Prospero999
2005-10-22
Hi all,
I'm writing a roll angle demand control loop for X-Plane (the flight simulation), but I'm coming up against what I suspect are the "usual problems" with a Euler Angles representation of attitude.
To start with, I should mention that X-Plane outputs roll, pitch and yaw as Euler angles. Roll has range +/-180 degrees. Pitch has range +/-90 degrees. Yaw has range +/-180 degrees. I should also mention that the roll demand control loop's error signal is generated by calculating "desired roll angle minus actual roll angle."
So, here's an example of the problem I'm having:
Let's say that the aircraft starts out flying straight and level (pitch is about 0 degrees) and then pulls up into an almost vertical climb (pitch is almost 90 degrees). Well, now the roll value is just about to flip over from 0 to 180 degrees, and becomes VERY noisy, which in turn means my error signal is very noisy and my control loop doesn't function nearly as well as it does when the aircraft is flying straight and level with pitch around 0.
I believe that quaternions may provide the answer, but I'm trying to work out how I actually use them to determine the roll error signal. I'm afraid I have only a little experience of quaternion mathematics.
X-plane outputs the aircraft's attitude as Euler Angles, so if one's going to work with quaternions, I presume that the first stage would be to convert from a Euler Angles representation of attitude to a quaternion representation of attitude thusly (note that roll, pitch and yaw are in degrees, and q1w, q1x, q1y and q1z are the four elements of the quaternion, and DEGTORAD is Pi/180):
q1w = Cos(roll * DEGTORAD / 2) * Cos(pitch * DEGTORAD / 2) * Cos(yaw * DEGTORAD / 2) + Sin(roll * DEGTORAD / 2) * Sin(pitch * DEGTORAD / 2) * Sin(yaw * DEGTORAD / 2)
q1x = Sin(roll * DEGTORAD / 2) * Cos(pitch * DEGTORAD / 2) * Cos(yaw * DEGTORAD / 2) - Cos(roll * DEGTORAD / 2) * Sin(pitch * DEGTORAD / 2) * Sin(yaw * DEGTORAD / 2)
q1y = Sin(roll * DEGTORAD / 2) * Cos(pitch * DEGTORAD / 2) * Sin(yaw * DEGTORAD / 2) + Cos(roll * DEGTORAD / 2) * Sin(pitch * DEGTORAD / 2) * Cos(yaw * DEGTORAD / 2)
q1z = Cos(roll * DEGTORAD / 2) * Cos(pitch * DEGTORAD / 2) * Sin(yaw * DEGTORAD / 2) - Sin(roll * DEGTORAD / 2) * Sin(pitch * DEGTORAD / 2) * Cos(yaw * DEGTORAD / 2)
And one can form the corresponding direction cosine matrix from the attitude quaternion like this:
m11 = q1w ^ 2 + q1x ^ 2 - q1y ^ 2 - q1z ^ 2
m12 = 2 * (q1x * q1y + q1w * q1z)
m13 = 2 * (q1x * q1z - q1w * q1y)
m21 = 2 * (q1x * q1y - q1w * q1z)
m22 = q1w ^ 2 - q1x ^ 2 + q1y ^ 2 - q1z ^ 2
m23 = 2 * (q1y * q1z + q1w * q1x)
m31 = 2 * (q1x * q1z + q1w * q1y)
m32 = 2 * (q1y * q1z - q1w * q1x)
m33 = q1w ^ 2 - q1x ^ 2 - q1y ^ 2 + q1z ^ 2
And the roll Euler Angle can be extracted from the direction cosine matrix like this (RADTODEG is 180/Pi):
roll = Atn2(m23, m33) * RADTODEG
But that's as far as I can get. What I need to be doing is finding the roll error signal - i.e. the difference between desired roll and actual roll. Could some kind person help?
Many thanks,
Anthony
Martin Baker
2005-10-22
Hi Anthony,
I think one important issue is to minimise conversions between euler angles and quaternions or matrices because these conversions are costly in terms of performance and unstable around the singularities. Doing these conversions every time you go through the control loop would be horrible.
