Euler Angles

Here we will follow quite closely the online class notes prepared by Professor Mona Berciu, Department of Physics & Astronomy, University of British Columbia.

Basic Relations

In terms of the unit vectors of the $(X, Y, Z)$ Cartesian coordinate system shown in the left panel of Figure 1, we can uniquely specify the (red) vector, $\vec{A}$ , by the expression,

$\vec{A} = {\vec{e}}_{X} (A_{X}) + {\vec{e}}_{Y} (A_{Y}) + {\vec{e}}_{Z} (A_{Z})$

where the coefficient triplet, $(A_{X}, A_{Y}, A_{Z})$ , give the length (and $\pm$ direction) of each vector component. Alternatively, in terms of the unit vectors of the $(x_{1}, x_{2}, x_{3})$ Cartesian coordinate system shown in the right panel of Figure 1, the same (red) vector is specified by the expression,

$\vec{A} = {\vec{e}}_{1} (A_{1}) + {\vec{e}}_{2} (A_{2}) + {\vec{e}}_{3} (A_{3}) .$

Figure 1

Now, it is clear from the nature of unit vectors and vector dot-products that the value of the coefficient, $A_{1}$ — which explicitly appears in the second of these two expressions — may be obtained from the dot product, ${\vec{e}}_{1} \cdot \vec{A}$ . The same must be true if we insert, for $\vec{A}$ , the first of the two expressions; that is to say,

$A_{1} = {\vec{e}}_{1} \cdot \vec{A}$

=

${\vec{e}}_{1} \cdot {\vec{e}}_{X} (A_{X}) + {\vec{e}}_{1} \cdot {\vec{e}}_{Y} (A_{Y}) + {\vec{e}}_{1} \cdot {\vec{e}}_{Z} (A_{Z}) .$

Analogously, we can write,

$A_{2} = {\vec{e}}_{2} \cdot \vec{A}$	$=$	${\vec{e}}_{2} \cdot {\vec{e}}_{X} (A_{X}) + {\vec{e}}_{2} \cdot {\vec{e}}_{Y} (A_{Y}) + {\vec{e}}_{2} \cdot {\vec{e}}_{Z} (A_{Z}),$
$A_{3} = {\vec{e}}_{3} \cdot \vec{A}$	$=$	${\vec{e}}_{3} \cdot {\vec{e}}_{X} (A_{X}) + {\vec{e}}_{3} \cdot {\vec{e}}_{Y} (A_{Y}) + {\vec{e}}_{3} \cdot {\vec{e}}_{Z} (A_{Z}) .$

This set of three relations therefore provides a generic way to express one set of projections in terms of the other. When written in matrix form, the set becomes,

$[\begin{matrix} A_{1} \\ A_{2} \\ A_{3} \end{matrix}]$

$=$

$[\begin{matrix} {\vec{e}}_{1} \cdot {\vec{e}}_{X} & {\vec{e}}_{1} \cdot {\vec{e}}_{Y} & {\vec{e}}_{1} \cdot {\vec{e}}_{Z} \\ {\vec{e}}_{2} \cdot {\vec{e}}_{X} & {\vec{e}}_{2} \cdot {\vec{e}}_{Y} & {\vec{e}}_{2} \cdot {\vec{e}}_{Z} \\ {\vec{e}}_{3} \cdot {\vec{e}}_{X} & {\vec{e}}_{3} \cdot {\vec{e}}_{Y} & {\vec{e}}_{3} \cdot {\vec{e}}_{Z} \end{matrix}] \cdot [\begin{matrix} A_{X} \\ A_{Y} \\ A_{Z} \end{matrix}] = \hat{R} \cdot [\begin{matrix} A_{X} \\ A_{Y} \\ A_{Z} \end{matrix}] .$

Alternatively, we could "dot" the unit-vector triplet $({\vec{e}}_{X}, {\vec{e}}_{Y}, {\vec{e}}_{Z})$ into the vector, $\vec{A}$ , in which case it would be easy to demonstrate that mapping the other direction is accomplished via the relation,

$[\begin{matrix} A_{X} \\ A_{Y} \\ A_{Z} \end{matrix}]$

$=$

${\hat{R}}^{- 1} \cdot [\begin{matrix} A_{1} \\ A_{2} \\ A_{3} \end{matrix}],$

where,

${\hat{R}}^{- 1}$

$\equiv$

$[\begin{matrix} {\vec{e}}_{X} \cdot {\vec{e}}_{1} & {\vec{e}}_{X} \cdot {\vec{e}}_{2} & {\vec{e}}_{X} \cdot {\vec{e}}_{3} \\ {\vec{e}}_{Y} \cdot {\vec{e}}_{1} & {\vec{e}}_{Y} \cdot {\vec{e}}_{2} & {\vec{e}}_{Y} \cdot {\vec{e}}_{3} \\ {\vec{e}}_{Z} \cdot {\vec{e}}_{1} & {\vec{e}}_{Z} \cdot {\vec{e}}_{2} & {\vec{e}}_{Z} \cdot {\vec{e}}_{3} \end{matrix}] .$

