导弹气动特性工程计算通用程序设计与研究  

Design and Study on the General Program of Missile Aerodynamic Characteristics Engineering Calculation

作　　者：程养民[1] 

机构地区：[1]中国航天工业总公司四院四十一所

出　　处：《固体火箭技术》1999年第2期1-7,共7页Journal of Solid Rocket Technology

摘　　要：以三级以下弹箭常见的气动外形为计算模型，编制了气动特性工程计算通用程序（ＡＤＭ系统），该软件适用于计算马赫数０～１０、飞行攻角０～３０°范围内多种火箭和导弹的气动参数。利用风洞实验数据详细检验了计算误差，除跨音速段外，升力、阻力系数计算误差分别小于３％和３．５％，压心系数误差小于１％。经过防雹火箭和探空火箭使用验证，该程序用于火箭设计是可靠的。The general program of aerodynamic characteristics engineering calculation (ADM system) is compiled by using the common aerodynamic configuration of the rocket or missile with less than three stages as a calculation model, it is suitable for calculating aerodynamic parameters of different types of rocket and missile which flight at 0～10 Ma with an attack angle of 0～30°. The calculated results are checked by the wind tunnel experiment. It is obtained that the calculated errors of the lift coefficient and the drag coefficient are less than 3%, 3.5% respecttively, and the pressure center coefficient error is less than 1% except for the transonic region. The program is verified to be reliable to rocket design through tests of antihail rocket and sounding rocket.

关 键 词：导弹 气动特性 气动力计算 火箭弹 程序 

分 类 号：TJ760.11[兵器科学与技术—武器系统与运用工程]