Create a flat plate vehicle with two flaps

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See also BuildCADModel, CreateBody, CreateComponent, PlateTwoSided,
SaveStructure.
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%-------------------------------------------------------------------------------
%   Copyright (c) 2011 Princeton Satellite Systems, Inc. All rights reserved.
%-------------------------------------------------------------------------------


% Initialize the CAD GUI
%-----------------------
BuildCADModel( 'initialize' );

m = CreateBody( 'make', 'name', 'Core' );
BuildCADModel('add body', m );

% Add spacecraft properties
%--------------------------
BuildCADModel( 'set name' ,  'FlatPlateAircraft' );
BuildCADModel( 'compute paths' );

% Wing
%-----
b  = 12.8*2;
x  = [27.66 1 1 0 0 1 1];
y  = [0 b/2 1 1 -1 -1 -b/2];
zT =  0.1;
zB = -0.1;
vW = [x' y' zT*ones(7,1);x' y' zB*ones(7,1)];
fW = [ 1 3 2;...
       1 6 3;...
       1 7 6;...
       6 4 3;...
       6 5 4];

vWN = vW;
vWN(:,2) = -vWN(:,2);
f = [fW;fliplr(fW)+size(vW,1)];

v = [vW;vWN];

lF = 1;
wF = 11.8;


m = CreateComponent( 'make', 'generic','name', 'Fuselage', 'body', 1,...
                     'rA',[0;0;0],'b',eye(3),...
					 'vertex', v,'face', f,'faceColor', 'aluminum' );
BuildCADModel('add component', m );


% Flaps
%------
[v, f] = PlateTwoSided( [0 lF lF 0], [0 0 wF wF], 0 );

x =  0;
y =  1;

m = CreateComponent( 'make', 'generic','name', 'Flap1', 'body', 1,...
                     'rA',[x;y;zT],'b',eye(3),...
					 'vertex', v,'face', f,'faceColor', 'steel' );
BuildCADModel('add component', m );

m = CreateComponent( 'make', 'generic','name', 'Flap2', 'body', 1,...
                      'rA',[x;-y-wF;zT],'b',eye(3),...
					 'vertex', v,'face', f,'faceColor', 'steel' );
BuildCADModel('add component', m );

d.cadModel              = BuildCADModel('get model');

ax    = [0 0  0;...
         1 1  1;...
         0 0  0];


r     = [5    0.5  0.5;...
         0    1.5 -1.5;...
         0    0    0];


s = zeros(3,1);

c = [0;0;0];

for k = 1:3
    s(k) = sum(d.cadModel.component(k).a)/2;
    c    = c + r(:,k)*s(k);
end

d.rCM = c/sum(s);

k = 1;

x = [1;0;0];

% Aspect ratios
%--------------
aR  = b^2/sum(s);
aRA = wF^2/s(2);

% Thickness ratio
%----------------
t   = 0.01;


d.surface(k) = struct('name', 'Wing',           'length', 1,'alpha0',0,'zeroAxis',x,...
                      'oswaldEff', 0.99, 'aspectRatio', aR, 'thickness', t, 's', s(1), ...
                      'r', r(:,1),'axis',ax(:,k), 'cP', 0.002); k = k + 1;

d.surface(k) = struct('name', 'Left aileron',       'length', 1,'alpha0',0,'zeroAxis',x,...
                      'oswaldEff', 0.99, 'aspectRatio', aRA, 'thickness', t, 's', s(2), ...
                      'r', r(:,2),'axis',ax(:,k), 'cP', 0); k = k + 1;

d.surface(k) = struct('name', 'Right aileron',      'length', 1,'alpha0',0,'zeroAxis',x,...
                      'oswaldEff', 0.99, 'aspectRatio', aRA, 'thickness', t, 's', s(3), ...
                      'r', r(:,3),'axis',ax(:,k), 'cP', 0);

SaveStructure(d,'FlatPlateAircraft');


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