does anyone knows how to write vector components inside matlab function?

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Alexandre Masson Vicente
编辑： per isakson 2016-1-21
I tried to create a simulink block with embedded code through "matlab function":
function xdot = fcn(m,J,u,x)
%#codegen
R = [cos(x(8))*cos(x(9)) cos(x(8))*sin(x(9)) -sin(x(8));
-cos(x(7))*sin(x(9))+sin(x(7))*sin(x(8))*cos(x(9)) cos(x(7))*cos(x(9))+sin(x(7))*sin(x(8))*sin(x(9)) sin(x(7))*cos(x(8));
sin(x(7))*sin(x(9))+cos(x(7))*sin(x(8))*cos(x(9)) -sin(x(7))*cos(x(9))+cos(x(7))*sin(x(8))*sin(x(9)) cos(x(7))*cos(x(8))];
%
M = [1 sin(x(7))*tan(x(8)) cos(x(7))*tan(x(8));
0 cos(x(7)) -sin(x(7)) ;
0 sin(x(7))*sec(x(8)) cos(x(7))*sec(x(8))];
%
Wskew = [ 0 -x(12) x(11);
x(12) 0 -x(10);
-x(11) x(10) 0 ];
%
Vb = [x(4);
x(5);
x(6)];
%
W = [x(10);
x(11);
x(12)];
%
xdot=[R*Vb;
F-Wskew*Vb;
M*W;
J\(N-Wskew*J*W];
But matlab does not interpret the entries of vector "x" to form the matrices "W", "Vb", "R" and "Wskew".
DOES ANYONE HAVE ANY IDEA THAT I CAN TRY ON THIS PROBLEM?
Thanks.
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Alexandre Masson Vicente
Alexandre Masson Vicente 2016-1-21
编辑：per isakson 2016-1-21
Sorry, guys. I wrote the code with some errors. The program worked!
function xdot = fcn(m,J,u,x)
%#codegen
% atitude da aeronave na sequência 321 (projeta as medidas do INERCIAL no CORPO)
R = [cos(x(8))*cos(x(9)) cos(x(8))*sin(x(9)) -sin(x(8));
-cos(x(7))*sin(x(9))+sin(x(7))*sin(x(8))*cos(x(9)) cos(x(7))*cos(x(9))+sin(x(7))*sin(x(8))*sin(x(9)) sin(x(7))*cos(x(8));
sin(x(7))*sin(x(9))+cos(x(7))*sin(x(8))*cos(x(9)) -sin(x(7))*cos(x(9))+cos(x(7))*sin(x(8))*sin(x(9)) cos(x(7))*cos(x(8))];
%
% transformação das velocidades angulares nas taxas dos ângulos de euler
M = [1 sin(x(7))*tan(x(8)) cos(x(7))*tan(x(8));
0 cos(x(7)) -sin(x(7)) ;
0 sin(x(7))*sec(x(8)) cos(x(7))*sec(x(8))];
%
% matriz anti-simétrica de velocidades angulares (componentes no CORPO)
Wskew = [ 0 -x(12) x(11);
x(12) 0 -x(10);
-x(11) x(10) 0 ];
%
% vetor velocidade do centro de massa da aeronave escrito no CORPO
Vb = [x(4);
x(5);
x(6)];
%
% vetor velocidade angular da aeronave escrito no CORPO
W = [x(10);
x(11);
x(12)];
%
% vetor soma das forças externas aplicadas ao veículo
F = [u(1);
u(2);
u(3)]
%
% vetor soma dos torques externos em torno do baricentro da aeronave
N = [u(4);
u(5);
u(6)];
%
% Dinâmica do Corpo Rígido descrita em ESPAÇO DE ESTADOS, xdot = f(x,u,t)
xdot=[R*Vb; % velocidade escrita no INERCIAL
F-Wskew*Vb; % aceleração escrita no CORPO
M*W; % rapidez com que variam os ângulos de euler
J\(N-Wskew*J*W)]; % aceleração angular escrita no CORPO

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