We have to use quaternions or matrices when we want to combine rotations (we can only add euler angles if we are only changing one of pitch, roll or yaw or if the angles are very small) otherwise its probably best to stay in quaternions.
So can you do the whole control loop in quaternions? Since adding angles is equivalent to multiplying quaternions then I suspect that finding the error would be equivalent to finding the angle difference which would be equivalent to dividing quaternions which is equivalent to multiplying by the conjugate.
Martin
Prospero999
2005-10-22
Hi Martin,
Excellent - that last paragraph particularly was what I think I need! I will try to implement it and I'll get back to you.
Many thanks,
Anthony
Prospero999
2005-10-22
Hi Martin,
Well, I'm trying, but it's not quite right yet...
Two things:
1) When you say, "Finding the error would be equivalent to finding the angle difference which would be equivalent to dividing quaternions which is equivalent to multiplying by the conjugate."
Do you mean is equivalent to multipling by the inverse rather than by the conjugate? It's just that I read up on dividing quaternions, and they seemed to say inverse rather than conjugate...
2) Once the "difference" quarternion has been correctly calculated (if only!), you seem to imply that elements of this quarternion can be used "directly" to feed the autopilot with the roll angle error (i.e. without converting to matrix form and then extracting it from the matrix). How would I do this?
Your help most appreciated!
Anthony
Martin Baker
2005-10-23
> Do you mean is equivalent to multipling by the inverse rather than by the conjugate? It's just that I read up on dividing
> quaternions, and they seemed to say inverse rather than conjugate...
Yes, I should make that clearer on the website, the conjugate is the multiplicative inverse for quaternions.
> 2) Once the "difference" quarternion has been correctly calculated (if only!), you seem to imply that elements of this
> quarternion can be used "directly" to feed the autopilot with the roll angle error (i.e. without converting to matrix form
> and then extracting it from the matrix). How would I do this?
Since I don't know about your application I can only suggest general principles which may not be applicable to what you are doing.
I was thinking that you had some control loop which, in a 2D case would be something like this:
error angle = actual angle - required angle
The equivalent is 3D might be:
error quaternion = actual quaternion * conj(required quaternion)
However, re-reading your message you are looking for the 'roll angle error' so perhaps you have to extract out the roll angle every time? but that does look horrible so its much better to formulate the problem in terms of quaternions or matrices if you can.
Martin
Andy Goldstein
2005-10-23
Hi, Anthony...
As Martin says, once you're into quaternion form things are fairly simple. Given Q1 as your current attitude and Q2 as your desired attitude, the correction Qx you need (i.e., the difference between Q1 and Q2) is simply Q2 multiplied by the conjugate of Q1. To apply the correction gradually, you can divide the rotation angle represented by Qx by going back to the definition of a rotation quaternion - (w,x,y,z) where w is cos(rotation/2) and (x,y,z) is a vector of length sin(rotation/2) along the axis of rotation.
Ultimately, to turn Qx back into control inputs for the plane you'll have to convert back to Eulers, since the flight controls of a plane ultimately control Euler angles. The good news is that the converted Euler angles are now in the plane's frame of reference, and as long as the error isn't too large the results should look pretty rational.
Since you're dealing with X-Plane, I may be able to help since I helped Austin sort out his rotation math. X-Plane actually maintains the plane's attitude internally as a quaternion. If the quaternion form of the attitude is not available at the plugin interface (which I assume you're using), you should talk to Sandy Barbour or Ben Supnik about making it available. One thing you need to be aware of is that X-Plane's coordinate systems for the quaternion and for the XYZ space are not consistent, so the transformations between them are not the obvious ones. Please contact me directly at Andy.Goldstein@hp.com and I can send you code.
