弹道修正弹脉冲修正机构简易控制方法

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19320079JournalofBallisticsVol.19No.3Sep.2007:2006-10-11:(1981-),,,.姚文进,王晓鸣,高旭东,李文彬(,210094):建立了采用脉冲力控制的弹道修正弹飞行弹道模型.利用均匀设计方法,通过回归分析研究了脉冲修正起始时间脉冲力级数弹丸射角以及作用角度对修正效果的影响,推导出关系模型,利用该模型提出了一种简易的脉冲力控制方法.仿真结果证实该简易方法控制脉冲发动机工作能够有效提高弹丸的命中精度,对脉冲发动机在弹道修正弹上的工程应用有一定的参考意义.:弹道修正弹;脉冲修正;均匀设计;简易控制:TJ410.6:A:1004-499X(2007)03-0019-04ASimpleControlMethodforImpulseCorrectionDeviceinTrajectoryCorrectionProjectileYAOWen-jin,WANGXiao-ming,GAOXu-dong,LIWen-bin(CollegeofMechanicalEngineering,NUST,Nanjing210094,China)Abstract:Thetrajectorycorrectionprojectilemodelusingimpulsewasestablished.Basedonthetheoryofequalitydesignandmethodofregressionanalysis,effectofthestartingtime,impulsenumber,elevationangleandactingangleonthecorrectionabilitywasstudied.Therelationshipmodelwasdeduced.Accordingtothismodel,onesimplecontrolmethodwasputforward.Thesimulationresultsshowthismethodcanimprovethehittingprecisioneffectively.Thismethodisusefulintheengineeringapplicationofimpulseengineintrajectorycorrectionprojectile.Keywords:trajectorycorrectionprojectile;impulsecorrection;designofequality;simplecontrol.,.,.,.[1],.[2],;[3],,,.,,.,.,,,,.191,8,,,,1.,Ox1y1z1Oy1C1,,,2.,[5].12FOx1y1z1(Fx1Fy1Fz1)T=F(0-cosC1-sinC1)T(1)AD1D2AD1D2=cosD2cosD1-sinD1-sinD2cosD1cosD2sinD1cosD1-sinD2sinD1sinD20cosD2(2),Fx2Fy2Fz2=F(cosC1sinD1+sinC1sinD2cosD1)-F(cosC1cosD1-sinC1sinD2sinD1)-FsinC1cosD2(3),D1,D2,C1Oy1.(3).2:3175N#s,0.01s,.[6].2.13,[7],.38U8(83),.,Dd,1,,t0,n,H.1t0/snH/(b)Dd/m13.00047027.28823.57185052.88434.14333018.07044.71471038.20455.28628010.73465.85766028.57576.4291404.22187.00052017.532,Dd=26.014-3.4067t0+0.42513n-0.0042t0H+0.509n2+0.009181nH(4)2.,SS,fD,SM.2SSfDSMF17085341.6149730.1373820.06871708.27R=1,s=0.26208,A=0.05,Ft=4973,FF0.05(5,2)=19.3,.,(4),.2.23(3)Oxyz3203,3,C1.3C13.3,,.Oxyz3,xyz3Dx=cx1cos(C1+cx2)+cx3Dy=cy1cos(C1+cy2)+cy3Dz=cz1sin(C1+cz2)+cz3(5),cx1cx2cx3cy1cy2cy3cz1cz2cz3.3.(),,.3,.,.3.1$d,di,2Ei.$d,$d[E1/2,;$dd8,,8;E1/2$d[d8,4n.?T(T).43.2,(5).$x$y$z(5)CxCyCz,$dx$dy$dz,$dmin=min($dx,$dy,$dz),$dmin,,.430b5s,,3-50m30m10m,59.16m,38.xyz3:Dx=18.303cosC1Dy=-38.764cosC1Dz=-42.898sinC1(6)Cx=0b,Cy=40b,Cz=13.5b,$dx=34.3m,$dy=40.1m,$dz=33.1m,$dmin=$dz=33.1m.,8,Oy113.5b,33.1m.5,.,2119,,3.,.[1]Der-RenT,ChernJS.Optimalthrustvectorcontroloftact-icalmissiles,AIAA-97-3475[R].1997.[2],.[J].,1999,20(4):453-458.[3],.[J].,2002,21(1):18-21.[4]ThanatJ,BradleyB,MarkC.Acomparisonofdifferentguid-anceschemesforadirectfirerocketwithapulsejetcontrolmechanism,AIAA-2001-4326[R].2001.[5]ThanatJ,MarkC.Dispersionreductionofadirectfirerocketusinglateralpulsejets,AIAA-2001-0104[R].2001.[6],.[J].,2004,24(5):383-386.[7].[M].:,1994.(上接第18页):v],R0,CxCx0,(15)Cx0,,,1,x=Q1v0dvav=1alnv1v0=-1alnv0=2mQSCx0lnv0(16)4,xSB16xSD20xSB12xSB6,,,;.5,,..[1].[M].,.:,1983.[2]FuHuiping,LuChuanjing,LiJie.Numericalresearchondragreductioncharacteristicsofsupercavitatingbodyofrevolution[J].JournalofShipMechanics,2004,8(3):1-7.[3]FarrarCL,LeemingDW.[M].,,,.:,1990.[4]SinghalAK,AthavaleMM,LiHY,etal.Mathematicalba-sisandvalidationofthefullcavitationmodel[J].JournalofFluidsEngineering,2002,124:617-624.[5]YuN.Supercavitation-problemsandperspectives[C].4thIn-ternationalSymposiumonCavitation.California:CaliforniaInstituteofTechnologyPasadena,2001.22

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