Efficiency of Hysteresis Rods in Small Spacecraft Attitude Stabilization

Figure 13

Variation of the damping time, 𝑡_𝑑, with the diameter, 𝑑, of the CCSR (Delfi-C3 design), and thickness, 𝑡, for TFRs (proposed option), for Delfi-C3 satellite. Rhombi: in-orbit data. Max and min correspond to 𝜇_𝑖=3.8×10⁻³ Tm/A, and 𝜇_𝑖=12.6×10⁻³ Tm/A, respectively.