旋成体弹丸气动力计算与气动外弹道优化设计
详细信息    本馆镜像全文|  推荐本文 |  |   获取CNKI官网全文
摘要
在弹箭设计的初级阶段和末期靶场试验中,都需要对弹箭的气动外弹道性能进行快速测算,对所设计弹箭进行快速选型或对其落点进行预先估算。为实现这两个目的,进行了弹箭气动力性能工程算法的研究与计算,并对某型号榴弹进行了气动力外弹道综合性能优化设计。
     在全弹道上飞行的轴对称旋成体弹丸,会以亚、跨、超音速等不同速度和不同姿态在相应海拔高度的气象条件下运动,为此采用部件组合法将弹丸拆分为前体(头部和圆柱部)和后体(尾部和底部),并分别在亚、跨、超音速下对各组成部件的气动力参数工程计算方法进行了深入研究,精选出了一整套可用于弹箭全弹道气动性能工程估算的方法；建立了5D弹道模型,并采用龙格-库塔法对微元方程组进行求解；完成理论分析后,采用模块化语言Fortran95将气动力计算和外弹道求解两部分内容程序化；应用所编制的程序对某型号榴弹进行计算,并与试验结果进行对比,通过各马赫数、攻角下气动参数的数据对比证明该程序的精度较好,完全满足精度要求；在此基础上,应用该程序对某型号榴弹进行了气动外弹道多目标综合优化设计,优化目标参数包括头部母线线形、长细比和初始弹重。
     通过优化设计,某型号榴弹增程率达到17.35%,效果明显。经验证,本程序可应用于0.0Ma～3.5Ma内的轴对称旋成体弹箭的气动外弹道计算,精度较好,能够用于弹箭设计初级阶段快速选型和靶场实验阶段快速预估弹丸落点。
In the initial stage and final range test of the design of Projectiles, it had to calculate the aerodynamics and ballistic performance of the projectiles rapidly to get the better shape or the droppoint of projectile. To achieve both of the purposes, we studied on research and calculation of algorithm and made a optimal design for certain type of grenade.
     Axisymmetric projectiles flying in the while trajectory moves in respective elevations meteorological conditions, with different speeds (for instance, subsonic, transonic or supersonic) and different angles. Thus we should consider the influence of weather conditions. We split the projectile into fore part (the head and Cylinder part) and after part (tail and base part) in component combination method, then we studied the Engineering Methods in different speeds of every part of the projectile, at last we picked out a selective series of methods to calculate the aerodynamics of projectiles. We built 5D ballistic model, and tried to solve that differential equations with runge-kutta method. After that theory analysis works, we developed that two parts into genneral progress in Fortran95 which could be applied to projectiles to predict lift, drag, pitching moment, and center of pressure over the Mach number range,0.0     In the optimal design, the range of a certain type of grenade increased to a significant 17.53%. This program was verified to be appliable to projectiles to accurately predict aerodynamics and ballistic performance over the Mach number range,0.0
引文
[1]周洪旭.精确制导武器的技术特点分析[J].科技风,2009年6月(下)：276-277
    [2]方松柏,音生译.导弹空气动力学的现状及展望.58-79
    [3]音生译.一种用于寻常的导弹空气动力预估的部件装配技术Missile DATCOM[J].译自AIAA-84-0388
    [4]苗瑞生,邱晓华.兵器发展对气动力的要求[J].兵工学报弹箭分册,1989,(4)：1-21
    [5]刘志洋.尾冀弹超音速下气动特性的计算与分析[D].南京：南京理工大学.2003
    [6]李中武,成水燕.基于N S方程的十字翼大攻角导弹绕流数值模拟[J].弹箭与制导学报,2009,29(2)：195-198
    [7]郭效芝,吴慧.带有进气道的导弹法向气动力工程估算[J].兵工自动化,2010，29(5)：7-9
    [8]张维全.超音速翼体干扰气动力特性与计算[J].弹箭与制导学报,1996：24-30
    [9]周岭,赵协和.吸气式导弹气动力预计方法研究[J].空气动报,2006,24(4)：491-494
    [10]袁伟,居贤铭.矩形截面弹体法向气动力计算方法[J].战术导弹技术,2003(3)：33-36
    [11]施志佳,张永刚.翼面亚音速非定常气动力的工程计算方法[J].弹道与制导学报,1994：34-40
    [12]颜大椿.实验流体力学[M].北京：国防工业出版社,1992
    [13]恽起麟.风洞试验[M].国防工业出版社,2000
    [14]挥起麟.实验空气动力学[M].北京：国防工业出版社,1991
    [15]于勇,张俊明,江连田.FLUENT入门与进阶教程[M].北京：北京理工大学出版社,2008
    [16]刘导治.计算流体力学基础[M].北京：北京航空航天大学出版社,1989
    [17]杨维维,陈小前,李晓斌,王振国.通用导弹气动力计算软件DATCOM的开发与校验[J].固体火箭技术,2006,29(3)：161-164
    [18]尚伟烈.滑翔增程弹气动力计算及分析[D].南京：南京理工大学.2003
    [19]钱翼稷编著.空气动力学[M].北京：北京航空航天大学出版社,2004,9
    [20]王中原,张卫平编著.外弹道设计理论与方法[M].北京：科学出版社,2004
    [21]韩子鹏等编著.弹箭外弹道学[M].北京：北京理工大学出版社等,2008
    [22]浦发编著.外弹道学[M].北京：国防工业出版社,1980,7
    [23]钱杏芳,林瑞雄,赵亚男编著.导弹飞行力学[M].北京：北京理工大学出版社,2011
    [24]陈士橹,吕学富编著.导弹飞行力学[M].北京：航空专业教材编审组,1983,12
    [25]魏惠之,朱鹤松,汪东辉,都兴良.弹丸设计理论[M].北京：国防工业出版社,1985
    [26]臧国才,李树常编著.弹箭空气动力学[M].北京：兵器工业出版社,1989,9
