Path: Missions/SunNadir
% Spacecraft sun-nadir RHS with 4 RWA's and 2 solar arrays. -------------------------------------------------------------------------- Form: xDot = RHSSNP( x, t, inr, invInr, tExt, inrW, uW, tW, eSAC ) -------------------------------------------------------------------------- ------ Inputs ------ x (15,1) The state vector t Time inr (3,3) Inertia invInr (3,3) Inverse inertia tExt (3,1) External torque inrW (6) [SA,RWA] inertias uW (3,6) [SA,RWA] unit vectors tW (6) [SA,RWA] torque eSAC (2) Solar array commanded angle (always one step) ------- Outputs ------- xDot (15,1) The derivative of the state vector -------------------------------------------------------------------------- See also GSModel, SunNadirPointingSim --------------------------------------------------------------------------
AerospaceUtils: Coord/QIToBDot SC: Dynamics/GSModel
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