Ultimately, though, we get back to what it is you're really trying to accomplish - in particular how you're arriving at and expressing the plane's desired attitude. You observed in your initial post that the roll angle becomes unstable in near vertical flight. This is absolutely correct and is characteristic of traditional Euler angles. The problem is that if you're expressing your desired roll angle as Eulers, that value has the same instability characteristics. So we get back to what the process is for establishing the plane's desired attitude to begin with. I don't have a good answer for this because I don't understand enough about what you're doing.
- Andy
Prospero999
2005-10-23
Many, many thanks Martin and Andy.
Lots to think about there. I need a while to let it all sink in!
Andy, by coincidence, I've been in correspondence with Sandy Barbour and Austin about related matters on the X-Plane.org forums. I've actually been putting off using Sandy's plugin SDK, though I mean eventually to use it, and so far have stuck with VB and UDP since my C++ is, well, shall we say rough at best?;) I have so many questions for you, but I'll try to think of framing them in a semi-intelligent way before emailing you!
Cheers and thanks again,
Anthony
Prospero999
2005-10-24
Hi chaps,
I'm still having a problem with using the quaternion division method to determine my roll angle error.
I'm almost there, but something odd is going on.
Here's the setup:
actual attitude = w1, x1, y1, z1
desired attitude = w2, x2, y2, z2
So, to determine the error, we do the "quaternion equivalent" of "w2 minus w1" which is
w2 mutiplied by the conjugate of w1:
w3 = w2 * cw1 - x2 * cx1 - y2 * cy1 - z2 * cz1
x3 = x2 * cw1 + w2 * cx1 + y2 * cz1 - z2 * cy1
y3 = w2 * cy1 - x2 * cz1 + y2 * cw1 + z2 * cx1
z3 = w2 * cz1 + x2 * cy1 - y2 * cx1 + z2 * cw1
So I try this, and the resulting quaternion (w3, x3, y3, z3) isn't correct!
But here's the odd thing: when I do "w1 minus w2" (i.e. w1 mutiplied by the conjugate of w2)
using the following lines of code:
w3 = w1 * cw2 - x1 * cx2 - y1 * cy2 - z1 * cz2
x3 = x1 * cw2 + w1 * cx2 + y1 * cz2 - z1 * cy2
y3 = w1 * cy2 - x1 * cz2 + y1 * cw2 + z1 * cx2
z3 = w1 * cz2 + x1 * cy2 - y1 * cx2 + z1 * cw2
...I get the right error angles, but they are all the wrong sign. Which is I guess exactly what
they should be...
So how come w2 multiplied by the conjugate of w1 doesn't seem to work...? It *should*
give me same numbers with the signs flipped, surely?
Agh! I'm in Quaternion Hell! Any help much appreciated!
Anthony
Andy Goldstein
2005-10-24
Anthony,
Reverse the order of multiplication and you'll get the right answer. You didn't give a formal expression of the quaternion product and I can't afford the time right now to reverse-compute it from your algebra. (Sorry - I know how tedious this stuff is. I've spent may hours cranking through multiplications.) However...
Going back to basic quaternion theory, the way you rotate a vector P using quaternion Q is
QP' = Q x QP x Q*
where QP is the quaternion (0,P), Q* is the conjugate of Q and "x" denotes quaternion multiplication. To compose rotations, say Q1 and Q2 in that order, the math becomes
QP' = Q2 x (Q1 x QP x Q1*) x Q2*
Quaternion multiplication is associative and reversing the order yields you the conjugate, i.e.
(Q1* x Q2*) = (Q2 x Q1)*
So you can conclude that composing the rotations Q1 and Q2 (in that order) is Q2 x Q1. Relating my notation back to yours, the math you want is
(conjugate of w1) x (w2)
- Andy
Martin Baker
2005-10-24
Just to amplify what Andy said some people find it helpful to think of quaternions in terms of their relationship with the axis-angle representation:
http://www.euclideanspace.com/maths/algebra/realNormedAlgebra/quaternions/notations/axisAngle/
With axis-angle reversing the angle reverses the direction of rotation.
And reversing the direction of axis reverses the direction of rotation.
