Path: Missions/LunarLanding
% This function computes the matrices a and b for dx/dt = a*x + b*u . This is for the function RHSPlanet3D. If aL is entered it will use an analytical solution for a spherical planet. The mass state equation is not output. b multiplies the acceleration vector. Type RHSPlanet3DToAB for a demo. -------------------------------------------------------------------------- Form: [a,b,aC] = RHSPlanet3DToAB( x, d, dT ) -------------------------------------------------------------------------- ------ Inputs ------ x (6,1) [r;v] (km/km/s) d (.) Data structure for RHSPlanet3D dT (1,1) Time step ------- Outputs ------- a (6,6) State transition matrix b (6,3) Input matrix aC (6,6) Continuous --------------------------------------------------------------------------
AC: ACData/ACTConstants Missions: LunarLanding/RHSPlanet3D SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/xSplashSmall Common: Control/C2DZOH Common: Database/Constant Common: General/DeleteCell Common: General/DispWithTitle Math: Linear/Mag Math: Linear/Skew
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