Single thruster attitude control software simulator for spinning spacecraft

Slew Control of Prolate Spinners Using Single Magnetorquer

“…= angular momentum of spacecraft, that in reference inertial/spacecraft-fixed body coordinates, that after H t = the first actuation, that at end of the slew, and the target angular momentum, N · ms I, I z , I t = spacecraft moment of inertia matrix, moment of inertia of transverse axis/spin axis, kg · m 2 k = rotation number around spin axis of the spacecraft m = magnetic moment of the magnetorquer dipole, A · m 2 T, T magnet = control torque/ magnetic torque applied to the spacecraft, N · m t 0 , t 1f , t 2s , t 2f , t 1;2 , Δt 2 , t E XISTING research [1][2][3][4][5] on the prolate spinning spacecraft attitude maneuver has developed a series of slew algorithms using a single thruster in two categories: half-cone derived algorithms and pulse-train algorithms. Half-cone derived algorithms consist of half-cone (HC), multi-half-cone, dual-half-cone, extended half-cone, sector arc slew, and multisector arc slew, using the precession behavior of a spinning prolate spacecraft.…”