MATLAB simulation of fixed-mass rigid-body 6DOF
by Stacey Gage
30 Apr 2003
(Updated 06 May 2003)
Calculate aircraft fixed-mass rigid-body six-degrees-of-freedom equations of motion using MATLAB ODE
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| File Information |
| Description |
% 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:
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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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| MATLAB release |
MATLAB 6.5 (R13)
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| 29 Nov 2012 |
Marine
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