Function lupnt::AccelerationDrag

Function Documentation

Vec3 lupnt::AccelerationDrag(Real mjd_tt, const Vec6 &rv, const Mat3 &T, Real bcoeff_drag)

Computes the acceleration due to the atmospheric drag.

Computes the acceleration due to atmospheric drag.

Parameters:

  • mjd_tt – Terrestrial Time (Modified Julian Date)

  • rv – Satellite position and velocity in the inertial system [km, km/s]

  • R – Transformation matrix to true-of-date inertial system

  • area – Cross-section [m^2]

  • mass – Spacecraft mass [kg]

  • CD – Drag coefficient

  • mjd_tt – Modified Julian Date (Terrestrial Time).

  • rv – State vector (position and velocity) of the spacecraft.

  • T – Transformation matrix from inertial to body frame.

  • bcoeff_drag – Ballistic coefficient for atmospheric drag.

Returns:

Acceleration [km/s^2] 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:

Vec3 Acceleration vector due to atmospheric drag.