% SIXDOF Calculate aircraft fixed-mass rigid-body six-degrees-of-freedom 
% equations of motion using MATLAB ODE45 solver.
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% Inputs:
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% 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
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% 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
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% Outputs:
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% t = simulation time
% y(1:3) = body rates
% y(4:6) = velocity in body coordinates
% y(7:9) = position in body coordinates
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