#include <iostream>
#include <stdio.h>
using namespace std;
// Potisak motora u Njutnima
double dEngineThrust = 1971429;
// Broj motora na prvom stepenu
double dNumOfEngines = 35;
// Ukupan potisak u Njutnima
double dTotalThrust;
// Specifican impuls motora u sekundama
double dIsp = 330;
// Gravitaciona konstanta 9.81 N/kg
const double cdg = 9.81;
// Inkrement vremena u sekundama
const double dt = 0.01;
// Masa kompletne rakete u kg
double dStartMass = 4655000;
// Trenunta masa rakete
double dCurrentMass;
// Protok goriva u N/sec
double dFuelFlow;
// Brzina rakete u m/sec
double dVelocity = 0;
// Prethodna brzina
double dOldVelocity;
// Finalna brzina u m/sec
const double cdFinalVelocity = 100;
// Visina rakete u m
double dHeight = 0;
// Simulacija u odsustvu gravitacije Da/Ne (true/false)
bool bSimNoGravity = false;
// Potroseno goriva u tonama
double dFuelSpent;
int main()
{
int dIt = 0;
dCurrentMass = dStartMass;
dTotalThrust = dEngineThrust*dNumOfEngines;
dFuelFlow = dTotalThrust/(dIsp*cdg);
while(dVelocity < cdFinalVelocity)
{
dIt++;
dOldVelocity = dVelocity;
dCurrentMass = dCurrentMass - dt * dFuelFlow;
if (bSimNoGravity)
{
dVelocity = dVelocity + dTotalThrust/dCurrentMass*dt;
}
else
{
dVelocity = dVelocity + (dTotalThrust/dCurrentMass - cdg)*dt;
}
dHeight = dHeight + (dOldVelocity + dVelocity)*dt/2;
}
dFuelSpent = (dStartMass - dCurrentMass)/1000.0;
double dCurrentMassT = dCurrentMass/1000.0;
double dTime = dIt*dt;
printf("Krajnja masa : %10.2f t\n", dCurrentMassT);
printf("Potroseno gorivo: %10.2f t\n", dFuelSpent);
printf("Visina : %10.2f m\n", dHeight);
printf("Vreme : %10.2f sec\n", dTime);
return 0;
}
