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Hi Bill
I have been trying to write a matlab code using the dcm imu theory. i had one question though. Is yaw angle and heading of the aircraft same? As in isnt it possible for and aircraft to point in one direction and have an overall heading in another... if so is there anyway to find the heading from the pitch, roll and yaw?
Regards
Naomi
Naomi,
Yaw angle is heading, which is the direction the aircraft is pointing, which is not the same as which direction the aircraft is moving (course over ground) because of the wind. You can compute one from the other if you know the airspeed of the aircraft and the wind vector.
The earliest version of MatrixPilot used GPS course over ground for navigation, which does not need to concern itself with the wind. However, GPS has latency.
So, we switched to heading, because that comes from IMU without latency. But for that you need to compensate for wind.
Two years ago we were able to achieveIMU "dead reckoning", which provides course over ground without any latency. So we switched back to course over ground for navigation in MatrixPilot, providing better navigation performance.
Best regards,
Bill
Hey Bill
Thank you so much for your reply. It makes sense now. Been looking for this answer everywhere. Thanks a lot.
Regards
Naomi
Dear Bill
I'm reading your perfect paper(DcmDraft2)
please let me ask a problem if I may.
in the paper, we got "a convenient matrix form" in Eqn 17
we know the new "DCM“ is not a definite DCM for its magnitude is not 1 ,and each vector member is not orthogonality.so the next step is "Renormalization"
In my understand ,although we get a new definite DCM after renormalization,but it is still an approximate one to the true accurate dcm. anyway this renormalized DCM is acceptable in such a little time slice(eg: 0.02s)
However, I wonder that there will be an apparent error(or deviation) after a long time 's calculation.
(we assume that the gyro output is very accurate)
I mean every renormalization process will create deviation,and these deviation will accumulate into a "big" DCM error.
Is it possible?
sorry for my poor english.
Thanks.
Dear Bill
quote:
the bottom row of the direction cosine matrix should be aligned with the vector produced by the accelerometers
May I know the reason why these two vectors should be aligned ?under what condition?
because,from the earth frame. the plane also can own an acceleration other than the Z-axis(earch reference). it is a normal case i think.
so i am confused why we know it is a gyro drift when there two vectors are not aligned
maybe gyro has no drift ,and currently the plane is accelerating in some direction .therefore
the accelerateometer's output is also not aligned to earth Z-axis
Thanks
Dear
Regarding the Eqn 26 in the paper(DcmDraft2)
I think
the acceleromter is aligned with the plane(body).so its output is the combination result of gravity and centrigual acceleration.
and we only need the gravity acceleration as our reference vector.
so the equation should be (Vector) as follows?
g_reference = Acceleration - centrigual acceleration
I confused with the Eqn26
Thanks.
Additions:
for example. the x-axis has the whole Centrigual acceleration(Vector C). the Gravity works in z-axis (Vector G)
under this condition. the Accelerometer will output the result Vetor A = C + G
so if we want to get the G, we need A-C,but the Eqn.26 shows G= A+C
may I know the reason?
sorry for the stupid question .
I have known it .
the sign is negative if exchange the cross product of them
Johnson,
Thanks for your questions.
Regarding renormalization introducing drift, in practice, it does not create much drift. I have done static (motionless) tests on the UDB5 hardware with drift correction turned off and measured the residual drift from all sources (such as noise, renormalization, offset shift) to be on the order of one degree per minute. There are much larger sources of error in flight due to gyro calibration errors. See for example:
http://diydrones.com/profiles/blogs/sustained-rotations-pushing
In any case, you need to apply continual drift compensation in flight to prevent accumulation of attitude estimation error. This is done with the aid of known reference vectors.
Regarding the bottom row of the matrix, it represents the image of the earth vertical axis in the body frame. You can use the accelerometer as a reference vector for vertical if you compensate for centrifugal acceleration. There are a couple of ways of doing that, DCMDraft2 describes one way to do it, the following describes another way:
http://diydrones.com/forum/topics/an-improved-method-for-accounting...
Regarding the interpretation of the sign of the accelerometer data, depending on your preference, you can think of it as producing gravity minus acceleration, or acceleration minus gravity. I have been told by some of the members of the MatrixPilot team that the way that I think of it is opposite to the rest of the world, so I apologize if I have confused you.
Finally, here is another source of information on this subject, it is nicely organized, fun to read and easy to understand:
http://www.starlino.com/dcm_tutorial.html
Best regards,
Bill
Dear
Thanks very much for your elaborate answer.
I can understand it now.
Thanks
Dear I reviewed the Eqn14~17 which someone feels confused maybe. would it be better if we add some tips or comments about this setction
1. the θ(x/y/z) in the matrix of Eqn 17 stands for the magnitude of the Vector : dt * W(x/y/z) X r(t)
not the angel between the r(t) and r(t+dt)
while the definite DCM use the cosin of this angle.
2. I draw a draft and try to distinguish them
and I am not sure it is correct but i think so. I hope this will help other readers
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