vulcan::orbital::elements Namespace Reference

Functions
template<typename Scalar>
OrbitalElements< Scalar >	cartesian_to_keplerian (const Vec3< Scalar > &r, const Vec3< Scalar > &v, double mu=constants::earth::mu)
	Convert Cartesian state to Keplerian elements.
template<typename Scalar>
std::pair< Vec3< Scalar >, Vec3< Scalar > >	keplerian_to_cartesian (const OrbitalElements< Scalar > &oe, double mu=constants::earth::mu)
	Convert Keplerian elements to Cartesian state.

Function Documentation

cartesian_to_keplerian()

template<typename Scalar>

OrbitalElements< Scalar > vulcan::orbital::elements::cartesian_to_keplerian	(	const Vec3< Scalar > &	r,
		const Vec3< Scalar > &	v,
		double	mu = constants::earth::mu )

Convert Cartesian state to Keplerian elements.

Transforms position and velocity vectors to classical orbital elements. Handles singular cases (circular, equatorial orbits) with numerical guards.

Template Parameters

Scalar

double or casadi::MX

Parameters

r	Position vector in inertial frame [m]
v	Velocity vector in inertial frame [m/s]
mu	Gravitational parameter [m³/s²] (default: Earth)

Returns

OrbitalElements<Scalar>

keplerian_to_cartesian()

template<typename Scalar>

std::pair< Vec3< Scalar >, Vec3< Scalar > > vulcan::orbital::elements::keplerian_to_cartesian	(	const OrbitalElements< Scalar > &	oe,
		double	mu = constants::earth::mu )

Convert Keplerian elements to Cartesian state.

Transforms classical orbital elements to position and velocity vectors.

Template Parameters

Scalar

double or casadi::MX

Parameters

oe	Orbital elements
mu	Gravitational parameter [m³/s²] (default: Earth)

Returns

Pair of (position, velocity) vectors in inertial frame