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/* SIMULATION OF SHUTTLE TAKE OFF & FLIGHT UP TO MAIN ENGINE SEPARATION */
/* contributed by IVOR J LEWIS for Ch users*/
#include <chplot.h>
#include <math.h>
#include <stdlib.h>
#include <stdio.h>
#include <conio.h>
#include <time.h>
time_t ltime;
float z=32.2,b=16788,f=2622,po=7,t=2,w4=365000,w5=190000,r1=134,r2=494;
float f1o=-32.2,h=2,t1=5800000,t2=1410000,w2=2216000,w3=1360000,w1=4410000;
float x1o=0,y1o=0,c1,co,f2,f3,i,j,k,la,m1,m2,mh,n1,n2,y1a,S[255];
float r,ro,u,ug,vg,wg,x,xa,xd,xg,xl,xr,y,ya,yb,yd,yg,yt,zg;
float miny,minx,maxy,maxx,to,amaxy,amaxx,fq,ds,tq,xt,xb,xk,az,yk,za,fg,bn;
float aminy,aminx,ato,axo,avo,ago,xo,yo,f1a,tt1,tI,an;
float x1,x2,x3,x4,zz,y2,y3,y4,t3, f1, f4,q,p;
int l,hm,tm,it,id,nv;
int np=255;
array double D[np],E[np],G[np],GL[np],AI[np],PW[np],SI[np],AU[np],V[np],W[np];
char buffer [np];
string_t title="Shuttle Flight Parameters - Zero to 500 seconds from Lift Off",
xlabel="Time - secs",
ylabel="Magnitude";
class CPlot plot;
main(argc, argv) /* MAIN DRIVER START ****************************** */
int argc;
char *argv[];
{
time(<ime);
printf("\n");
printf(" This program is the property of Ivor J Lewis\n");
printf(" CURRENT TIME %s\n", ctime (<ime));
printf(" SIMULATED LIFT-OFF AND INITIAL LAUNCH OF THE SPACE SHUTTLE\n\n");
/* SUMMARY OF INITIAL PRE-FLIGHT CONDITIONS************************* */
printf("* INITIAL PRE¡ª FLIGHT PARAMETERS *\n\n" );
printf("* SOLID BURN RATE = %12.2f LB/SEC\n",b);
printf("* G CONSTANT = %12.2f FT/SEC\n",z);
printf("* DRAG COEFFICEINT = %12.2f FT/FT~2/SEC^2\n",po);
printf("* LIQUID BURN RATE = %12.2f LB/SEC\n",f);
printf("* SOLID ROCKET WEIGHT = %12.2f LB\n",w4);
printf("* LIFT OFF TIME REFERENCE = %12.2f SEC\n",t);
printf("* BOOSTER SEPARATION TIME = %12.2f SEC\n",r1);
printf("* MAIN ENGINE WEIGHT = %12.2f LB\n",w5);
printf("* RELATIVE ACCELERATION BATE = %12.2f FT/SEC\n",f1o);
printf("* MAIN ENGINE SEPARATION TIME = %12.2f SEC\n",r2);
printf("* BOOSTER THRUST = %12.2f LB\n",t1);
printf("* FLIGHT TIME INCREMENT = %12.2f SEC\n",h);
printf("* SOLID FUEL WEIGHT = %12.2f LB\n",w2);
printf("* MAIN ENGINE THRUST = %12.2f LB\n",t2);
printf("* INITIAL TOTAL WEIGHT = %12.2f LB\n",w1);
printf("* LIQUID FUEL WEIGHT = %12.2f LB\n",w3);
printf("* INITIAL VELOCITY REFERENCE = %12.2f FT/SEC\n",y1o);
