Path: Missions/Comsat
% Performs a spin precession maneuver. -------------------------------------------------------------------------- Form: [fuelUsed, qECIToBody] = SPMMnvr( p, tId, pulsewidth, jD, inertia, cM, w, rAI, decI, rAF, decF, database ) -------------------------------------------------------------------------- ------ Inputs ------ p (1,:) Thruster pressure (psia) tId (1,:) Thruster ids pulsewidth (1,1) Pulsewidth for all thrusters jD (1,1) Julian date inertia (3,3) Spacecraft inertia cM (3,1) Spacecraft center-of-mass w (3,1) Initial body rate rAI (1,1) Initial right ascension (rad) decI (1,1) Initial declination (rad) rAF (1,1) Final right ascension (rad) decF (1,1) Final declination (rad) database (1,:) Database to use -------- Database -------- 'SSA Boresight Vector' 'REA Rise Time' 'REA Fall Time' 'Spin Axis' 'SSA FOV' 'SSA Boresight Vector' 'SSA Aperture Vector' 'r thruster' 'u thruster' 'REA Model' ------- Outputs ------- fuelUsed (1,n) Fuel used per thruster qECIToBody (4,:) The ECI to body quaternion --------------------------------------------------------------------------