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Design a basic attitude control system for a spacecraft. The system should be able to maintain the spacecraft's orientation within certain limits, and should be able to rotate the spacecraft about one or more axes. The system should also be able to compensate for any external forces acting on the spacecraft, such as solar radiation pressure or gravity. in C++

C++

#include <iostream>
#include <cmath>
using namespace std;

int main() {

double x, y, z; // position of the spacecraft in 3D space (x,y,z)

double vx, vy, vz; // velocity of the spacecraft in 3D space (vx,vy,vz)

double ax = 0.0; // acceleration of the spacecraft in 3D space (ax=0.0)

double m = 1.0; // mass of the spacecraft (m=1.0)

double Fx = 0.0; // force acting on the spacecraft in x direction (Fx=0.0)

double Fy = 0.0; // force acting on the spacecraft in y direction (Fy=0.0)

double Fz = 0.0; // force acting on the spacecraft in z direction (Fz=0.0)

// initial conditions: 
	// position: x=1 y=-2 z=-3 
	// velocity: vx=-2 vy=-3 vz=-4 
	// acceleration: ax=1 ay=-2 az=-3 
	// mass: m=1 
    x = 1.; y = -2.; z = -3.; 
    vx = -2.; vy = -3.; vz = -4.; 
    ax = 1.; ay = -2.; az = -3.;

double t_max_simulation_time_in_seconds(10); // maximum simulation time is 10 seconds

double dt(1e-5); // time step is 10^(-5) seconds

int N((int)(t_max_simulation_time_in_seconds/dt)); // number of iterations is equal to maximum simulation time divided by time step

for(int i(1); i<N+1 ; i++) {

double r(sqrt(pow(x, 2.) + pow(y, 2.) + pow(z, 2.)));

double G(-6.67e-11);

double M(5.97e24);

Fx += G*M*m*ax/pow(r , 3.) * x / r ;

Fy += G*M*m*ay/pow(r , 3.) * y / r ;

Fz += G*M*m*az/pow(r , 3.) * z / r ;     }     }

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