CARIOQA Quantum Pathfinder Mission Phase A orbit and accelerometer data

The data is provided in csv file format with file names according to the following convention: YYYY-MM-DD_VENQS_data_fileX_ORBIT_Fall_24h YYYY-MM-DD: date of creation of dataset fileX: filetype 1 or 2 (see following tables) ORBIT: orbit scenario ELLIP or CIRC The simulated data is provided for 24h starting on 22.09.2030 12:00 with a 4s sampling intervall. Data formats Filetype 1 This file includes satellite orbit information. Column Title Description 1 MJD [d] Time stamp as Modified Julian Date 2 pos. x [m]  x component of satellite position in ECI (i) frame (ICRF) 3 pos. y [m]  y component of satellite position in ECI (i) frame (ICRF) 4 pos. z [m]  z component of satellite position in ECI (i) frame (ICRF) 5 vel. x [m/s] x component of satellite velocity in ECI (i) frame (ICRF) 6 vel. y [m/s] y component of satellite velocity in ECI (i) frame (ICRF) 7 vel. z [m/s] z component of satellite velocity in ECI (i) frame (ICRF) 8 qs Scalar component of quaternion of satellite altitude 9 q1 1st imaginary part 10 q2 2nd imaginary part 11 q3 3rd imaginary part 12 omega x [rad/s] x-component of angular velocity in the satellite body frame (b) 13 omega y [rad/s] y-component of angular velocity in the satellite body frame (b) 14 omega z [rad/s] z-component of angular velocity in the satellite body frame (b) The provided quaternions transform a vector in ECI frame (i) into satellite body frame (b) Filetype 2 This filetype includes accelerations and gravity gradients data. Column Title Description 1 MJD [d] Time stamp as Modified Julian Date 2 Drag Acc-x [m/s^2] x-component of satellite acceleration due to atmospheric drag 3 Drag Acc-y [m/s^2] y-component of satellite acceleration due to atmospheric drag 4 Drag Acc-z [m/s^2] z-component of satellite acceleration due to atmospheric drag 5 SRP Acc-x [m/s^2] x-component of satellite acceleration due to solar radiation pressure 6 SRP Acc-y [m/s^2] y-component of satellite acceleration due to solar radiation pressure 7 SRP Acc-z [m/s^2] z-component of satellite acceleration due to solar radiation pressure 8 GG-matrix 1,1 [1/s^2] G11 9 GG-matrix 1,2 [1/s^2] G12 10 GG-matrix 1,3 [1/s^2] G13 11 GG-matrix 2,1 [1/s^2] G21 12 GG-matrix 2,2 [1/s^2] G22 13 GG-matrix 2,3 [1/s^2] G23 14 GG-matrix 3,1 [1/s^2] G31 15 GG-matrix 3,2 [1/s^2] G32 16 GG-matrix 3,3 [1/s^2] G33 The accelerations are provided in the satellite sensor frame. The gravity gradient matrix (GG) is defined at the centre of mass of the satellite in satellite body frame (b) with the components Gxy (x:row y:column).