And reversing the axis and the angle leaves the direction of rotation unchanged.
similarly with quaternions, so,
If w + i x + j y + k z rotates from A to B
Then w - i x - j y - k z rotates from B to A
And -w + i x + j y + k z rotates from B to A
And -w - i x - j y - k z rotates from A to B
(the last two don't apply to fundamental particles which have to rotate by 720 degrees to get back to where they started - When you get to the stage where quaternions are too simple for you its worth reading about quantum mechanics!).
But for the sort of rotations we are talking about w + i x + j y + k z and -w - i x - j y - k z represent the same rotation.
If the axis-angle way of looking at it doesn't help, ignore this message, different people like to think about quaternions in different ways.
Martin
Nobody/Anonymous
2005-10-24
Thanks chaps,
But something is still wrong. I must be bloody stupid. I am truly in Quaternion Hell.
Andy, you said I should swap the order of multiplication, so when I originally said...
"So, to determine the error, we do the "quaternion equivalent" of "w2 minus w1" which is
w2 mutiplied by the conjugate of w1:
w3 = w2 * cw1 - x2 * cx1 - y2 * cy1 - z2 * cz1
x3 = x2 * cw1 + w2 * cx1 + y2 * cz1 - z2 * cy1
y3 = w2 * cy1 - x2 * cz1 + y2 * cw1 + z2 * cx1
z3 = w2 * cz1 + x2 * cy1 - y2 * cx1 + z2 * cw1"
...should I actually be doing the following?:
w3 = cw1 * w2 - cx1 * x2 - cy1 * y2 - cz1 * z2
x3 = cx1 * w2 + cw1 * x2 + cy1 * z2 - cz1 * y2
y3 = cw1 * y2 - cx1 * z2 + cy1 * w2 + cz1 * x2
z3 = cw1 * z2 + cx1 * y2 - cy1 * x2 + cz1 * w2
I tried this and it doesn't come out right:( Should it be right? If so, there's something wrong elsewhere!!!
(By the way, when I use w, x, y and z, I mean that w is the "angle" component of the quaternion and x, y and z form the "vector" component.)
(And cw1, cx1, cy1 and cz1 is the conjugate).
Thanks both of you,
Anthony
Martin Baker
2005-10-26
Perhaps by analogy with the 2D case, we could use:
error angle = actual angle - required angle
Or we could use:
error angle = required angle - actual angle
These are the same except it reverses which direction of error is considered positive and which is considered negative.
In the 3D case addition is replaced with multiplication and multiplication by -1 is replaced by conjugate.
So the equivalent is 3D might be:
error quaternion = actual quaternion * conj(required quaternion)
or
error quaternion = required quaternion * conj(actual quaternion)
depending on which direction of error we consider 'positive'.
One result would be the conjugate of the other (which could be proved by the equation Andy gives)
Martin
Andy Goldstein
2005-10-26
The answer to the above two possibilities is "probably neither". The reason has to do with frame of reference.
Anthony, you haven't said so, but I'm going to make a guess that you want your "difference angle" (i.e., the correction quaternion) expressed in the frame of reference of the airplane. (After all, that's how control inputs are applied - ailerons apply a roll along the *plane's* roll axis.) With that in mind, let's look very carefully at the rotation quaternions we're dealing with:
Q1 = the plane's actual attitude, expressed in the external frame of reference.
Q2 = the plane's desired attitude, expressed in the external frame of reference.
Q3 = the difference, expressed in the plane's frame of reference.
Expressed formally, the problem is defined as
Q2 = Q1 x Q3
The reason for this ordering is that
(1) Q3 is expressed in the plane's frame of reference, and therefore must be applied first, and
(2) referring to my preceding post, rotations are composed by ordering the quaternions right to left.
