In many satellite attitude control problems a desired trajectory is defined to be reached. Is the desired trajectory (in quaternion) the same as q_LVLH (a 4x1 matrix defined by orbital parameters)?
Any trajectory design of a spacecraft involves the knowledge of orbit and attitude both (i.e. position, velocity and orientation w.r.t an inertial frame of reference). Off course the desired trajectories are optimized for delta-V requirement for the transfer. There are many ways of attitude representations viz. Euler angles, Quaternions etc. and can be found in associated literature.....
I would suggest
1) "Fundamentals of Astrodynamics and Applications" by D A Vallado
2) "Spacecraft Attitude Determination and Control" by James Wertz and
3) "Orbital Mechanics" by V A Chobotov
Go through these and you will find your answer.
satellite attitude is defined with respect to references. LVLH is one the main reference frames and you can define your attitude with respect to it. e.g. for normal mode in which satellite is going to point toward nadir this frame is proper. what is your tracking aim exactly?
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