printf("* GROUND ZERO REFERENCE = %12.2f FT\n\n",x1o);
printf("PRESS RETURN TO CONTINUE\n");
getchar();
printf("\n");
printf("\n");
printf("\n\n");
/* CALCULATION OF FLIGHT PARAMETERS */
int i;
float y1;
l_newc:;
for (i=1;i<=(np);i++)
{
tI=q=c1=0;
x1=x1o;
y1=y1o;
f1=f1o;
p=po;
W[0] = E[0]= D[0] = V[0]= AI[0] = 0.0;
SI[0] = 2.0;
G[0] = -32.2;
r = tI;
q = p;
c1 = w1;
nv=1;
W[0]=c1;
for(i=0; i <= np-1; i++)
{
if(r < 9) goto l_510;
t3 = t1 + t2;
goto l_530;
l_510:;
t3 = (r * (t1 + t2)) / 9.;
c1 = w1;
goto l_830;
l_530:
if(r > r1) goto l_560;
c1 = w1- ((b + f) * r);
zz = z / c1;
goto l_610;
l_560:;
if(r > r2) goto l_590;
c1 = (w1 - w4 - w2 - (f * r));
zz=z / c1;
goto l_610;
l_590:;
c1 = w1 - w4 - w2 - w5 - w3;
zz = z / c1;
t2 = t2 * .416;
l_610:;
x2 = x1 + (h * y1) / 2;
y2 = y1 + (h * f1) / 2;
if(r > r1) goto l_650;
f2 = zz * (t3 - c1 -( q * y2*y2));
goto l_660;
l_650:;
f2 = zz * (t2 - c1 -( q * y2*y2));
l_660: ;
x3 = x1 + h * y2/2;
y3 = y1 + h * f2 / 2;
if( (r > r1)) goto l_700;
f3 = zz * (t3 - c1 - q * y3*y3);
goto l_710;
l_700:;
f3 = zz * (t2 - c1 - q * y3*y3);
l_710:;
x4=x1+h*y3;
y4 = y1 + h * f3;
if(r > r1) goto l_750;
f4 = zz * (t3 - c1 - q * y4 * y4);
goto l_760;
l_750: ;
f4 = zz * (t2 - c1 - q * y4 * y4);
l_760:;
D[(i)] = x1 + h * (y1 + 2 * y2 + 2 * y3 + y4) / 6;
V[(i)] = y1 + h * (f1 + 2 * f2 + 2 * f3 + f4) / 6;
if(r > r1) goto l_810;
G[(i)] = zz * (t3 - c1 - q * V[(i)]*V[(i)]);
goto l_930;
l_810: ;
G[(i)] = zz * (t2 - c1 - q * V[(i)]*V[(i)]);
goto l_930;
l_830:;
G[(i)] = (t3 * z / w1) - z;
if(G[(i)] < 0) goto l_910;
V[(i)] = ((G[(i - 1)] + G[(i)]) / 2)* h;
if(V[(i)] < 0) goto l_910;
D[(i)] = ((V[(i - 1)] + V[(i)])/ 2)* h;
if(D[(i)] < 0) goto l_910;
if(r == 7) goto l_930;
goto l_940;
l_910: ;
D[(i)] = 0;
V[(i)] = 0;
goto l_940;
l_930: ;
f1 = G[(i)];
x1 = D[(i)];
y1 = V[(i)];
l_940: ;
SI[(i)] = tI + h;
tI = SI[(i)];
AI[(i)] = SI[(i)] - 4;
E[(i)] = q * V[(i)]*V[(i)];
if(D[(i)] > 300000.) goto l_990;
goto l_1010;
l_990: ;
E[(i)] = 0.;
l_1010:;
AU[(i)] = V[(i)] / 998.96;
GL[(i)] = ((G[(i)] + 32.2) / 32.2);
PW[(i)] = V[(i)] * c1 / 550;
mh =.68181818 * V[(i)];
W[i]=c1;
r=tI +h;
if((r > r2) && (D[(i)] > 300000.)) goto l_1370;
if((r > r1) && (D[(i)] > 300000.)) goto l_1390;
goto l_1400;
l_1370:;
p = .343 * p;
goto l_1400;
l_1390:;
p = .66 * p;
l_1400: ;
if(D[(i)] > 300000.) goto l_1430;
q = (p * 1.12 * 1 / exp(4.1865e-05 * x1));
goto l_1440;
