MATLAB Simulation of variable-mass rigid-body 6DOF

% SIXDOFVM Calculate aircraft variable-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
% dMass = mass rate of change for the aircraft
% dInertia = 3x3 Inertia Tensor matrix rate of change
% 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
% Imass = initial mass of aircraft
% IInertia = initial 3x3 Inertia Tensor matrix
% 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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