Function lupnt::ClassicalToCart

• Defined in File state_conversions.cc

Function Documentation

State lupnt::ClassicalToCart(const State &coe, Real GM)

Convert classical orbital elements to Cartesian state.

Convert classical orbital elements to Cartesian position and velocity.

Parameters:

• coe – Classical orbital elements [km, –, rad, rad, rad, rad]

• GM – Gravitational parameter [km^3/s^2]

• coe – Classical orbital element state [a, e, i, RAAN, arg_periapsis, anomaly].

• GM – Gravitational parameter consistent with the semi-major-axis units.

Returns:

Cartesian state [km, km/s] O. Montenbruck and G. Eberhard, Satellite orbits: models, methods, and applications. Berlin : New York: Springer, 2000. doi: 10.1007/978-3-642-58351-3.

Returns:

Cartesian state in the same frame as coe.