Cartesian Coordinates¶

Functions for working with Cartesian state vectors and conversions.

State Conversions¶

state_osculating_to_cartesian(x_oe: ndarray, angle_format: AngleFormat) -> np.ndarray

Convert osculating orbital elements to Cartesian state.

Transforms a state vector from osculating Keplerian orbital elements to Cartesian position and velocity coordinates.

Parameters:

Name	Type	Description	Default
`x_oe`	`ndarray`	Osculating orbital elements `[a, e, i, RAAN, omega, M]` where `a` is semi-major axis (meters), `e` is eccentricity (dimensionless), `i` is inclination (radians or degrees), `RAAN` is right ascension of ascending node (radians or degrees), `omega` is argument of periapsis (radians or degrees), and `M` is mean anomaly (radians or degrees).	required
`angle_format`	`AngleFormat`	Angle format for angular elements (`RADIANS` or `DEGREES`).	required

Returns:

Type	Description
`ndarray`	Cartesian state `[x, y, z, vx, vy, vz]` where position is in meters and velocity is in meters per second.

state_cartesian_to_osculating(x_cart: ndarray, angle_format: AngleFormat) -> np.ndarray

Convert Cartesian state to osculating orbital elements.

Transforms a state vector from Cartesian position and velocity coordinates to osculating Keplerian orbital elements.

Parameters:

Name	Type	Description	Default
`x_cart`	`ndarray`	Cartesian state `[x, y, z, vx, vy, vz]` where position is in meters and velocity is in meters per second.	required
`angle_format`	`AngleFormat`	Angle format for output angular elements (`RADIANS` or `DEGREES`).	required

Returns:

Type	Description
`ndarray`	Osculating orbital elements `[a, e, i, RAAN, omega, M]` where `a` is semi-major axis (meters), `e` is eccentricity (dimensionless), `i` is inclination (radians or degrees), `RAAN` is right ascension of ascending node (radians or degrees), `omega` is argument of periapsis (radians or degrees), and `M` is mean anomaly (radians or degrees).