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PX4-Autopilot/EKF/matlab/scripts/Inertial Nav EKF/yaw_input_312.c
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2018-05-03 22:25:36 -04:00

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A0[0][0] = q0*q3*2.0-q1*q2*2.0;
A0[1][0] = q0*q0-q1*q1+q2*q2-q3*q3;