【作者】 李阳；

【导师】 王亚斌；

【作者基本信息】 北京理工大学 ， 兵器工程（专业学位）， 2018， 硕士

【摘要】 滑翔增程技术是一种目前增程效果较好的增程技术。本论文以某滑翔增程弹为研究对象,针对该滑翔增程弹的空气动力特性进行研究,具体工作如下:在滑翔增程弹的研究和外形初步设计阶段,需要一种能够快速预估弹药气动力特性的方法。解决这个问题的最佳选择为工程计算。本论文采用细长体理论、线性理论Van Driest平板理论和经验公式等思想结合起来,建立了计算滑翔增程弹的空气动力特性工程算法,该工程算法可以分别计算弹身、弹翼、尾舵以及“弹身+弹翼+尾舵”组合体等大展弦比弹体的升力系数和阻力系数。将滑翔增程弹分解成各个部件,然后对各个部件的空气动力分别进行计算,并考虑各部件之间的相互干扰从而给出弹药武器的总体气动力参数。该方法适用的攻角范围0°～10°和马赫数Ma=0～3.0。该工程计算方法所得结果与气动仿真结果进行对比,本文所使用的方法误差为10%以内,满足工程需要。建立该滑翔增程弹气动模型,通过ICEM软件进行前处理,导入Fluent软件进行数值仿真。研究滑翔增程弹在马赫数Ma=0.4～3.0,攻角范围2°～10°条件下进行气动仿真,得到滑翔增程弹的阻力系数、升力系数、俯仰力矩系数及弹药周围的压力、温度和速度分布云图。获得该滑翔增程弹在不同条件下的气动参数随马赫数和攻角的变化规律。进行有翼弹和无翼弹的气动参数的对比。分析了滑翔增程弹的工作原理和弹道特点,该弹药以最大升阻比为条件进行滑翔增程,并给出最大升阻比下的攻角和马赫数关系。更多还原

【Abstract】 The gliding flight of projectile is an efficient extended range technique.Glide Range Extended Projectile(GREP)were studied in this dissertation centering on several characteristics calculation for GREP research.Details are as follow:During the period of researching the GREP aerodynamic configuration design,an approximate method which can predict GREP aerodynamic in a short time is demanded.This paper compiles several calculation of the aerodynamics of each of parts mainly use the approximate method such as slender body theory,linearized flow theory,and empirical methods to get the aerodynamics of GREP.The aerodynamic characteristic model of GREP is built by parts combination,calculated the aerodynamic characteristics for the projectile,wing and rudder.It can calculate the lift coefficient,drag coefficient.When calculating the aerodynamics of a combination of GREP configuration,we break it down to the parts which constitute it and get their aerodynamics respectively with method corresponding to each of them and at last take the interference between each of them into account so as to get the total aerodynamics.This method can be used during the angle of attack is 2 degrees and10 degrees and Mach number 0.4～3.0.The result of the above methods,and the result is compared with mathematical simulation data so as to verify its practicability.The compare shows that the errors of the result about 10%.The 3D model of GREP was established,ICEM software was used to establish the calculation flow field and the grid division,Using the Fluent to simulation calculation the flow field.In the calculation of the under the calculation condition,The aerodynamic parameters of GREP,as well as the distribution of ambient pressure,temperature and Mach number are got by aerodynamic simulation through Ansys-Fluent,which provide messages for optimization of aerodynamic configuration how the resistance,lift,drag coefficient,lift coefficient,lift-to-drag ratio and pitching moment coefficient.According to the simulation results and analysis variation of GREP aerodynamic parameters change with different Match numbers and angles of attack.There are several differences about aerodynamic configuration between projectile with wing or without wing.The working principle of GREP and ballistic characteristics are analyzed.The gliding extendable projectile is glide extended with the maximum lift-drag ratio as the condition,and the relationship between the angle of attack and the Mach number under the maximum lift-drag ratio is given.更多还原