Declared in GuidanceSunPointingMessage
Declaration
Vector3 Omega_RN_B;Description
The attitude rate in the body frame when the spacecraft is in eclipse. This is relative between the reference point R and the inertial point N in the body frame B.
Declared in GuidanceSunPointingMessage
Vector3 Omega_RN_B;The attitude rate in the body frame when the spacecraft is in eclipse. This is relative between the reference point R and the inertial point N in the body frame B.