orbitalMotion¶

Defines

N_DEBYE_PARAMETERS¶

Enums

enum CelestialObject_t¶

Values:

enumerator CELESTIAL_MERCURY¶

enumerator CELESTIAL_VENUS¶

enumerator CELESTIAL_EARTH¶

enumerator CELESTIAL_MOON¶

enumerator CELESTIAL_MARS¶

enumerator CELESTIAL_PHOBOS¶

enumerator CELESTIAL_DEIMOS¶

enumerator CELESTIAL_JUPITER¶

enumerator CELESTIAL_SATURN¶

enumerator CELESTIAL_URANUS¶

enumerator CELESTIAL_NEPTUNE¶

enumerator CELESTIAL_PLUTO¶

enumerator CELESTIAL_SUN¶

enumerator MAX_CELESTIAL¶

Functions

double E2f(double E, double e)¶

double E2M(double E, double e)¶

double f2E(double f, double e)¶

double f2H(double f, double e)¶

double H2f(double H, double e)¶

double H2N(double H, double e)¶

double M2E(double M, double e)¶

double N2H(double N, double e)¶

void elem2rv(double mu, classicElements *elements, double *rVec, double *vVec)¶

void rv2elem(double mu, double *rVec, double *vVec, classicElements *elements)¶

double atmosphericDensity(double alt)¶

double debyeLength(double alt)¶

void atmosphericDrag(double Cd, double A, double m, double *rvec, double *vvec, double *advec)¶

void jPerturb(double *rvec, int num, double *ajtot, ...)¶

void solarRad(double A, double m, double *sunvec, double *arvec)¶

struct classicElements¶

#include <orbitalMotion.h>

This structure contains the set of Keplerian orbital elements that define the spacecraft translational state. It is operated on by the orbital element routines and the OrbElemConvert module.

Public Members

double a¶: object semi-major axis

double e¶: Eccentricity of the orbit.

double i¶: inclination of the orbital plane

double Omega¶: Right ascension of the ascending node.

double omega¶: Argument of periapsis of the orbit.

double f¶: True anomaly of the orbit.

double rmag¶: Magnitude of the position vector (extra)

double alpha¶: Inverted semi-major axis (extra)

double rPeriap¶: Radius of periapsis (extra)

double rApoap¶: Radius if apoapsis (extra)