Why do i recieve Dot indexing is not supported for variables of this type error when i call my function

I'm trying to implement a aircraft model.

I created a struct for aircraft data's

When i trying to implement my eom function i'm getting this error

Dot indexing is not supported for variables of this type.

Error in eom (line 4)

m = spec.m.table{1};

Error in odearguments (line 92)

f0 = ode(t0,y0,args{:}); % ODE15I sets args{1} to yp0.

Error in ode45 (line 107)

odearguments(odeIsFuncHandle,odeTreatAsMFile, solver_name, ode, tspan, y0, options, varargin);

Error in flight (line 25)

[t, vecste,spec,aero,thrust] = ode45('eom', tspan, stvecinit);

How can i solve it

Thanks

Answer 1

[Torsten]

Use

[t, vecste] = ode45(@(t,vecste)eom(t,vecste,spec,aero,thrust), tspan, stvecinit);

instead of

[t, vecste,spec,aero,thrust] = ode45('eom', tspan, stvecinit);

run('database.m')

% For Initial Values
uinit = 50;
vinit = 0;
winit = 1;
pinit = 0;
qinit = 0;
rinit = 0;
phiinit = 0;
thetainit = 0;
psiinit = 0;
xinit = 0;
yinit = 0;
H = 3000;
zinit = -H;

tspan = [0 3];
stvecinit = [uinit vinit winit pinit qinit rinit phiinit thetainit psiinit xinit yinit zinit];
[t, vecste] = ode45(@(t,vecste)eom(t,vecste,spec,aero,thrust), tspan, stvecinit);

alpha = 0.0200

atmosphere requires Radar Toolbox.

Error in solution>eom (line 108)
[density,temperature,pressure] = atmosphere(h);

Error in solution>@(t,vecste)eom(t,vecste,spec,aero,thrust) (line 22)
[t, vecste] = ode45(@(t,vecste)eom(t,vecste,spec,aero,thrust), tspan, stvecinit);

Error in odearguments (line 92)
f0 = ode(t0,y0,args{:}); % ODE15I sets args{1} to yp0.

Error in ode45 (line 104)
odearguments(odeIsFuncHandle,odeTreatAsMFile, solver_name, ode, tspan, y0, options, varargin);

%% Results Calculations
u = vecste(:,1);
v = vecste(:,2);
w = vecste(:,3);
p = vecste(:,4);
q = vecste(:,5);
r = vecste(:,6);
phi = vecste(:,7)*180/pi;
theta = vecste(:,8)*180/pi;
psi = vecste(:,9)*180/pi;
xx = vecste(:,10);
y = vecste(:,11);
z = vecste(:,12);

V = sqrt(u.^2+v.^2+w.^2);
alpha = atand(w./u);
beta = asin(v./V);


figure (1)
plot(t,alpha, 'LineWidth', 1.5)
grid on; grid minor
title('Variation of AoA with Time')
xlabel('Time (in sec)')
ylabel('AoA (in degrees)')

figure (2)
plot(t,beta, 'LineWidth', 1.5)
grid on; grid minor
title('Variation of pitch attitude with time')
xlabel('Time (in sec)')
ylabel('\theta (in degrees)')

figure (3)
plot(t,V, 'LineWidth', 1.5)
grid on; grid minor
title('Variation of Velocity with Time')
xlabel('Time (in sec)')
ylabel('Velocity (in m/sec)')

figure (4)
plot(xx,-z, 'LineWidth', 1.5)
grid on; grid minor
title('X vs Z')
xlabel('X (in m)')
ylabel('Z (in m)')

figure (5)
plot3(xx,y,-z, 'LineWidth', 1.5)
grid on; grid minor
title('3-D plot of the Trajectory')
xlabel('X (in m)')
ylabel('Y (in m)')
zlabel('Z (in m)')

function x = eom(t,vecste,spec,aero,thrust)


m = spec.m.table{1};
g = spec.g.table{1};
Ixx = spec.Ixx.table{1};
Iyy = spec.Iyy.table{1};
Izz = spec.Izz.table{1};
Ixz = spec.Ixz.table{1};

u = vecste(1);
v = vecste(2);
w = vecste(3);
p = vecste(4);
q = vecste(5);
r = vecste(6);
phi = vecste(7);
theta = vecste(8);
psi = vecste(9);
xx = vecste(10);
y = vecste(11);
z = vecste(12);
h = -z;
V = sqrt(u^2+v^2+w^2);

alpha = atan(w/u)
beta = asin(v/V);
V = sqrt(u^2+v^2+w^2);

