Function lupnt::AccelerationEarthSpacecraft

Function Documentation

Vec3 lupnt::AccelerationEarthSpacecraft(Real mjd_tt, const Vec6 &rv, Real bcoeff_srp, Real bcoeff_drag, GravityField<Real> grav)

Computes the acceleration acting on a satellite orbiting the Earth.

Computes the total acceleration on a spacecraft due to Earth’s gravity, solar radiation pressure, and atmospheric drag.

Parameters:

  • mjd_tt – Terrestrial Time (Modified Julian Date)

  • rv – Satellite position and velocity in the inertial system [m]

  • area – Cross-section [m^2]

  • mass – Spacecraft mass [kg]

  • CR – Solar radiation pressure coefficient [N/m^2]

  • CD – Drag coefficient [-]

  • mjd_tt – Modified Julian Date (Terrestrial Time).

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

  • bcoeff_srp – Ballistic coefficient for solar radiation pressure.

  • bcoeff_drag – Ballistic coefficient for atmospheric drag.

  • grav – Gravity field model.

Returns:

Acceleration [m/s^2]

Returns:

Illumination factor [0,1], 0 if in shadow, 1 if fully illuminated 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 Total acceleration vector on the spacecraft.