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ksp: add staging support

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This commit is contained in:
Vince Weaver 2016-05-26 15:24:05 -04:00
parent 46c446433b
commit 9ab8b70cd9
1 changed files with 59 additions and 29 deletions

88
ksp/c/ksp_launch.c

@ -50,20 +50,20 @@ int main(int argc, char **argv) {
FILE *logfile;
double angle=45;
double angle=0;
double capsule_mass=1.0;
double engines=3;
// double engines=3;
double engine_isp=270.0; /* s */
double engine_mass=(1.5)*engines; /* tons */
double engine_thrust=(168.0)*engines; /* kN */
double fuel_flow_rate;
// double engine_mass=(1.5)*engines; /* tons */
// double engine_thrust=(168.0)*engines; /* kN */
// double fuel_flow_rate;
double tanks=6;
double tank_mass=(0.5)*tanks; /* tons */
double fuel_mass=(4.0)*tanks; /* tons */
double total_fuel=fuel_mass;
// double tanks=6;
// double tank_mass=(0.5)*tanks; /* tons */
// double fuel_mass=(4.0)*tanks; /* tons */
// double total_fuel=fuel_mass;
double fuel_left=100.0;
double gravity=-9.8; /* m/s^2 */
@ -84,60 +84,79 @@ int main(int argc, char **argv) {
double rocket_y=KERBIN_RADIUS+10;
double rocket_altitude=KERBIN_RADIUS; /* m */
double deltav,twr;
double total_mass,empty_mass;
double v0_x,v0_y;
double time=0.0; /* s */
int stage=1;
int stage=2;
int log_step=0;
char input;
int thrusting=1;
int thrusting=1,i,j;
int stages=3;
int engines[3],stacks[3],tanks[3];
double stage_empty_mass[3],stage_full_mass[3],total_mass[3],thrust[3];
double fuel_mass[3],stage_fuel_total[3];
double deltav[3],twr[3],fuel_flow[3];
logfile=fopen("log.jgr","w");
total_mass=engine_mass+tank_mass+fuel_mass+capsule_mass;
empty_mass=total_mass-fuel_mass;
engines[0]=1; stacks[0]=1; tanks[0]=1;
engines[1]=2; stacks[1]=2; tanks[1]=1;
engines[2]=3; stacks[2]=3; tanks[2]=1;
deltav=engine_isp*gravity*log(total_mass/empty_mass);
for(i=0;i<stages;i++) {
stage_empty_mass[i]=(engines[i]*1.5)+(stacks[i]*tanks[i]*0.5)+capsule_mass;/* tons */
fuel_mass[i]=(stacks[i]*tanks[i]*4.0);
stage_fuel_total[i]=fuel_mass[i];
stage_full_mass[i]=stage_empty_mass[i]+fuel_mass[i];
twr=engine_thrust/(total_mass*-gravity);
total_mass[i]=0.0;
for(j=i;j>=0;j--) {
total_mass[i]+=stage_full_mass[j];
}
thrust[i]=engines[i]*168.0; /* kN */
deltav[i]=engine_isp*-gravity*log(total_mass[i]/(total_mass[i]-fuel_mass[i]));
twr[i]=thrust[i]/(total_mass[i]*-gravity);
fuel_flow[i]=(thrust[i])/(engine_isp*-gravity);
printf("Stage %d\n",i+1);
printf("\ttanks=%d engines=%d\n",stacks[i]*tanks[i],engines[i]);
printf("\tstage mass=%lf total_mass=%lf\n",stage_full_mass[i],
total_mass[i]);
printf("\tdeltaV=%lf\n",deltav[i]);
printf("\tTWR=%lf\n",twr[i]);
fuel_flow_rate=(engine_thrust)/(engine_isp*-gravity);
}
printf("DeltaV=%lf m/s\n",deltav);
printf("Thrust/weight=%lf\n",twr);
printf("Fuel flow rate=%lf, time=%lfs\n",
fuel_flow_rate,fuel_mass/fuel_flow_rate);
// printf("Fuel flow rate=%lf, time=%lfs\n",
// fuel_flow_rate,fuel_mass/fuel_flow_rate);
scanf("%c",&input);
while(1) {
/* 4010 */
fuel_left=fuel_mass*100.0/total_fuel;
fuel_left=fuel_mass[stage]*100.0/stage_fuel_total[stage];
thrusting=1;//autopilot(fuel_left, rocket_altitude,&angle);
if (thrusting) {
if (fuel_mass<0.1) {
fuel_mass=0.0;
if (fuel_mass[stage]<0.1) {
fuel_mass[stage]=0.0;
rocket_acceleration_x=0;
rocket_acceleration_y=0;
}
else {
rocket_acceleration_x=(engine_thrust/total_mass)*sin_degrees(angle);
rocket_acceleration_y=(engine_thrust/total_mass)*cos_degrees(angle);
rocket_acceleration_x=(thrust[stage]/total_mass[stage])*sin_degrees(angle);
rocket_acceleration_y=(thrust[stage]/total_mass[stage])*cos_degrees(angle);
fuel_mass=fuel_mass-fuel_flow_rate;
total_mass=engine_mass+tank_mass+fuel_mass+capsule_mass;
fuel_mass[stage]=fuel_mass[stage]-fuel_flow[stage];
total_mass[stage]=total_mass[stage]-fuel_flow[stage];
}
}
else {
@ -238,6 +257,17 @@ int main(int argc, char **argv) {
else printf("^");
scanf("%c",&input);
if (input==' ') {
if (stage>0) stage--;
}
if (input=='d') {
angle+=45.0;
if (angle>=360) angle=0.0;
}
if (input=='a') {
angle-=45.0;
if (angle<0.0) angle+=360.0;
}
time+=1.0;