Examples
pos = [6378.e3; 0; 0]; vel = [0; 7000.; 0]; omega = [0; 0; 1] * 5.e-12; // 1 deg / century CL_fo_apparentAcc(pos, vel, omega) |  |  |
Apparent acceleration (non-inertial frame)
[acc] = CL_fo_apparentAcc(pos, vel, omega, omegadot)
Acceleration due to the "non inertiallity" of the frame. ("rotation" accelerations only, i.e. Coriolis + centrifugal force)
Notes:
- The origin for the position vector must be the central body (there is no acceleration of the origin of the frame considered).
- The coordinates frame can be any frame.
- omega is the angular velocity vector of the (current) frame (noted R) with respect to an inertial (i.e. not rotating) frame (noted R0).
- All vectors have coordinates in frame R.
- If vel or omegadot are empty, they are considered as [0;0;0].
See Force models for more details.
Position vector [m]. (3xN or 3x1)
Velocity vector (relative to frame R) [m/s]. (3xN or 3x1)
Angular velocity vector of frame R with respect to frame R0 [rad/s]. (3xN or 3x1)
(optional) Time derivative (in frame R0) of omega [rad/s^2]. Default is [0;0;0] (3xN or 3x1)
Acceleration [m/s^2]. (3xN)
CNES - DCT/SB
pos = [6378.e3; 0; 0]; vel = [0; 7000.; 0]; omega = [0; 0; 1] * 5.e-12; // 1 deg / century CL_fo_apparentAcc(pos, vel, omega) | | |