#include "dumbLog.h"

#include "../src/orbits.h"


void
testOrbitPropagation()
{
	orbital_elements orbit = {};
	ellipse_parameters ep = {};
	ep.a = 26564.5; // meters
	ep.e = 0.7411;
	orbit.ep = ep;

	// NOTE: solve for gravitational parameter from mean motion
	double mean_motion = 0.00014582; // rad/s
	orbit.mu = pow(mean_motion, 2) * pow(ep.a, 3);

	double initial_anom = 260 * M_PI / 180; // radians
	unsigned int time_step = 60 * 50; // seconds
	double next_pos = getPropagatedPosition(orbit, initial_anom, time_step);

	LOG(Debug) << "E2_1: " << next_pos << "\n";

	return;
}

int
main()
{
	testOrbitPropagation();
	return 0;
}