l_1430:;
q = 0.;
l_1440:;
}
for (i=0;i<np;i++)
{
/* start of plot routines */
AI[0]=0;
G[0]=-32.2;
W[0]=0;
E[0]=0;
V[0]=0;
PW[0]=0;
D[0]=0;
GL[0]=0;
printf("\n\n");
plot.axisRange(PLOT_AXIS_X, 0, AI[(np-1)], 25);
plot.axisRange(PLOT_AXIS_Y, 0-20,100,5);
plot.grid(PLOT_ON);
plot.data2D(AI,(G/2));
plot.data2D(AI,(W/50000));
plot.data2D(AI,(E/25000));
plot.data2D(AI,(V/150));
plot.data2D(AI,(PW/250000));
plot.data2D(AI,((D/5280)/5));
plot.data2D(AI,(GL*20));
/* Plot data scaled to suit graphic layout*/
plot.legend("G Acceleration - ft/sec^2- Div 2",0);
plot.legend("W Shuttle Flight weight - lb- Div 50000",1);
plot.legend("E Drag Force - lb -Div 25000",2);
plot.legend("V Shuttle Speed - m.p.h - Div 150",3);
plot.legend("PW Developed HP - Div 250000",4);
plot.legend("D Distance into Flight - miles -Div 5",5);
plot.legend("GL G-Load -Times 20",6);
plot.legendLocation(380,97);
plot.title(title);
plot.label(PLOT_AXIS_X, xlabel);
plot.label(PLOT_AXIS_Y, ylabel);
plot.grid(PLOT_ON);
plot.plotting();
/* end of plot routines */
if(i=np)goto l_7000;
}
l_7000:;
/* CALCULATE SPECIFIC TIME FRAMES */
int nimp;
float sm;
printf("\n");
printf("TO LIST A FLIGHT TIME SUMMARY INPUT VALUE -2 TO 500\n");
printf("ENTER TIME VALUE <= 504\t");
scanf("%d",&it);
if(it > 504) goto l_tv1;
it =(it/2+2);
printf("* TIME INTO LAUNCH %12.2f SEC\n",AI[it]);
printf("* RANGE DISTANCE %12.2f FT\n",D[it]);
printf("* RANGE DISTANCE %12.2f MI\n",D[it]/5280);
printf("* SHUTTLE VELOCITY %12.2f FT/SEC\n",V[it]);
printf("* EQUIVILANT LAND SPEED %12.2f MPH\n",.68181818*V[it]);
printf("* RELATIVE ACCELERATION %12.2f FT/SEC^2\n",G[it]);
printf("* AERODYNAMIC DRAG FORCE %12.2f LB\n",E[it]);
printf("* MACH NUMBER %12.2f M\n",AU[it]);
printf("* G LOADING %12.2f G\n",GL[it]);
printf("* DEVELOPED HORSE POWER %12.2f HP\n",PW[it]);
printf("* TOTAL WEIGHT OF SHUTTLE %12.2f LB\n",W[it]);
l_tv1:;
/* REDO CALCULATION CHANGING PARAMETERS*/
int iq;
if(it > 504) goto l_e1;
printf("TO CHANGE BOOSTER THRUST INPUT VALUE 5800000 LB\n");
printf("ENTER NEW VALUE OR ZERO\t");
scanf("%f",&an);
t1=an;
getchar ();
printf("TO CHANGE MAIN ENGINE THRUST INPUT VALUE 1410000 LB\n");
printf("ENTER NEW VALUE OR ZERO\t");
scanf("%f",&bn);
t2=bn;
if(bn==0 && an==0) goto l_e1;
getchar();
goto l_newc;
l_e1:;
printf("END OF PROGRAM\n");
exit(0);
}
}
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