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License: Freeware \$0.00 30 Windows /Linux/Mac OS/BSD/Solaris 2010-06-24 2 KB Stacey Gage
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### Publisher description for MATLAB simulation of fixed-mass rigid-body 6DOF

% SIXDOF Calculate aircraft fixed-mass rigid-body six-degrees-of-Freedom % equations of motion using MATLAB ODE45 solver. % % =-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-= % Inputs: % =-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-= % Forces = 3x1 vector of forces in body coordinates % Moments = 3x1 vectory of moments in body coordinates % Mass = fixed mass of the aircraft % Inertia = 3x3 Inertia Tensor matrix % tarray = time series vector % % OPTIONAL INPUTS: % Ipos_i = 3x1 vector of initial position % Ivel_b = 3x1 vector of initial velocity (body) % Irates_b = 3x1 vector of initial body rates % Ieuler = 3x1 vector of initial euler angles % % =-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-= % Outputs: % =-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-=-= % t = simulation time % y(1:3) = body rates % y(4:6) = velocity in body coordinates % y(7:9) = position in body coordinates %