DYNAMICS OF ROTATING BODIES
The motion of a rigid body in threedimensional space is determined by the forces and moments acting on the body at each instant of time. There are two main types of general motion of a rigid body: (1) translational motion, which typically deals with the velocity and position of the center of mass of the body, and (2) rotational or attitude motion, which typically deals with the (angular) velocity and (angular) position about the center of mass. The angular position about the center of mass is often referred to as the attitude or orientation of the body. The choice of the center of mass as the reference point to describe the general body motion is not restrictive, but it has the advantage of allowing the rotation and translation to be treated separately. That is, the translation of the body center of mass does not affect nor is it affected by the rotation of the body about the center of mass.
To understand the two types of motion, consider the example of a spacecraft traveling in space. The spacecraft translates and rotates at the same time. For an observer located on Earth, the spacecraft can be thought of as a single particle, and its trajectory through space is primarily determined by its instantaneous position and velocity. Its orientation with respect to Earth is irrelevant (unless a communication antenna needs to be always pointing toward Earth) or very difficult to observe from such a large distance. On the other hand, as the same observer moves closer and closer to the spacecraft, the orientation of the spacecraft may be very important, and it certainly becomes much more obvious.
Translational motion therefore deals with the motion of particles, that is, idealized points with zero dimensions but nonzero mass. Rotational motion, on the other hand, deals with the motion of rigid bodies, that is, physical objects with nonzero dimensions and nonzero mass. One can safely think of translation as the macroscopic, or faraway view of the motion of an object and of rotation as the microscopic, or close — by view of the motion.
Dynamics of the Attitude Motion
The dynamic equations of the attitude motion of a rotating body describe the behavior of the angular momentum or the angular velocity vector as a function of the externally applied torques or moments. The basic equation that governs the body behavior under external torques is Euler’s equation of motion (2). It states that the rate of change of the angular momentum vector H of the body at every instant is equal to the applied moment M
M 
(1) 
dH
dt
(2) 
where the angular momentum is defined by H= rx vdm
and the integration extends over the entire body. In Eq. (2) the vector v = r denotes the inertial velocity of the mass element dm (see Fig. 1).
Figure 1. Inertial and bodyfixed reference frames. The bodyfixed reference frame is located at the center of mass cm. The vector r denotes the location of the element mass dm in the inertial frame and the vector p denotes the location of the mass in the body frame. 
where 
2 
2 
x 
И 
2 
2 
У 
L 
2 
2 
z 
dV dt 
dV dt 
(3) 
В 
1 
The time derivative in Eq. (1) must be taken with respect to an inertial reference frame. In addition, in the calculation of H we have a choice of the reference point about which to calculate the moments and the angular momentum. Equation (1) implies that we have chosen either a point fixed in inertial space or the center of mass. The center of mass offers the most convenient and natural choice. In this case, from Fig. 1 we have that the location of the mass element dm is at r = R + p, where R denotes the location of the center of mass. Differentiation of a vector V, as seen from an inertial frame, is related to differentiation as seen in a moving (body) frame through the relationship 
The momentofinertia matrix depends on the shape of the body and the manner in which its mass is distributed. The larger the moments of inertia the greater resistance the body will have to rotation. When using Eq. (3) and recalling that in a bodyfixed frame the inertia matrix is constant, it follows that Eq. (1) can be written as 
II 
1 xydm 
Jb 

II N 
1 xzdm 
Jb 

Jyz = 
m d y 
JB 
JO + о x Jo = M 
(12) 
where ы is the angular velocity of the moving frame. The velocity of the mass element dm is thus given by
v = R+ о x p (4)
Subsequently, the angular momentum vector is given by
H = / p x R dm + I p x (о x p) dm (5)
J в J в
The first integral in the previous expression vanishes, because the origin is at the center of mass
I p dm = 0 (6)
J в
The angular momentum vector with respect to the center of mass is thus
H = / p x (о x p)dm (7)
Jb
Since the position vector p changes with time in an inertial frame, it is beneficial to choose a reference frame fixed in the body, since in this case the mass distribution does not change.
Therefore, choosing a reference frame fixed in the body and located at the center of mass, we can express ы and p in this bodyfixed frame as
о = Oxi + Oyj + Oz k, p = xi + yj + zk (8)
Then Eq. (7) yields
H = Jo (9)
where J is the momentofinertia matrix and is given by
1 J 
Jxy 
Jxz 