    [27]Van Driest,E,R.:"Terbulent Boundery Layer in Compressible Fluids". JAS.Vol.18,No 3,1951,pp.145-160,216
    [28]Frank G. Moore. Body alone aerodynamics of Guided and Unguided Projeetiles at Subsonic, Transonic,and Supersonic Mach numbers. AD 754098
    [29]丁则胜,陈少松,刘亚飞,曹顶贵.底排尾迹流场实验研究[J].弹道学报,1999年第一期第12卷：43-48
    [30]Love,E,S.:"Base Pressure at Supersonic Speeds on Two-Dimen-sional Airfoils and on Bodies of Revolution with and without Turbulent Boundary Layers",NACA TN 3819,1957
    [31]Cartright,E,M.,Jr.;Schroeder,A. H:"Investigation at Mach Number 1.91 of Side and Base Pressure Distributions Over Conical Boattials Without and With Jet Flow Issuing From Base",NACA RM E51F26,1951
    [32]Kurzweg,H,H.:"Interrelationship Between boundary Layer and Base pressure",JAS,No. 11,1951,pp.743-748
    [33]Crocco,L.;Lees,L.:"A Mixing Theory for the Interration Between Dissipative Flows and Nearly-Isentropic Streams",Report No.187,Princeton University,Aero. Engr. Lab;1952
    [34]Bureau of Naval Weapons:"Handbook of supersionc Streams",NAVWEPS Report 1488,Vol.3,1961
    [35]Reller,J. O.,Jr.;Hamaker,F. M:"An Experimental Investigation of the Base Pressure Characterristics of Nonlifting Bodies of Revolution at Mach Number from 2.73 to 4. 98", NACA,Vol.3,1961
    [36]Peck,R. F.:"Flight Measurements of Base Pressure on Bodies of Revolution with and without Simulated Rocket Chambers",NACA TN 372,1955
    [37]Fraenkel,L. E.:"A Note on the Estimation of the Base Pressure on Bodies of Revolution at Supersonic Speeds,"Royal aircraft Establishment Tn No. AERO 2203,1952
    [38]U. S. Army Missile Commend:Engineering Design Handbook:Design of Aerodynamically Stabilized Free Rockets,AMCP 706-280,1968
    [39]Stoney,W. E,Jr.:"Collection of Zero-Lift Data on Bodies of Revolution from Free-Flight Investigations",AS A TR R-100,1961
    [40]Kurzweg,H,H.:"New Experimental Investigations on Base Pressure in the NOLSupersonic Wind Tunnels at Mach Numbers 1.2 to 4.24",NOL Memo 10113,1950
    [41]Wu,J,M;Aoyoma,K.:"Transonic Flow-Field Calculation Around Ogive Cylinder by Nolinear-Linear Streching Method",U. S. Army Missile Command Technical Report No. RD-TR-70-12,April 1970. Also AIAA 8th Aerospace Sciences Meeting,AIAA Paper,70-189,Janyary 1970
    [42]谭俊杰.旋转弹丸纵向气动力的一种计算方法.内部资料,1988
    [43]王中原,臧国才.弹丸空气动力的一个计算方法[J].华东工学院学报,1987年第一期：61-65
    [44]Van Dyke, M. D.:"A Study of Second-Order Superdonic Flow Theory",NACA Report 1081,1952
    [45]Van Dyke, M. D.:"Frist and Second-Order Theory of Supersonic Flow Past Bldies of Revolution",JAS,Vol.18,No.3,March1951,pp.161-179
    [46]铫永兴,李彬.弹丸气动力特性计算方法[J].气动实验与测量控制,1990,4(4)：93-98
    [47]沈仲书,刘亚飞编著.弹丸空气动力学[M].北京：国防工业出版社,1984,12
    [48]张维全等.箭弹空气动力特性分析与计算[M].北京：国防工业出版社,1979
    [49]Allen,J. H.;Perkins,E. W.:"Characteristics of Flow Over Inclined Bodies of Revolution ",NACA RM A 50L07,1965
    [50]苗瑞生,居贤铭,吴甲生编著.导弹空气动力学[M].北京：国防工业出版社,2006,1
    [51]张德礼.求三角形、梯形等分面积形心至顶点距离(1m)的公式和线解图[J].邮电设计技术,1994年第8期：31-42
    [52]宋丕极,崔新军.旋转稳定炮弹降阶的刚体弹道方程及应用[J].兵工学报弹箭分册,1990年第四期：12-31
    [53]陈阳泉.一个新的旋转稳定弹弹道计算的刚体六自由度和五自山度模型[J].西安工业学院学报,1990年11月,第3、4期,第十卷：63-72
    [54]裔萍.一维弹道修正弹的气动特性研究[D].南京：南京理工大学.2006
    [55]唐伟,江定武,桂业伟,张瑞文.旋成体弹道头部母线线形的选择问题研究[J].空气动力学报,2010,4(2)：218-221
    [56]Moore,F. G.:"A Study to Optimize the Aeroballistic Design of Naval Projectiles", NWLTR-2337, September 1969
    [57]安复兴.关于钝椎体气动特性分析及最优化外形选择[J].空气动力学报,1981年3月第三期：104-110
    [58]高旭东,王晓鸣,刘亚飞.高炮弹丸长径比与飞行稳定性研究[J].弹箭与制导学报,2004年24卷第三期：37-38