px4-firmware/EKF/matlab/scripts/Inertial Nav EKF/Tbn_312.c

16 lines
293 B
C

t2 = sin(yaw);
t3 = cos(yaw);
t4 = sin(pitch);
t5 = cos(pitch);
t6 = sin(roll);
t7 = cos(roll);
A0[0][0] = t3*t5-t2*t4*t6;
A0[0][1] = -t2*t7;
A0[0][2] = t3*t4+t2*t5*t6;
A0[1][0] = t2*t5+t3*t4*t6;
A0[1][1] = t3*t7;
A0[1][2] = t2*t4-t3*t5*t6;
A0[2][0] = -t4*t7;
A0[2][1] = t6;
A0[2][2] = t5*t7;