Examples
pos = [6378.e3; 0; 0]; CL_fo_centralAcc(pos) |  |  |
Acceleration due to gravity (central force)
[acc] = CL_fo_centralAcc(pos [, mu])
Acceleration (relative to an inertial frame) due to the central force (Newtonian acceleration).
It is directed from the central body to the satellite, and is inversely proportional to the distance squared.
Notes:
- The origin for the position vector must be the central body.
- The coordinates frame can be any frame.
See Force models for more details.
Position vector (from the central body) [m]. (3xN)
(optional) Gravitational constant [m^3/s^2]. Default value is %CL_mu. (1x1)
Acceleration [m/s^2]. (3xN)
CNES - DCT/SB
pos = [6378.e3; 0; 0]; CL_fo_centralAcc(pos) | | |