Function lupnt::CartToClassical(Real, const State&, const State&, Real)

Function Documentation

State lupnt::CartToClassical(Real dt, const State &r1, const State &r2, Real GM)

Compute the classical orbital elements from two position vectors and the time difference between them.

Estimate classical orbital elements from two Cartesian position states.

Parameters:

  • dt – Time difference between the two position vectors [s]

  • r1 – Initial position vector [m]

  • r2 – Final position vector [m]

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

  • dt – Time elapsed between r1 and r2.

  • r1 – First position state.

  • r2 – Second position state.

  • GM – Gravitational parameter consistent with the state units.

Returns:

Classical orbital elements [m, –, rad, rad, rad, rad] 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:

Classical orbital element state.