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%