A Sequence of Rotations

It is quite generally true that we can transition/map/migrate from one set of orthogonal unit vectors — such as the $({\vec{e}}_{X}, {\vec{e}}_{Y}, {\vec{e}}_{Z})$ inertial/laboratory frame illustrated by the black arrows in the left panel of Figure 1 — to any other set of orthogonal unit vectors — such as the $({\vec{e}}_{1}, {\vec{e}}_{2}, {\vec{e}}_{3})$ body frame illustrated by the black arrows in the right panel of Figure 1 — by carrying out three rotations. The order in which rotations are carried out is relevant, but one fairly standard sequence of rotations is illustrated in Figure 2:

Figure 2

Rotation #1	Rotation #2	Rotation #3

First Rotation

As depicted in the left-most panel of Figure 2, rotate the triplet of unit vectors about the $Z$ (i.e., ${\vec{e}}_{Z}$ ) axis by an angle, $ϕ$ . The result is the green coordinate system labeled, $(1^{'}, 2^{'}, 3^{'})$ . Note: (a) The 3' axis remains aligned with the inertial-frame Z-axis; and (b) we will refer to the 1' axis as the line of nodes. Given that the 3' axis is aligned with the Z-axis — that is, ${\vec{e}}_{3^{'}} = {\vec{e}}_{Z}$ — it is easy to recognize that the other two mappings are:

{\vec{e}}_{1^{'}} = {\vec{e}}_{X} \cos ϕ + {\vec{e}}_{Y} \sin ϕ,

and

{\vec{e}}_{2^{'}} = {\vec{e}}_{Y} \cos ϕ - {\vec{e}}_{X} \sin ϕ

.

Hence, the corresponding rotation matrix is,

${\hat{R}}_{3} (ϕ)$

$=$

$[\begin{matrix} {\vec{e}}_{1^{'}} \cdot {\vec{e}}_{X} & {\vec{e}}_{1^{'}} \cdot {\vec{e}}_{Y} & {\vec{e}}_{1^{'}} \cdot {\vec{e}}_{Z} \\ {\vec{e}}_{2^{'}} \cdot {\vec{e}}_{X} & {\vec{e}}_{2^{'}} \cdot {\vec{e}}_{Y} & {\vec{e}}_{2^{'}} \cdot {\vec{e}}_{Z} \\ {\vec{e}}_{3^{'}} \cdot {\vec{e}}_{X} & {\vec{e}}_{3^{'}} \cdot {\vec{e}}_{Y} & {\vec{e}}_{3^{'}} \cdot {\vec{e}}_{Z} \end{matrix}] = [\begin{matrix} \cos ϕ & \sin ϕ & 0 \\ - \sin ϕ & \cos ϕ & 0 \\ 0 & 0 & 1 \end{matrix}] .$

Note that the subscript, 3, has been attached to $\hat{R}$ in order to indicate that rotation was about the "third" axis.

Second Rotation

As depicted in the center panel of Figure 2, rotate the triplet of unit vectors about the line of nodes by an angle, $θ$ . The result is the light-blue coordinate system labeled, (1", 2", 3"). Note: (a) The 1" axis is aligned with the 1' axis (line of nodes); and (b) the values of the first pair of rotation angles, $(ϕ, θ)$ , have been chosen to ensure that the 3" axis aligns with the ${\vec{e}}_{3}$ unit vector. In this case, ${\vec{e}}_{1^{″}} = {\vec{e}}_{1^{'}}$ and the other two mappings are,

${\vec{e}}_{2^{″}} = {\vec{e}}_{2^{'}} \cos θ + {\vec{e}}_{3^{'}} \sin θ$ and ${\vec{e}}_{3^{″}} = {\vec{e}}_{3^{'}} \cos θ - {\vec{e}}_{2^{'}} \sin θ$ .

In this case, then, the corresponding rotation matrix is,

${\hat{R}}_{1} (θ)$

$=$

$[\begin{matrix} {\vec{e}}_{1^{″}} \cdot {\vec{e}}_{1^{'}} & {\vec{e}}_{1^{″}} \cdot {\vec{e}}_{2^{'}} & {\vec{e}}_{1^{″}} \cdot {\vec{e}}_{3^{'}} \\ {\vec{e}}_{2^{″}} \cdot {\vec{e}}_{1^{'}} & {\vec{e}}_{2^{″}} \cdot {\vec{e}}_{2^{'}} & {\vec{e}}_{2^{″}} \cdot {\vec{e}}_{3^{'}} \\ {\vec{e}}_{3^{″}} \cdot {\vec{e}}_{1^{'}} & {\vec{e}}_{3^{″}} \cdot {\vec{e}}_{2^{'}} & {\vec{e}}_{3^{″}} \cdot {\vec{e}}_{3^{'}} \end{matrix}] = [\begin{matrix} 1 & 0 & 0 \\ 0 & \cos θ & \sin θ \\ 0 & - \sin θ & \cos θ \end{matrix}] .$

In this case the subscript, 1, has been attached to $\hat{R}$ in order to indicate that rotation was about the "first" axis.

