%液体火箭发动机主参数计算% %程序编写者Into Space (Beihang University) %程序编写时间:2020-5-19 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %需要输入参数:设计地面推力Ftc、喉部半径Rt、燃烧室室压Pc和燃烧室容积Vc、喷管出口扩张半角、钟型喷管相对长度、数据输出地址及文件名称(程序最后)% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% clear; Ftc=500000; %单位牛顿% I=2835.6;%理论比冲,单位m/s% y1=0.98;%燃烧室效率 y2=0.98;%喷管效率 r=2.715;%推进剂混合比 C=1833;%特征速度,单位m/s pia=3.15159;%(圆周率设定) L0=2.4;%特征长度,参见附件,单位m Pc=8.0;%燃烧室室压,单位MPa %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %推力室总质量流量计算% qmc=Ftc/(I*y1*y2); %推进剂流量计算% qmoc=qmc*r/(r+1);%氧化剂流量 qmof=qmc-qmoc;%燃料流量 %主结构参数计算% At=10^(-6)*C*qmc/Pc;%喉部面积 Dt=sqrt(4*At/pia); Rt=Dt/2; Vc=L0*At; %计算喷注器尺寸 %%%%煤油——液体燃料,已知总压,流量,求文氏管喉部直径%% rio=810;%煤油密度 a=0.8;%流量系数 Pt=1.25*Pc;%总压,高于燃烧室室压1.2以上 Atf=qmof/(a*sqrt(2*rio*Pt*1000000))*1000000;%文氏管喉部面积,单位平方毫米 Dtf=2*sqrt(Atf/pia);%文氏管喉部直径,单位毫米 %%%%液氢——液体氧化剂,已知总压,流量,求文氏管喉部直径%% rio1=1140;%y液氢密度 a1=0.8;%液氢流量系数 Ato=qmoc/(a1*sqrt(2*rio1*Pt*1000000))*1000000;%文氏管喉部面积,单位平方毫米 Dto=2*sqrt(Ato/pia);%文氏管喉部直径,单位毫米 %数据打印% fid=fopen('C:\Users\96558\Desktop\rocket01.txt','wt')%输入文件保存地址及新建文件名称% fprintf(fid,'推力室总流量(kg/s),qmc= %d\n\r',qmc); fprintf(fid,'推力室氧化剂流量(kg/s),qmoc= %d\n\r',qmoc); fprintf(fid,'推力室燃料流量(kg/s),qmoc= %d\n\r',qmof); fprintf(fid,'推力室喉部直径(m),Dt= %d\n\r',Dt); fprintf(fid,'发动机特征长度选择(m),L0= %d\n\r',L0); fprintf(fid,'燃烧室容积(m3),Vc= %d\n\r',Vc); fprintf(fid,'氧化剂文氏管喉部直径(mm),Dto= %d\n\r',Dto); fprintf(fid,'燃料文氏管喉部直径(mm),Dtf= %d\n\r',Dtf); fclose(fid);