J = 
Jxy 
Jy 
— Jyz 
(10) 
Jxz 
Jyz 1 
Jz 
The inertia matrix J, also called the inertia tensor, is symmetric and positive definite. One can therefore choose a reference frame such that the matrix J is diagonal. This particular choice of bodyfixed axes is called the axes of principal moments of inertia. The directions of these axes are exactly those determined by the eigenvectors of the matrix J.
The components of Eq. (12) resolved along the principal axes are given by
JxO x = (Jy — Jz )OyOz + Mx
JyO y = (Jz — Jx )OzOy + Mz (13)
JzO z = (Jx — Jy )OxOy + Mz
where Jx, Jy, Jz are the three principal moments of inertia (the eigenvalues of the matrix J), wx, wy, wz are the components of the angular velocity vector along the principal axes, as in Eq. (8), and Mx, My, Mz are the components of the applied moment along the same set of axes, i. e., M = Mxi + My j Mzk.
Equation (12) or Eq. (13) is the starting point for most attitude control problems.
Kinematics of the Attitude Motion
The solution of Eq. (13) provides the instantaneous angular velocity of the body about its center of mass. It does not capture the instantaneous orientation of the body with respect to, say, the inertial reference frame. In particular, integration of the angular velocity vector w does not, in general, give any useful information about the orientation of the body. The orientation of the body is completely determined if we know the orientation of the bodyfixed frame with respect to the inertial reference frame, used in deriving Eq. (13). The rotation matrix R between the bodyfixed and the inertial reference frames is used to completely describe the body orientation. The rotation matrix is a 3 X 3 matrix having as columns the components of the unit vectors of the inertial frame expressed in terms of the unit vectors of the bodyfixed frame.
In other words, i, j, k denote the unit vectors of the body frame and I, J, K denote the unit vectors in the inertial frame, a vector V having coordinates (Vx, Vy, Vz) and (VX, VY, VZ) with
respect to the bodyfixed and inertial frames, respectively, can be written as
(14) 
V = Vxi + Vy j + Vz k = VXI + VYJ + VZK
(15) 
The matrix R establishes the following relation between the coordinates of V in the two reference frames
"Vx" 
Vx" 

Vy 
= R 
Vy 
Vz 
B 
Vz 
I 
If ы = wxi + wyj + wzk denotes the angular velocity of the body frame with respect to the inertial frame (expressed in the body frame coordinates), the differential equation satisfied by R is given by (3,4)
(16)
(17) 
where S(w) is the skewsymmetric matrix (S = —ST)
0 
ffi>z 
—■ 
1 z 
0 
ffi>x 
®y 
1 x 
0 
S(a) = 
y 
rotations. Several definitions of the Euler angles are possible, depending on the choice of the axes of rotations and the particular order in which the rotations are performed. In fact, there are 12 different possible choices of Euler angle sets. These sets have been discussed in great detail elsewhere (3). One of the most common choices in aircraft and spacecraft attitude control problems is the (321) Euler angle sequence. According to this set of Euler angles, the orientation of the bodyfixed reference frame with respect to the inertial reference frame is described by a sequence of the following three elementary rotations:
1. First rotate the inertial reference frame about its Z axis through an angle ф to the new axes x’ — y’ — z’.
2. Then rotate about the y’ axis by an angle в to the new axes x" — y" — z".
3. Finally rotate about the x" axis by an angle ф to the final bodyaxes x, y, z.
This sequence of rotations that takes the inertial frame to coincide with the body frame after three rotations is depicted in Fig. 2. Note that the order of rotations is very important. The angles ф, в, and ф are called the roll, pitch, and yaw angles.
The elementary rotations of a reference frame about the axes x, y, and z are given, respectively, by
‘1 
0 
0 

Rx (Ф) = 
0 
cos Ф 
sin Ф 
0— 
sin Ф 
cos Ф 

cos 0 
0 
— sin 0 

Ry (0) = 
0 
1 
0 
sin 0 
0 
cos 0 
and it is also proper, that is, its determinant is +1. Equation (16) can also be used to calculate the angular velocity if the rate of change of R is known 
It can be shown that the matrix R is orthogonal, that is, it satisfies 
RRT =RTR=I 
S(&) = Rrt 
We can use Eq. (16) to find the orientation of the body at any instant of time if the corresponding angular velocity vector ы of the body is known. In particular, the matrix differential equation in Eq. (16) can be integrated from the known initial attitude of the body to propagate the attitude for all future times. This process will require the integration of the nine linear but timevarying differential equations for the elements of the matrix R in order to obtain R(t) at each time t. Careful examination of the matrix R, however, reveals that the nine elements of this matrix are not independent from each other, since the matrix R must necessarily satisfy the constraints in Eq. (18). An alternative approach to solving Eq. (16) is to parameterize the matrix R in terms of some other variables and then use the differential equations of these variables in order to propagate the attitude history. Euler Angles. The minimum number of parameters that can be used to parameterize all nine elements of R is three. [Notice that Eq. (18) imposes six independent constraints among the elements of R.] The Euler angles are the most commonly used threedimensional parameterization of the rotation matrix R. They have the advantage that they are amenable to physical interpretation and can be easily visualized. Using the Euler angles we can describe the final orientation of the bodyaxis frame by three successive elementary 
(18) 
(20) 
cos t sin t 0 — sin t cos t 0 
Rz (t) = 
(19) 
0 
0 
Z=z’ Figure 2. Euler angle sequence (321). We align the inertial and body frames by first rotating with an angle ф about the z axis, then rotating with an angle в about the new y axis, and finally rotating with an angle ф about the x axis. 
(21) 
(27) 
and thus 
The rotation matrix in terms of the (321) Euler angles can thus be expressed in terms of the three previous elementary rotations by 
R(f, в, ф) = Rx(^)Ry(0)Rz(f) 
The Euler parameters satisfy the constraint <?2 + q1 + q2 + q2 =1 The quantity q = qo + q^ + q2 j + q3k 
(22) 
(23) 
cos f cos в
R(f,0^) = — sin f cos ф + cos f sin в sin Ф
sin f sin ф + cos f sin в cos ф
sin f cos в — sin в
cos f cos ф + sin f sin в sin ф cos в sin ф — cos f sin ф + sin f sin в cos ф cos в cos ф
The components of the angular velocity vector in the body — frame are given in terms of the rates of these Euler angles by
Ox = —f sin в + ф
Oy = f cos в sin ф + в cos ф
Oz = f cos в cos ф — в sin ф
defined from the Euler parameters is called the quaternion (4,7). It should be pointed out that there is often a confusion in the literature about this term. With a slight abuse of terminology, many authors refer to the Euler parameters q0, q1, q2, q3 as the quaternion although, strictly speaking, this is incorrect.
The rotation matrix in terms of the Euler parameters is given by
R(qo, q, q2, q3)
20зд3— qoq2) 2(q1q2 — qoq3) q2 — q1 + q2 — q3 2(q2q3 + qoqx)
2(qxq3 + qoq2) 2(q2q3 — qoqx) q2 — q — q + q3
(28)
and the corresponding kinematic equations are given by
V 