This equation is solved for Q3 simply by pre-multiplying by Q1* (conjugate of Q1), yielding
Q1* x Q2 = Q1* x (Q1 x Q3) = (Q1* x Q1) x Q3) = Q3
Anthony, this matches the second of your computations in your last post. If that's the one you tried and you're not getting the right answer, then something is still wrong. First step would be to check your frames of reference again. If it's still not working for you I'll have to throw some code together quick and see if the actual reuslts match my theory...
- Andy
Prospero999
2005-10-28
Thanks guys,
I'm taking a few days to absorb this.
Cheers,
Anthony
Anonymous
2012-07-18
Greetings! I'm not sure if anyone will read this as the thread ended a long time ago…
I've been implementing an X-Plane autopilot using quaternions and I came across this thread. However, after implementing the above suggestions I was unable get the correct result. Let me explain more.
I begin with one quaternion representing the desired attitude and another representing the actual attitude. I then compute an error quaternion. The error quaternion should represent a rotation from the actual attitude to the desired attitude. My hope was to extract the roll, pitch, and yaw from the error quaternion to affect actuators. However, when I extract, for example, pitch from the error quaternion, it is not the case that actual pitch + error pitch = desired pitch. I know that I can extract euler angles correctly from a quaternion as I can convert the quaternion provided from X-Plane to the correct roll, pitch, and yaw. I also know that the error quaternion is correct (to some degree) because when I apply it to the actual quaternion I get back the desired quaternion.
Is there any chance you have code that can do this, or do you know how to do this?
Martin Baker
2012-07-19
> it is not the case that
> actual pitch + error pitch = desired pitch.
Isn't that the reason that we use quaternions in the first place?
If we could just add Euler angles like this we would not need to use quaternions.
Martin
nhughes
2012-07-20
go to my website,
noelhughes.net
look at the quaternion training charts. I also have a paper on conversion of a quaternion to euler angles. However, euler angles only work for attitude control for small errors. As you may have found, euler angles go singular (the dreaded "gimbal lock" of the movie Apollo 13). For example, if you are flying north and want to perform a loop, as you go through vertical, you are suddenly upside down, and flying south, a sudden 180 degree change in both heading and roll angle.
Read the material on my website and let me know if you have any questions.
noel.h.hughes@gmail.com
Peter Ruffner
2015-01-12
I moved this to a new topic (Virtual solar system with quaternions.
nhughes
2015-01-12
Sorry, I can't discern what your code does. A couple comments.
The conjugate of a quaternion is the inverse and vice versa. I don't
understand what you mean by you can't roll or knowing when to use conjugate
or flying off like rotating instead of rolling. Take a look at my websit
noelhughes.net for basic information about quaternions, coordinate frames,
rotations, etc.
Noel Hughes
On Jan 12, 2015 12:35 PM, "Peter Ruffner" mipada5@users.sf.net wrote:
I hope this discussion is still open and that Noel is still around.
I also am writing a flight-sim program (like many people I see asking
questions about quaternions). It's a virtual Solar system. It has planets,
spaceships, floating cameras (multiple views). I can fly at light speed and
faster but, I can't roll. I'm using quaternions now but can't get the input
right. I'm using Java3D, so I hope the libraries and objects work, and am
trying to use the 'local frame of reference' but, I don't know when to use
inverse() and conjugate(). This is what I have in a nutshell and the test
object in front of me flies off like I'm rotating (instead of rolling).
//initial setup
Q1 = new Quat4d();//initial rotation
Q1.inverse();
Q1.conjugate();//setup input
//set up Q2 (quaternion) with new rotation increment (delta)
//d is (x meters/sec) / frames per second
A2 = new AxisAngle3d(Math.toRadians(d.x), Math.toRadians(d.y),
Math.toRadians(d.z));
Q2 = new Quat4d();
Q2.set(A2);//set quaternion with axis/angle
Q2.inverse();//local frame of reference
Q2.conjugate();//local frame of reference
Q1.mul(Q2);//update with new rotation increment
Quaternions and Aircraft Roll Demand Control*
https://sourceforge.net/p/mjbworld/discussion/122133/thread/c845c088/?limit=25#bde2
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