rocket_flight_simulator.cpp

#include <iostream>
#include <cmath>
#include <vector>
#include <chrono> //obsluga czasu
#include <thread> //zatrzymanie petli

//klasa ma pobierac wysokosc, predkosc, mase paliwa i ciag silnika
class Rocket {
private:
    double height = 0.0;
    double velocity = 0.0;
    double fuel_mass = 0.0;
    double acceleration = 0.0;
    double rocket_mass = 0.0;
    double total_mass = 0.0;
    double fuel_burn_rate = 0.0;
    double exhaust_velocity = 0.0;
    double thrust = 0.0;
    double rocket_diameter = 0.0;
    double drag_coefficient = 0.0;

    std::vector<double> position;
public:
    void load_Data(){
        std::cout<<"Add fuel mass of the rocket: \n";
        std::cin>>fuel_mass;

        std::cout<<"Add rocket mass: \n";
        std::cin>>rocket_mass;

        std::cout<<"Add fuel burn rate per second: \n";
        std::cin>>fuel_burn_rate;

        std::cout<<"Add exhaust velocity: \n";
        std::cin>>exhaust_velocity;

        std::cout<<"Add rocket diameter: \n";
        std::cin>>rocket_diameter;

        std::cout<<"Add drag coefficient: \n";
        std::cin>>drag_coefficient;
    }

    double get_fuel_mass() {
        return fuel_mass;
    }

    double get_height(){
        return height;
    }

    //wysokosc rakiety
    double altitude(){
        height = height + velocity;
        if (height < 0) {
            height = 0;
        }
        return height;
    }

    //calkowita masa
    double rocket_total_mass(){
        total_mass = rocket_mass + fuel_mass;
        return total_mass;
    }
    //opor atmosfery i powietrza
    double air_density(double height) {
        double rho0 = 1.225; //gestosc przy powierzchni ziemi
        double H = 8500.0; // wysokosc skali dla ziemi

        double rho = rho0 * std::exp(-height / H);
        return rho;
        }

    void update_thrust() {
        if (fuel_mass > 0) {
            thrust = exhaust_velocity * fuel_burn_rate;
        }
        else {
            thrust = 0.0; // no fuel used or left
        }
    }
    // dzielenie thrust-masa zeby obliczyc przyspieszenie
    double rocket_acceleration(){
        rocket_total_mass(); // musimy update total_mass
            double radius = rocket_diameter / 2.0;
            double area = rocket_mass * pow(radius,2);
            double drag = 0.5 * air_density(height) * (velocity *std::abs(velocity)) * drag_coefficient * area;

            double net_force = thrust - drag - (rocket_total_mass() * 9.81);

            acceleration =  net_force/total_mass;
            return acceleration;
        }

    double update_velocity() { //przy zmianie
        velocity = velocity + acceleration;
        return velocity;
    }

    //sila przeciazenia
    double g_force(){ // przy zmianie mikrokontroller ktory pobiera g force i wprowadza ja tu
        return acceleration/9.81;
    }

    //jak rakieta staje sie lzejsza przy utracie - aktualna masa
    double rocket_weight_loss(){
        if (fuel_mass > 0) {
            fuel_mass = fuel_mass - fuel_burn_rate; //odejmujemy spalane paliwo od calego paliwa
            if (fuel_mass < 0){
                fuel_mass = 0; // paliwo nie moze byc ujemne
            }
        }
        total_mass = rocket_mass + fuel_mass; //nowa masa rakiety to masa rakiety plus nowa masa paliwa.
        return total_mass;
    }



//
};

int main(){
    Rocket Debris;
    Debris.load_Data();

    int second = 1;

    while(second == 1 || Debris.get_height() > 0 || Debris.get_fuel_mass() > 0) {
        //aktualizacja masy inaczej a bedzie liczone dla starej masy
        Debris.rocket_weight_loss();
        Debris.update_thrust();

        //liczymy parametry lotu
        double h = Debris.altitude();
        double a = Debris.rocket_acceleration();
        double v = Debris.update_velocity();



        std::cout<<"Second "<<second<< " | Altitude: "<< h << "m | Velocity: "<< v <<" | Acceleration: "<< a << "m/s^2 | G Force: " << Debris.g_force() << "\n";

        //
        second++;
        std::this_thread::sleep_for(std::chrono::seconds(1));
    }

}