CL_fo_thirdBodyAcc

Description

• Perturbing (differential) acceleration (relative to an inertial frame) 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.

Parameters

pos:

Position vector (from central body) [m]. (3xN or 3x1)

pos_b:

Position vector of third body (from central body) [m]. (3xN or 3x1)

mu_b:

Gravitational constant of third body [m^3/s^2]. (1x1)

acc:

Acceleration [m/s^2]. (3xN)

Authors

• CNES - DCT/SB

See also

• CL_fo_thirdBodyPot

Examples

pos = [7000.e3; 0; 0]; pos_sun = CL_eph_sun(CL_dat_cal2cjd(2000,3,21)); mu_sun = CL_dataGet("body.Sun.mu"); CL_fo_thirdBodyAcc(pos, pos_sun, mu_sun)