Economical attitude and orbit control of information satellites by electromechanical, magnetic and plasma drivers

Attitude guidance and control of land-survey mini-satellite

“…Then required pulse L p n of the MD electromagnetic moment vector is computed as L p n ≡ {l p in } = (b n × M pm n )/||B n ||, there are defined values s in = sign l p in ,τ in = l p in /l m and if max(τ in ) =τ m in ≥ T m u then τ in = (T m u /τ m in )τ in . Values s in and τ in are applied for the MD pulse-width control, that results in its energy economy [3], [4].…”