《导弹燃料相对高质量因数计算》由会员分享，可在线阅读，更多相关《导弹燃料相对高质量因数计算（14页珍藏版）》请在金锄头文库上搜索。
1、word防空导弹主级燃料相对质量因数计算导弹总体设计课程大作业班级某某学号目录一、实验目的3二、实验要求3三、计算方法3四、实验数据61、别离条件62、气动参数63、发动机参数64、导引规律75、大气模型7五、实验结果7778附 程序源代码9一、实验目的在导弹总体设计中，与导弹飞行性能关系最为密切的参数称为主要参数，包括导弹质量m，发动机推力P和导弹的参考面积S.这些参数在在很大程度上决定了导弹的飞行性能。因此，对对导弹总体设计来说，在战术技术要求确定之后，就应该确定上述主要参数。为便于解决问题和有利于应用设计经验统计数据，主要参数一般用相对量形式表示。对于质量m，引入相对参数表示导弹在某一瞬
2、间时t所消耗的燃料相对质量因数。本实验的目的:计算在确定战术性能指标要求下导弹的相对质量因数，为导弹总体设计提标准。导弹燃料质量由导弹运动特性决定，在导弹设计初期难以确切知道导弹运动微分方程组各项技术参数，因而无法求解。通过寻求能表征导弹运动特征的相对参量来取代方程中的绝对参量，形成相对量运动微分方程，从而可结合具体需要找出符合特殊设计要求的参数。二、实验要求1、 根据条件，采用数值积分法求解相对量运动微分方程组，计算燃料相对质量因数。2、 综合运用积分、插值计算等计算方法，采用C、C+，或者MATLAB等语言的一种，编制计算程序。三、计算方法导弹燃料质量由导弹运动特性决定，在导弹设计初期难以
3、确切知道导弹运动微分方程组各项技术参数，因而无法求解。通过寻求能表征导弹运动特征的相对参量来取代方程中的绝对参量，形成相对量运动微分方程1、导弹相对量运动微分方程(1)2、三点法三点法是指在攻击目标的过程中，导弹始终位于导引站和目标的连线上，即导引站、导弹、目标三点成一直线的导引法，它是遥控导弹的导引方法之一。图 1 三点法导引关系图弹道参数存在以下关系(2)(3)导引规律为(4)(5)弹道倾角与上下角的关系为：(6)时间与上下角的关系为：(7)将 两边积分，并带入上式可得：(8)通过导弹微分方程和三点法导引规律推导出相应的导弹微分方程，在所给表格数据的根底上利用二元插值法得到不同情况下的和，
4、利用龙格库塔四步四阶数值积分法逐步计算导弹的弹道，直到导弹击中目标，此时的值即为导弹在给定战术指标要求下的最小值。3、三点法导引的导弹微分方程三点法导引的导弹微分方程如下：(9)四、实验数据1、别离条件速度V=500m/s，时间t=3s，x方向位置，y方向位置，初始攻角，初始弹道倾角。2、气动参数阻力因数插值表：246810升力因数斜率插值表：1246810注：以上攻角单位均为度。3、发动机参数比冲Is=2156；重力加速度g=9.801；推重比；翼载。4、导引规律三点法。目标匀速直线等高迎头飞行，弹目斜距。5、大气模型，五、实验结果图 2弹道图形变化图图 3攻角的变化情况附 程序源代码% B
5、y JRD % %-clear;clc;u = 0; %燃料相对质量因数初始值%-初始参数-Is = 2156; %发动机参数g = 9.801;P2W = 2.2;P0 = 5880;Vt = 420; %目标参数yt = 15000;Dt0 = 34200;q0 = asin(yt/Dt0);V0 = 500; %导弹参数t0 = 3;x0 = 674;y0 = 329;Attack = 1.5;sita0 = 26;s0 = sita0*pi/180;T0 = 288.15; %大气参数r0 = 1.2495;H = y0;i = 1;while H = yt x(1) = x0; y(
6、1) = y0; s(1) = s0; V(1) = V0;if y(i)=11000 %不同高度的温度和密度 T=288.15-0.0065*y(i); r=r0*(T/T0)4.25588;else T=216.65; r=0.36392/exp(y(i)-11000)/6341.62);end V_sound = 20.0468*sqrt(T); %音速，马赫数计算 Ma = V(i)/V_sound; Attack(1) = 1.5;%-阻力因数插值表-attack1 = 2 4 6 8 10;Mach1 = 1.5, 2.1, 2.7, 3.3, 4.0;cx = 0.0430,0.
