高空气动特性对远程弹箭弹道的影响研究  

Study on Ballistic Effect of Long-range Shells and Rockets by Aerodynamic Characteristics at High Altitude

作　　者：李臣明[1] 韩子鹏[2] 孔建国[1] 

机构地区：[1]解放军炮兵学院南京分院,江苏南京211132 [2]南京理工大学动力工程学院,江苏南京210094

出　　处：《系统仿真学报》2007年第5期990-992,共3页Journal of System Simulation

摘　　要：为了考察远程弹箭高空条件下的弹道特性,推导了远程火箭在高空稀薄气体中的阻力系数表达式,对阻力系数在稀薄大气中随马赫数与攻角的变化进行了计算分析。提出在高空弹道计算中应考虑稀薄大气的影响,把整个弹道分成稠密段、过渡段和稀薄段三部分,全弹道的阻力系数与各段对应使用。仿真结果表明,稀薄气体中的阻力系数比稠密大气中的大,采用复合阻力系数进行弹道计算比完全采用稠密大气中的阻力系数计算更符合实际。In order to study the ballistic characteristic of long-range shells and rockets at high altitude, the expression of drag coefficients of long balance range rocket in rarefied gas was deduced based on rarefied gas dynamics, and the calculating and analysis about aerodynamic characteristic along with March number and angle of attack were made. Meanwhile, an optimal method was proposed to deal with the drag coefficients in full ballistic, and the full height was divided into dense region, transitional region and rarefied region, and the drag coefficients is different in every region accordingly. The results show that the value of drag coefficients in rarefied gas is lager than that in dense gas as the Mach number and angle of attack are same. The ballistic calculating method using complex drag coefficients is better than that using the drag coefficients of dense gas only.

关 键 词：稀薄气体动力学 高空弹道 远程弹箭 分子运动论 

分 类 号：TJ714[兵器科学与技术—武器系统与运用工程]