Function lupnt::AccelerationDrag

• Defined in File forces.h

Function Documentation

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

Computes the acceleration due to atmospheric drag.

Parameters:

• 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:

Vec3 Acceleration vector due to atmospheric drag.