<?1 
1 
q2 
“ 2 
q3 
о 
x 
СО 
z 
"qo" 

q1 

q2 

q3 
o —Ox —Oy —Oz 
Ox o 
—о 
o Oz —Oz o Oy Ov 
y 
y 
(24) 
tan ф = 
Ф 
q0 = cos —, qi = ei sin —, і = 1, 2, 3 
The previous equation indicates that there is a singularity when в = ±n/2. This singularity does not allow for a global parameterization of the attitude using the Euler angles. The previous (321) Euler sequence, for example, is defined only for — n < ф < n, — n/2 < в< n/2, and —n< ф < n. Other threedimensional parameterizations include the CayleyRodrigues parameters and the modified Rodrigues parameters (4). However, the singularity problem is always present, when using a threedimensional parameterization of the rotation matrix R (5). Higher order parameterizations need to be used to avoid singularities. Euler Parameters (Quaternions). A fourdimensional parameterization of the attitude kinematics that does not have any singularities is given by the Euler parameters. The Euler parameters are defined via Euler’s theorem, which can be stated as follows (6): The most general displacement of a rigid body with one point fixed is equivalent to a single rotation about some axis through that point. The corresponding axis is called the eigenaxis of rotation, and and the corresponding angle is called the principal angle. If the eigenaxis unit vector is e = e1i + ej + e3k and the principal angle is Ф, the Euler parameters are defined by 
Conversely, we can solve the previous equations and express the rates of the Euler angles in terms of the angular velocity components in the bodyframe 
ф = ox + oy tan в sin ф + oz tan в cos ф в = oy cos ф — oz sin ф f = Oy sec в sin ф + Oz sec в cos ф 
(25) 
Ф 
These equations are linear and do not involve any trigonometric functions as the corresponding kinematic equations in terms of the Euler angles. Integration of these equations to obtain attitude information can thus be performed very fast on a computer. In addition, the attitude description in terms of qo, q1, q2, q3 is global and nonsingular. For these reasons the Euler parameters have increasingly gained popularity in many attitudecontrol applications. The main disadvantage when using the Euler parameters is that they are difficult to visualize. The orientation needs to be transformed to an Euler angle sequence if they are to be meaningful, for example to a pilot or an engineer. The Eu — lerian angles (ф, в, ф) in terms of the Euler parameters can be computed, for example, from sin в = 2(q^3 — qoq2) 2(qxq2 + qoq3) 
The Euler parameters are related to the (321) Euler angles by qo = cos (ф/2) cos^/2) cos^/2) + sin^/2) sin(в/2) sin(f/2) q1 = sin^/2) cos(в/2) cos(f/2) — cos^/2) sin(в/2) sin(f/2) q2 = cos (ф/2) sin(в/2) cos(f/2) + sin(ф/2) cos^/2) sin(f/2) q3 = cos(ф/2) cos^/2) sin(f/2) — sin(ф/2) sin(в/2) cos(f/2) (3o) 
q2 + q? — q2 — q3 2(<?2<?з +<?o<?i) ЯІ 
q2 — q2 + q3 
tan f = 
(29) 
Careful examination of Eq. (28) shows that both a given set of values of q0, q1, q2, q3, as well as and their negatives give the same rotation matrix R. Every orientation corresponds to two different sets of Euler parameters. This slight ambiguity has no significant effect in applications, however.
Добавить комментарий