7、0511,0.0651,0.0847,0.1120;0.0360,0.0436,0.0558,0.0736,0.0973;0.0308,0.0372,0.0481,0.0641,0.0849;0.0265,0.0323,0.0419,0.0560,0.0746;0.0222,0.0272,0.0356,0.0478,0.0644;Cx = interp2(attack1,Mach1,cx,Attack(i),Ma,spline);%-升力因数插值表-attack2 = 1, 2, 4, 6, 8, 10;Mach2 = 1.5, 2.0, 2.5, 3.0, 3.5, 4.0;cy = 0.0
8、302,0.0304,0.0306,0.0309,0.0311,0.0313;0.0279,0.0280,0.0284,0.0286,0.0288,0.0290;0.0261,0.0264,0.0267,0.0269,0.0272,0.0274;0.0247,0.0248,0.0251,0.0254,0.0257,0.0259;0.0226,0.0227,0.0231,0.0233,0.0236,0.0238;0.0209,0.0210,0.0213,0.0216,0.0219,0.0221;Cy = interp2(attack2,Mach2,cy,Attack(i),Ma,spline);
9、%-数值积分-%-四级四阶Runge-Kutta法-h = 0.001; %步长K1 = Is/(1-u)-r*V(i)2*Cx*Is/(2*P2W*P0*(1-u)-Is*sin(s(i)/P2W;K2 = Is/(1-(u+h/2)-r*(V(i)+h/2*K1)2*Cx*Is/(2*P2W*P0*(1-(u+h/2)-Is*sin(s(i)/P2W;K3 = Is/(1-(u+h/2)-r*(V(i)+h/2*K2)2*Cx*Is/(2*P2W*P0*(1-(u+h/2)-Is*sin(s(i)/P2W;K4 = Is/(1-(u+h)-r*(V(i)+h*K3)2*Cx*Is/(2*P
10、2W*P0*(1-(u+h)-Is*sin(s(i)/P2W; V(i+1) = V(i)+(K1+2*K2+2*K3+K4)*h/6;y(i+1) = y(i)+Is/(P2W*g)*V(i)*sin(s(i)*h;H=y(i+1);x(i+1) = x(i)+Is/(P2W*g)*V(i)*cos(s(i)*h;p = P2W;p0 = P0;Ks1 = Vt/yt*(Is/(P2W*g)+(V(i)*Is/(P2W*g)*V(i)*sin(s(i)-y(i)*(K1+2*K2+2*K3+K4). /6)/V(i)2/sin(s(i)/(1+(cot(q0)-u*Is*Vt/P2W/g/y
11、t)*cot(s(i);Ks2 = Vt/yt*(Is/(P2W*g)+(V(i)*Is/(P2W*g)*V(i)*sin(s(i)+Ks1*h/2)-y(i)*(K1+2*K2+2*K3+K4). /6)/V(i)2/sin(s(i)+Ks1*h/2)/(1+(cot(q0)-(u+h/2)*Is*Vt/P2W/g/yt)*cot(s(i)+Ks1*h/2);Ks3 = Vt/yt*(Is/(P2W*g)+(V(i)*Is/(P2W*g)*V(i)*sin(s(i)+Ks2*h/2)-y(i)*(K1+2*K2+2*K3+K4). /6)/V(i)2/sin(s(i)+Ks2*h/2)/(1
12、+(cot(q0)-(u+h/2)*Is*Vt/P2W/g/yt)*cot(s(i)+Ks2*h/2);Ks4 = Vt/yt*(Is/(P2W*g)+(V(i)*Is/(P2W*g)*V(i)*sin(s(i)+Ks3*h)-y(i)*(K1+2*K2+2*K3+K4). /6)/V(i)2/sin(s(i)+Ks3*h)/(1+(cot(q0)-(u+h)*Is*Vt/P2W/g/yt)*cot(s(i)+Ks3*h);s(i+1) = s(i)+(Ks1+2*Ks2+2*Ks3+Ks4)*h/6;Attac(i) = (V(i)*(Ks1+2*Ks2+2*Ks3+Ks4)/6+Is*cos(s(i)/P2W)/(r*V(i)2*Cy*180/pi*Is. /(2*P2W*P0*(1-u)+Is/(1-u);Attack(i+1) = Attac(i)*180/pi; u = u+h;i = i+1;endu = u-h;Attack(1) = Attack(2);%-图像绘制-figure(1);plot(x,y,r-); %弹道曲线xlabel(x/m);ylabel(y/m);grid;%hold on;figure(2);plot(Attack,b-);
