Prime Keys are: DATE_OBS is slotted 'ts_eq' using DATE_OBS_index DB Index Keys are: DATE_OBS_index All Keywords for series iris.pointing_data: DATE_OBS (time) DATE_OBS DATE_OBS_epoch (time) DATE_OBS_epoch DATE_OBS_step (float) DATE_OBS_step DATE (time) DATE and TIME of processing:ISO 8601 TFLAG (short) Flag indicating valid data TIME_QBI (time) (TIME_QBI); Packet time of the quaterion parameters A_QBI_AST_X (float) (AQBIASTX); inertial to body frame quaternion, X component A_QBI_AST_Y (float) (AQBIASTY); inertial to body frame quaternion, Y component A_QBI_AST_Z (float) (AQBIASTZ); inertial to body frame quaternion, Z component A_QBI_AST_S (float) (AQBIASTS); inertial to body frame quaternion, S component TIME_POS_VEL (time) (TIME_POS); Packet time of the position, velocity and angle info A_EP_POS_J2000_X (float) (AEP_POSX); spacecraft position vector, (J2000), X component A_EP_POS_J2000_Y (float) (AEP_POSY); spacecraft position vector, (J2000), Y component A_EP_POS_J2000_Z (float) (AEP_POSZ); Spacecraft position vector, (J2000), Z component A_EP_VEL_J2000_X (float) (AEP_VELX); Spacecraft velocity vector, (J2000), X component A_EP_VEL_J2000_Y (float) (AEP_VELY); spacecraft velocity vector, (J2000), Y component A_EP_VEL_J2000_Z (float) (AEP_VELZ); spacecraft velocity vector, (J2000), Z component A_EULERBR_X (float) (AEULRBRX); Euler Angle Sun ref to S/C body frame, X component A_EULERBR_Y (float) (AEULRBRY); Euler Angle Sun ref to S/C body frame, Y component A_EULERBR_Z (float) (AEULRBRZ); Euler Angle Sun ref to S/C body frame, Z component OPHASE (float) Orbital Phase TIME_CG_ROLL (time) (TIMEROLL); Packet time of the CG_ROLL_ANGLE parameter A_CG_ROLL_ANGLE (float) (ACG_ROLL); Roll profile commanded angle from solar north pole