Kepler Namespace Reference

Classes
struct	Elements
	Object holding Keplerian orbital elements of a body. More...

Functions
Optional< Elements >	computeOrbitalElements (const Float M, const Float mu, const Vector &r, const Vector &v)
	Computes the orbital elements, given position and velocity of a body. More...
Float	solveKeplersEquation (const Float M, const Float e, const Size iterCnt=10)
	Computes the eccentric anomaly by solving the Kepler's equation. More...
Float	eccentricAnomalyToTrueAnomaly (const Float u, const Float e)
	Computes the true anomaly from the eccentric anomaly and the eccentricity. More...
Float	trueAnomalyToEccentricAnomaly (const Float v, const Float e)
	Computes the eccentric anomaly from the true anomaly and the eccentricity. More...
Vector	position (const Float a, const Float e, const Float u)
	Computes the position on the elliptic trajectory. More...
Vector	velocity (const Float a, const Float e, const Float u, const Float n)
	Computes the velocity vector on the elliptic trajectory. More...
Float	meanMotion (const Float a, const Float m_total)
	Computes the mean motion from the Kepler's 3rd law. More...

Function Documentation

computeOrbitalElements()

Optional< Kepler::Elements > Kepler::computeOrbitalElements	(	const Float	M,
		const Float	mu,
		const Vector &	r,
		const Vector &	v
	)

Computes the orbital elements, given position and velocity of a body.

If the body trajectory is not closed (hyperbolic motion), returns NOTHING.

Parameters

M	Mass characterizing the gravitational field, or sum of body masses for two-body problem
mu	Mass of the orbiting body, or reduced mass for two-body problem
r	Position of the orbiting body
v	Velocity of the orbiting body

Definition at line 37 of file TwoBody.cpp.

eccentricAnomalyToTrueAnomaly()

Float Kepler::eccentricAnomalyToTrueAnomaly	(	const Float	u,
		const Float	e
	)

Computes the true anomaly from the eccentric anomaly and the eccentricity.

Definition at line 70 of file TwoBody.cpp.

meanMotion()

Float Kepler::meanMotion	(	const Float	a,
		const Float	m_total
	)

Computes the mean motion from the Kepler's 3rd law.

Definition at line 90 of file TwoBody.cpp.

position()

Vector Kepler::position	(	const Float	a,
		const Float	e,
		const Float	u
	)

Computes the position on the elliptic trajectory.

It assumes a planar motion in z=0 plane.

Parameters

a	Semi-major axis
e	Eccentricity
u	Eccentric anomaly

Definition at line 82 of file TwoBody.cpp.

solveKeplersEquation()

Float Kepler::solveKeplersEquation	(	const Float	M,
		const Float	e,
		const Size	iterCnt = 10
	)

Computes the eccentric anomaly by solving the Kepler's equation.

Parameters

M	Mean anomaly
e	Eccentricity

Definition at line 62 of file TwoBody.cpp.

trueAnomalyToEccentricAnomaly()

Float Kepler::trueAnomalyToEccentricAnomaly	(	const Float	v,
		const Float	e
	)

Computes the eccentric anomaly from the true anomaly and the eccentricity.

Definition at line 76 of file TwoBody.cpp.

velocity()

Vector Kepler::velocity	(	const Float	a,
		const Float	e,
		const Float	u,
		const Float	n
	)

Computes the velocity vector on the elliptic trajectory.

It assumes a planar motion in z=0 plane.

Parameters

a	Semi-major axis
e	Eccentricity
u	Eccentric anomaly
n	Mean motion

Definition at line 86 of file TwoBody.cpp.