[density,temperature,pressure] = atmosphere(h);

[Thrust] = thrustmodel(V, density,thrust);

[Fax,Fay,Faz,Mx,My,Mz] = aeromodel(p,q,r,V,alpha,beta,aero,spec,density);


[FGx,FGy,FGz] = weightmodel(phi,theta,psi,spec);


%Forces

X = Fax + FGx+Thrust;
Y = Fay + FGy;
Z = Faz + FGz;

% Moments already defined with same name using aeromodel function(Mx,My,Mz)


% 1. Translational Dynamics
udot = X/m-g*sin(theta)-q*w+r*v;
vdot = Y/m+g*sin(theta)*sin(phi)-r*u+p*w;
wdot = Z/m+g*cos(theta)*cos(phi)-p*v+q*u;

% 2. Rotional Dynamics

pdot = Mx/Ixx + ((Iyy-Izz) * (q*r/Ixx)); %+ (( (x(6,1) + p*q) /Ixx )*Ixz);
qdot = My/Iyy + ((Izz-Ixx) * (r*p/Iyy)); %- ((p^2 + r^2)/Iyy)*Ixz;
rdot = Mz/Izz + ((Ixx-Iyy) * (p*q/Izz)); %- ((q*r-x(4,1))/Izz)*Ixz;


% Euler dots
attmatrix = [    1           tan(theta)*sin(phi)     cos(phi)*tan(theta);
                 0           cos(phi)                -sin(phi)      ;
                 0           sec(theta)*sin(phi)     sec(theta)*cos(phi) 
];
omega = [p;q;r];
attvec = attmatrix*omega;
phidot = attvec(1);
thetadot = attvec(2);
psidot = attvec(3);

% x y z 

vector = [u;v;w];
transvector = ned2body(phi,theta,psi);
accvector = transvector*vector;
xdot = accvector(1);
ydot = accvector(2);
zdot = accvector(3);


x(1,1) = udot;
x(2,1) = vdot;
x(3,1) = wdot;
x(4,1) = pdot;
x(5,1) = qdot;
x(6,1) = rdot;
x(7,1) = phidot;
x(8,1) = thetadot;
x(9,1) = psidot;
x(10,1)= xdot;
x(11,1)= ydot;
x(12,1)= zdot;
end

[Muhammed Emin Yavuzaslan]

That's worked Thanks a lot.

But i would you like to know what is the main difference in this lines;

[t, vecste] = ode45(@(t,vecste)eom(t,vecste,spec,aero,thrust), tspan, stvecinit);

instead of

[t, vecste,spec,aero,thrust] = ode45('eom', tspan, stvecinit);

[Torsten]

Your command assumes that spec,aero,thrust are outputs from ode45. But they are your (additional) inputs (to function "eom").

Answer 2

[Florian Bidaud]

try with m = spec{1}.m.table or m = spec.m{1}.table

[Muhammed Emin Yavuzaslan]

when i'm try m = spec{1}.m.table im getting this error ,

Brace indexing is not supported for variables of this type.

Error in eom (line 5)

m = spec{1}.m.table;

When i try to other one

Dot indexing is not supported for variables of this type.

Error in eom (line 5)

m = spec.m{1}.table;

İm getting this error again.

What should i do ?

[Florian Bidaud]

Sorry I read too quickly. the format of spec.m.table is probably a cell array.

Can you show the variable in the workspace ?

I suspect spec.m.table(1) will work.

[Muhammed Emin Yavuzaslan]

Here the workspace.

I dont know why my structure has "ans" name

maybe run('database.m') doesn't works