physics::orbit Namespace Reference

Orbital mechanics. More...

Namespaces
	anomaly
	Orbital anomaly functions.
	frame
	Orbital reference frames.

Classes
struct	elements
	Set of six Keplerian elements required to uniquely identify an orbit. More...
struct	ephemeris
	Table of orbital trajectories. More...
struct	state
	Pair of orbital state Cartesian position (r) and velocity (v) vectors. More...
struct	trajectory
	Describes the trajectory of an orbit with Chebyshev polynomials. More...

Functions
template<class T >
T	period (T a, T gm)
	Calculates the period of an elliptical orbit according to Kepler's third law. More...
template<class T >
T	mean_motion (T a, T gm)
	Calculates the mean motion (n) of an orbit. More...
template<class T >
T	mean_motion (T t)
	Calculates the mean motion (n) of an orbit. More...
template<class T >
T	argument_periapsis (T om, T lp)
	Derives the argument of the periapsis (omega) of an orbit, given the longitude of periapsis (pomega) and longitude of the ascending node (OMEGA). More...
template<class T >
T	longitude_periapsis (T om, T w)
	Derives the longitude of the periapsis (pomega) of an orbit, given the argument of periapsis (omega) and longitude of the ascending node (OMEGA). More...
template<class T >
T	semiminor_axis (T a, T ec)
	Derives the semiminor axis (b) of an orbit, given the semimajor axis (a) and eccentricity (e). More...
template<class T >
T	semilatus_rectum (T a, T ec)
	Derives the semi-latus rectum (l) of an orbit, given the semimajor axis (a) and eccentricity (e). More...

Detailed Description

Orbital mechanics.

See also

Curtis, H. D. (2005). Orbital mechanics for engineering students. Amsterdam: Elsevier Butterworth Heinemann.

Function Documentation

argument_periapsis()

template<class T >

T physics::orbit::argument_periapsis	(	T	om,
		T	lp
	)

Derives the argument of the periapsis (omega) of an orbit, given the longitude of periapsis (pomega) and longitude of the ascending node (OMEGA).

Parameters

lp	Longitude of the periapsis (pomega), in radians.
om	Right ascension of the ascending node (OMEGA), in radians.

Returns

Argument of the periapsis (omega), in radians.

Definition at line 148 of file elements.hpp.

longitude_periapsis()

template<class T >

T physics::orbit::longitude_periapsis	(	T	om,
		T	w
	)

Derives the longitude of the periapsis (pomega) of an orbit, given the argument of periapsis (omega) and longitude of the ascending node (OMEGA).

Parameters

w	Argument of the periapsis (omega), in radians.
om	Right ascension of the ascending node (OMEGA), in radians.

Returns

Longitude of the periapsis (pomega), in radians.

Definition at line 154 of file elements.hpp.

mean_motion() [1/2]

template<class T >

T physics::orbit::mean_motion	(	T	a,
		T	gm
	)

Calculates the mean motion (n) of an orbit.

Parameters

a	Semimajor axis (a).
gm	Standard gravitational parameter (GM).

Returns

Mean motion (n), in radians per unit time.

Definition at line 136 of file elements.hpp.

mean_motion() [2/2]

template<class T >

T physics::orbit::mean_motion

(

T

t

)

Calculates the mean motion (n) of an orbit.

Parameters

t	Orbital period (T).

Returns

Mean motion (n), in radians per unit time.

Definition at line 142 of file elements.hpp.

period()

template<class T >

T physics::orbit::period	(	T	a,
		T	gm
	)

Calculates the period of an elliptical orbit according to Kepler's third law.

Parameters

a	Semimajor axis (a).
gm	Standard gravitational parameter (GM).

Returns

Orbital period (T).

Definition at line 130 of file elements.hpp.

semilatus_rectum()

template<class T >

T physics::orbit::semilatus_rectum	(	T	a,
		T	ec
	)

Derives the semi-latus rectum (l) of an orbit, given the semimajor axis (a) and eccentricity (e).

Parameters

a	Semimajor axis (a).
ec	Eccentricity (e).

Returns

Semi-latus rectum (l).

Definition at line 166 of file elements.hpp.

semiminor_axis()

template<class T >

T physics::orbit::semiminor_axis	(	T	a,
		T	ec
	)

Derives the semiminor axis (b) of an orbit, given the semimajor axis (a) and eccentricity (e).

Parameters

a	Semimajor axis (a).
ec	Eccentricity (e).

Returns

Semiminor axis (b).

Definition at line 160 of file elements.hpp.