Hi all,
I've posted quaternion questions on here before and I thank you all for your help. However, I am still a bit cofused so please bear with me. If I have an aircraft with an Euler Angle orientaiton of (yes, my aircraft can fly in this orientation)
Roll (phi, x-axis) = 0 degrees Pitch (theta, y-axis) = 90 degrees Yaw (psi, z-axis) = 20 degrees
and I measure this with a sensor, it will suffer from singularities which will yield erroneous results. However, that same sensor will yield the correct quaternion for that orientation:
Q = 0.696 + 0.123i + 0.696j + 0.123k
My question is how do I mathematically convert the quaternion (Q) back to Euler Angle format *while* still avoiding the singularities present at theta=90 degrees?
Thanks, weg