Abstract: The problem of flight vehicle relative attitude motion treatment is studied in detail in this paper. Three methods are presented for getting relative attitude of flight vehicle, the first one is statical, the second one is kinematical and the last one is dynamical. A theorem called theorem of composition of angular acceleration is specially derived as basis for dynamic method of relative attitude . The results can be used in the analytical study and numerical simulation of flight vehicle relative attitude motion and also provide the basis for the problem of guidance and control of flight vehicle relative motion for the future.