Acceleration due to gravity (third body)
[acc] = CL_fo_thirdBodyAcc(pos, pos_b, mu_b)
Acceleration due to third body.
It is equal to the gravity acceleration acting on the satellite minus the gravity acceleration acting on the central body.
Notes:
- The origin for all position vectors must be the central body.
- The coordinates frame can be any frame.
See Force models for more details.
Position vector (from central body) [m]. (3xN or 3x1)
Position vector of third body (from central body) [m]. (3xN or 3x1)
Gravitational constant of third body [m^3/s^2]. (1x1)
Acceleration [m/s^2]. (3xN)
CNES - DCT/SB