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Unformatted text preview: J. Peraire, S. Widnall 16.07 Dynamics Fall 2009 Version 2.0 Lecture L29  3D Rigid Body Dynamics 3D Rigid Body Dynamics: Euler Angles
The difficulty of describing the positions of the bodyfixed axis of a rotating body is approached through the use of Euler angles: spin , nutation and precession shown below in Figure 1. In this case we surmount the difficulty of keeping track of the principal axes fixed to the body by making their orientation the unknowns in our equations of motion; then the angular velocities and angular accelerations which appear in Euler's equations are expressed in terms of these fundamental unknowns, the positions of the principal axes expressed as angular deviations from some initial positions. Euler angles are particularly useful to describe the motion of a body that rotates about a fixed point, such as a gyroscope or a top or a body that rotates about its center of mass, such as an aircraft or spacecraft. Unfortunately, there is no standard formulation nor standard notation for Euler angles. We choose to follow one typically used in physics textbooks. However, for aircraft and spacecraft motion a slightly different one is used; the primary difference is in the definition of the "pitch" angle. For aircraft motion, we usually refer the motion to a horizontal rather than to a vertical axis. In a description of aircraft motion, would be the "roll" angle; the "yaw" angle; and the "pitch" angle. The pitch angle would be measured from the horizontal rather than from the vertical, as is customary and useful to describe a spinning top. 1 Figure 1: Euler Angles In order to describe the angular orientation and angular velocity of a rotating body, we need three angles. As shown on the figure, we need to specify the rotation of the body about its "spin" or z bodyfixed axis, the angle as shown. This axis can also "precess" through an angle and "nutate" through an angle . To develop the description of this motion, we use a series of transformations of coordinates, as we did in Lecture 3. The final result is shown below. This is the coordinate system used for the description of motion of a general threedimensional rigid body described in bodyfixed axis. To identify the new positions of the principal axes as a result of angular displacement through the three Euler angles, we go through a series of coordinate rotations, as introduced in Lecture 3. 2 We first rotate from an initial X, Y, Z system into an x , y , z system through a rotation about the Z, z axis. The angle is called the angle of precession. x cos sin 0 X X y = sin cos 0 Y = [T1 ] Y . z 0 0 1 Z Z The resulting x , y coordinates remain in the X, Y plane. Then, we rotate about the x axis into the x , y , z system through an angle . The x axis remains coincident with the x axis. The axis of rotation for this transformation is called the "line of nodes". The plane containing the x , y coordinate is now tipped through an angle relative to the original X, Y plane. The angle is called the angle of nutation. x 1 0 0 x x y = 0 cos sin y = [T2 ] y . z 0 sin cos z z And finally, we rotate about the z , z system through an angle into the x, y, z system. The z axis is called the spin axis. It is coincident with the z axis. The angle is called the spin angle; the angular velocity the spin velocity. x cos sin cos 0 0 x x The final "Euler" transformation is x X coscos  cossinsin y = [T3 ][T2 ][T1 ] Y = sincos  cossincos z Z sinsin y = sin z 0 0 y 1 z = [T3 ] y z . sinsin sincos Y . cos Z X cossin + coscossin sinsin + coscoscos cossin This is the final x, y, z bodyfixed coordinate system for the analysis, with angular velocities x , y , z as shown. The individual coordinate rotations , and give us the angular velocities. However, these vectors do not form an orthogonal set: is along the original Z axis; is along the line of nodes or the x axis; while is along the z or spin axis. 3 This is easily reorganized by taking the components of these angular velocities about the final x, y, z coordinate system using the Euler angles, giving x = sin sin + cos y = sin cos  sin z = cos + (1) (2) (3) We could press on, developing formulae for angular momentum, and changes in angular momentum in this coordinate system, applying these expressions to Euler's equations and develop the complete set of governing differential equations. In general, these equations are very difficult to solve. We will gain more understanding by selecting a few simpler problems that are characteristic of the more general motions of rotating bodies. 3D Rigid Body Dynamics: Free Motions of a Rotating Body
