136
V. A. Obukhov et al.
calculations. To maintain an average distance of 20 m, a thrust is required that is
higher than that produced by the considered EPS.
Using the simulation model for the IB impact on SDO, one can conduct qualitative
analysis for the process of the SDO removal from GEO for various values of the
parameters of control algorithms, simulation model, and SSC. The dependencies
shown in Fig. 10.2 were obtained using the algorithm for controlling the EPT rotation
that was considered in this chapter.
10.5.3 Parameters of Spacecraft Motion Dynamics
in the Process of SDO Removal from GEO
In Figs. 10.3, 10.4, 10.5 and 10.6 showing the changes in the parameters of the SSC
motion dynamics during the SDO removal from the GEO region, the average range
is 30 m, and the period of the oscillatory component of the effective radius of the IB
Fig. 10.3 Projections of the SSC acceleration (mm/s 2 )
Fig. 10.4 Projections of total momentum (Nm s)
V. A. Obukhov et al.
calculations. To maintain an average distance of 20 m, a thrust is required that is
higher than that produced by the considered EPS.
Using the simulation model for the IB impact on SDO, one can conduct qualitative
analysis for the process of the SDO removal from GEO for various values of the
parameters of control algorithms, simulation model, and SSC. The dependencies
shown in Fig. 10.2 were obtained using the algorithm for controlling the EPT rotation
that was considered in this chapter.
10.5.3 Parameters of Spacecraft Motion Dynamics
in the Process of SDO Removal from GEO
In Figs. 10.3, 10.4, 10.5 and 10.6 showing the changes in the parameters of the SSC
motion dynamics during the SDO removal from the GEO region, the average range
is 30 m, and the period of the oscillatory component of the effective radius of the IB
Fig. 10.3 Projections of the SSC acceleration (mm/s 2 )
Fig. 10.4 Projections of total momentum (Nm s)