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

Parameters:

  • 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:

Vec3 Total acceleration vector on the spacecraft.