We consider a rotating body in the absence of applied/external moments. There could be an overall gravitational force acting through the center of mass, but that will not affect our ability to study the rotational motion about the center of mass independent of such a force and the resulting acceleration of the center of mass. (Recall that we may equate moments to the rate of change of angular momentum about the center of mass even if the center of mass is accelerating.) Such a body could be a satellite in rotational motion in orbit. The rotational motion about its center of mass as described by the Euler equations will be independent of its orbital motion as defined by Kepler's laws. For this example, we consider that the body is symmetric such that the moments of inertia about two axis are equal, Ixx = Iyy = I0 , and the moment of inertia about z is I. The general form of Euler's equations for a free body (no applied moments) is 4 0 = Ixx x  (Iyy  Izz )y z 0 0 = Iyy y  (Izz  Ixx )z x = Izz z  (Ixx  Iyy )x y (4) (5) (6) For the special case of a symmetric body for which Ixx = Iyy = I0 and Izz = I these equations become 0 0 0 = I0 x  (I0  I)y z = I0 y  (I  I0 )z x = Iz (7) (8) (9) We conclude that for a symmetric body, z , the angular velocity about the spin axis, is constant. Inserting this result into the two remaining equations gives I0 x = ((I0  I)z )y I0 y = ((I0  I)z )x . (10) (11) Since z is constant, this gives two linear equations for the unknown x and y . Assuming a solution of the form x = Ax eit and y = Ay eit , whereas before we intend to take the real part of the assumed solution, we obtain the following solution for x and y x = A cos t y = A sin t (12) (13) equations. Although the components of the vector can be found from the solution of a linear equation, additional work must be done to find the actual position of the body. The body motion predicted by this solution is sketched below. where = z (I  I0 )/I0 and A is determined by initial conditions. Since z is constant, the total angular 2 2 2 2 velocity = x + y + z = A2 + z is constant. The example demonstrates the direct use of the Euler 5 The x, y, z axis are body fixed axis, rotating with the body; the solutions for x (t), y (t) and z give the components of following these moving axis. If angular velocity transducers were mounted on the body to measure the components of , x (t), y (t) and z from the solution to the Euler equations would be obtained, shown in the figure as functions of time. Clearly, as seen from a fixed observer this body undergoes a complex spinning and tumbling motion. We could work out the details of body motion as seen by a fixed observer. (See Marion and Thornton for details.) However, this is most easily accomplished by reformulating the problem expressing Euler's equation using Euler angles. Description of Free Motions of a Rotating Body Using Euler Angles
The motion of a free body, no matter how complex, proceeds with an angular momentum vector which is constant in direction and magnitude. For bodyfixed principle axis, the angular momentum vector is given by H G = Ixx x + Iyy y + Izz z . It is convenient to align the constant angular momentum vector with the Z axis of the Euler angle system introduced previously and express the angular momentum in the i, j, k "Euler" transformation to the angular momentum vector expressed in the X, Y, Z system, H G = {0, 0, HG }. system. The angular momentum in the x, y, z system, H G = {Hx , Hy , HZ } is obtained by applying the 6 H G = HG sin sin i + HG sin cos j + HG cos k (14) Then the relationship between the angular velocity components and the Euler angles and their time derivative given in Eq.(13) is used to express the angular momentum vector in the Euler angle coordinate system. HG sin sin HG sin cos HG cos = Ixx x = Ixx (sin sin + cos ) = Iyy y = = Izz z = Iyy (sin cos  sin ) Izz ( cos + ) (15) (16) (17) where HG is the magnitude of the H G vector. The first two equation can be added and subtracted to give expressions for and . Then a final form for spin rate can be found, resulting in cos2 sin2 = HG ( + ) Ixx Iyy 1 1 = HG (  ) sin sin cos Ixx Iyy = HG ( 1 cos2 sin2   ) cos Izz Ixx Iyy (18) (19) (20) For constant HG , these equations constitute a first order set of nonlinear equations for the Euler angle , and and their time derivatives , and . In the general case, these equations must be solved numerically. Considerable simplification and insight can be gained for axisymmetric bodies for which Ixx = Iyy = I0 and Izz = I. In this case, we have 7 = HG /I0 = 0 1 1 = HG (  ) cos I I0 (21) (22) (23) Thus, in this case, the nutation angle is constant; the spin velocity is constant, and the precession velocity is constant. Note that if I0 is greater that I, and are of the same sign; and if I0 is less than I, and are of opposite signs; for I0 = I, the problem falls apart since we are now dealing with the inertial equivalent of a sphere which will not exhibit precession. We now examine the geometry of the solution in detail. We assume that the body has some initial angular momentum that could have arisen from an earlier impulsive moment applied to the body or from a set of initial conditions set by an earlier motion. In this case, we would know both the magnitude of the angular momentum HG and its angle from the spin axis. The geometry of the solution is shown below. We align the angular momentum vector with the Z axis. For general motion of an axisymmetric body, the angular momentum H G and the angular velocity vectors are not parallel. Using the spin axis z as a reference, the angular momentum H G makes an angle with the spin axis; the angular velocity makes an angle with the spin axis. For this body, although the angular momentum is not aligned with the angular velocity, they must be in the x, z plane; this is a consequence of symmetry: that Iyy = Ixx = I0 . Therefore both y and HGy must be zero. We