Struct EphemerisOrbitConfig

• Defined in File ephemeris_simulation.h

Struct Documentation

struct EphemerisOrbitConfig

Initial classical orbital elements for the truth trajectory sampled by EphemerisSimulation (e.g. a lunar Elliptical Frozen Orbit).

Public Members

double a_m = 6541.4e3

double ecc = 0.6

double inc_rad = 56.2 * RAD

double raan_rad = 0.0

double argp_rad = 90.0 * RAD

double m0_rad = 0.0

Frame coe_frame = Frame::MOON_OP

Frame the elements above are defined in (e.g. Frame::MOON_OP for a frozen-orbit definition); converted to EphemerisSimulationConfig:: / propagate_frame at start_epoch_utc.