Third Rotation

As depicted in the right-most panel of Figure 2, rotate the triplet of unit vectors about the 3" axis by an. angle, $ψ$ . The result is the desired black coordinate system labeled, $({\vec{e}}_{1}, {\vec{e}}_{2}, {\vec{e}}_{3})$ . Given that this rotation — like the first — calls for rotation about the "third" axis, we can immediately deduce that the relevant rotation matrix is,

${\hat{R}}_{3} (ψ)$

$=$

$[\begin{matrix} \cos ψ & \sin ψ & 0 \\ - \sin ψ & \cos ψ & 0 \\ 0 & 0 & 1 \end{matrix}] .$

Combined

We can now write the general rotation matrix that links the body frame, $(x_{1}, x_{2}, x_{3})$ , to the inertial/laboratory frame, $(X, Y, Z)$ , as the product of the three rotations about the corresponding axes:

$\hat{R} (ϕ, θ, ψ) = {\hat{R}}_{3} (ψ) \cdot {\hat{R}}_{1} (θ) \cdot {\hat{R}}_{3} (ϕ)$

$=$

$[\begin{matrix} \cos ψ & \sin ψ & 0 \\ - \sin ψ & \cos ψ & 0 \\ 0 & 0 & 1 \end{matrix}] \cdot [\begin{matrix} 1 & 0 & 0 \\ 0 & \cos θ & \sin θ \\ 0 & - \sin θ & \cos θ \end{matrix}] \cdot [\begin{matrix} \cos ϕ & \sin ϕ & 0 \\ - \sin ϕ & \cos ϕ & 0 \\ 0 & 0 & 1 \end{matrix}] .$

Carrying out the matrix multiplications, starting from the left, this gives,

$\hat{R} (ϕ, θ, ψ)$

$=$

$[\begin{matrix} \cos ψ & \sin ψ \cos θ & \sin ψ \sin θ \\ - \sin ψ & \cos ψ \cos θ & \cos ψ \sin θ \\ 0 & 0 & 0 \end{matrix}] \cdot [\begin{matrix} \cos ϕ & \sin ϕ & 0 \\ - \sin ϕ & \cos ϕ & 0 \\ 0 & 0 & 1 \end{matrix}] .$

Carrying out the matrix multiplications, starting from the right, this gives,

$\hat{R} (ϕ, θ, ψ)$	$=$	$[\begin{matrix} \cos ψ & \sin ψ & 0 \\ - \sin ψ & \cos ψ & 0 \\ 0 & 0 & 1 \end{matrix}] \cdot [\begin{matrix} \cos ϕ & \sin ϕ & 0 \\ - \sin ϕ \cos θ & \cos θ \cos ϕ & \sin θ \\ \sin θ \sin ϕ & - \sin θ \cos ϕ & \cos θ \end{matrix}]$
	$=$	$[\begin{matrix} (\cos ψ \cos ϕ - \sin ψ \sin ϕ \cos θ) & (\sin ϕ \cos ψ + \sin ψ \cos θ \cos ϕ) & (\sin ψ \sin θ) \\ (- \sin ψ \cos ϕ - \sin ϕ \cos θ \cos ψ) & (- \sin ψ \sin ϕ + \cos ψ \cos θ \cos ϕ) & \sin θ \cos ψ \\ \sin θ \sin ϕ & - \sin θ \cos ϕ & \cos θ \end{matrix}]$

From the last row of the column labeled "Proper Euler angles" in Wikipedia's discussion of the rotation matrix, we find,

$Z_{1} X_{2} Z_{3}$

$=$

$[\begin{matrix} (c_{1} c_{3} - c_{2} s_{1} s_{3}) & (- c_{1} s_{3} - c_{2} c_{3} s_{1}) & (s_{1} s_{2}) \\ (c_{3} s_{1} + c_{1} c_{2} s_{3}) & (c_{1} c_{2} c_{3} - s_{1} s_{3}) & (- c_{1} s_{2}) \\ (s_{2} s_{3}) & (c_{3} s_{2}) & (c_{2}) \end{matrix}]$

The equivalent expression can be found in Professor Berciu's online class notes; it reads,

$\hat{R} (ϕ, θ, ψ)$

$=$

$[\begin{matrix} (\cos ϕ \cos ψ - \cos θ \sin ϕ \sin ψ) & (- \cos ϕ \sin ψ - \cos θ \cos ψ \sin ϕ) & (\sin ϕ \sin θ) \\ (\cos ψ \sin ϕ + \cos ϕ \cos θ \sin ψ) & (\cos ϕ \cos θ \cos ψ - \sin ϕ \sin ψ) & (- \cos ϕ \sin θ) \\ (\sin θ \sin ψ) & (\cos ψ \sin θ) & (\cos θ) \end{matrix}]$

Appendix/Mathematics/EulerAngles

Contents

Euler Angles

Basic Relations

A Sequence of Rotations

First Rotation

Second Rotation

Third Rotation

Combined

See Also

Navigation menu

Appendix/Mathematics/EulerAngles

Euler Angles

Basic Relations

A Sequence of Rotations

First Rotation

Second Rotation

Third Rotation

Combined

See Also

Navigation menu

Search