forked from Archive/PX4-Autopilot
30 lines
1006 B
Matlab
30 lines
1006 B
Matlab
% define roll, pitch and yaw variables
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syms roll pitch yaw 'real'
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% Define yransformaton matrices for rotations about the X,Y and Z body axes
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Xrot = [1 0 0 ; 0 cos(roll) sin(roll) ; 0 -sin(roll) cos(roll)];
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Yrot = [cos(pitch) 0 -sin(pitch) ; 0 1 0 ; sin(pitch) 0 cos(pitch)];
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Zrot = [cos(yaw) sin(yaw) 0 ; -sin(yaw) cos(yaw) 0 ; 0 0 1];
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% calculate the tranformation matrix from body to navigation frame resulting from
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% a rotation in yaw, roll, pitch order
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Tbn_312 = transpose(Yrot*Xrot*Zrot)
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% convert to c code and save
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ccode(Tbn_312,'file','Tbn_312.c');
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fix_c_code('Tbn_312.c');
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% define the quaternion elements
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syms q0 q1 q2 q3 'real'
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% calculate the tranformation matrix from body to navigation frame as a
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% function of the quaternions
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Tbn_quat = Quat2Tbn([q0;q1;q2;q3]);
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% collect the y,x terms required for calculation of the yaw angle
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yaw_input_312 = [-Tbn_quat(1,2);Tbn_quat(2,2)];
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% convert to c code and save
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ccode(yaw_input_312,'file','yaw_input_312.c');
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fix_c_code('yaw_input_312.c');
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