩系数增加4.53%,高塔试验表明优化模型双翼末敏弹能在下落过程中保持稳定。研究方法和结果可为双翼末敏弹的气动布局和优化设计提供参考。

Optimum Design on Aerodynamic Configuration of Terminal Sensitive Projectile With S C Style Wings

To seek the best aerodynamic shape of terminal sensitive projectile(TSP) with S C style wings for steady scanning,the simulation model of TSP was established by using computational fluid dynamics.The wings parameters were optimally designed based on orthogonal tests.The law of wing area and wing bent angle affecting the aerodynamic characteristics of TSP with S C style wings was analyzed.The primary relation of wing parameters affecting the drag coefficient and torque coefficient was obtained.An aerodynamic shape was obtained,which can meet large biggest drag coefficient and torque coefficient.Results show that drag coefficient of optimized model increases by 5.14% than that of the initial model,and the torque coefficient increases by 4.53%.Tower tests show that the optimized model stays steady when it falls.Research methods and results can offer help for optimum design of the double wings TSP.