examine the system in the plane formed by H g and , as shown in the figure. The relation between the angular velocities and 8 must be such that the vectors I0 y j + Iz k = H G . Since H G makes an angle with the z axis, and makes an angle with the Z axis, we have tan = HGx /HGz = (I0 x )/(Iz ) = (I0 /I)tan. (24) What we would see in this motion is a body spinning about the z axis with and "precessing" about the Z axis with this is essentially a definition of precession. The vector, which is the instantaneous axis of rotation, is in the x, z plane. We now focus on the Z axis, and investigate the motion that can exist for a freely rotating body with the given parameters when it has an angular momentum in the Z direction. We see that a body rotating about its own axis with angular velocity at an angle from the Z axis, will also undergo a steady precession of about the Z axis, keeping the angular momentum H G directed along the Z axis. The instantaneous axis the vertical. The motion is that of the body cone rolling around the space cone. of rotation maintains a fixed angle from the spin axis z. The vector maintains a fixed angle  from A variety of useful and general relations can be written between the various components of angular velocity and angular momentum H, the Euler angles and and the angles and . Using the notation HG and 9 for the magnitude of the H G and vectors, we have x = z = sin (25) (26) (27) (28) (29) (30) cos 2 2 2 HG = Hx + Hz = (x I0 )2 + (z I)2 = I0 sin2 + I 2 cos2 (sin2 + (I/I0 )2 cos2 ) = = (1  (I/I0 )) cos Two different solution geometries are shown: one for which I0 > I; one for which I0 < I. Consider first the case where I < IO . This would be true for a long thin body such as a spinning football, a reentering slender missile or an F16 in roll. In this case, the spin and the precession are of the same sign. The body precesses about the angular momentum vector while spinning. The vector is the instantaneous axis of rotation. The instantaneous axis of rotation is the instantaneous tangent between the body cone and the space cone. The outside of the body cone, shown in the figure as a cone of halfangle aligned along the body axis, rotates about the outside of the space cone, shown in the figure as a cone of halfangle  with its axis aligned along the angular momentum vector. This is called direct precession. For direct precession, < . Now consider the case where I > I0 ; this would be true for a frisbee, a flat spinning satellite, or a silver dollar tossed into the air. 10 In this case, the spin and the precession are of opposite signs. This means that the vector is on the other side of the angular momentum vector relative to the spin axis z. The body still precesses about the angular momentum vector while spinning. The vector is still the instantaneous axis of rotation. But now, the inside of the body cone rotates about the outside of the space cone. The angle is greater than the angle . The body cone shown in the figure as a cone of halfangle aligned along the body axis; the space procession; the rotations are in opposite directions. Depending upon body geometry, one of these solutions would be obtained whenever the angular momentum vector is not directed along a single principle axis. This would occur if an impulsive moment is applied to a body along any axis which is not a principle axis. An example of this is discussed below. cone has a halfangle  and is aligned along the angular momentum vector. This is called retrograde Extreme Aircraft Dynamics
The dynamics of aircraft have traditionally been dominated by aerodynamic forces. The location of the center of mass relative to the aerodynamic center was an important consideration as was the question of whether the vertical tail provided enough yaw moment to keep the vehicle flying straight. The details of the response of aerodynamic forces to small disturbances of the vehicle in pitch, roll and yaw, determined the stability of the aircraft and the frequency of the various longitudinal and lateral stability modes. With the introduction of highperformance fighter aircraft, whose moments of inertia about all three axes were comparable, which had the ability to initiate rapid rolling, and whose roll axis was not a principal axis, we entered into a new flight regime where, at the limit, dynamics dominated aerodynamics. Consider this limit, where dynamics dominates aerodynamics. We have a F16 at high altitude where atmospheric density is small, and we have a test pilot giving a strong roll input about the aircraft roll axis which is not a principal axis. For simplicity, we take the y and z inertias to be equal and equal to I0 . Low aspect ratio aircraft have moments of inertia in roll that are less than that in pitch or yaw so that this example is given by the case I0 > I and we may apply the freebody spinning solution just discussed. We consider that an impulsive moment/torque is applied about the roll axis and inquire what freebody motion this would set up. At this limit, we are neglecting aerodynamics forces. In agreement with our previous analysis, the moment about the x axis would produce an angular momentum about the x axis. But since the x axis is not a principal axis, we would initiate a coning motion as shown. 11 This could come as quite surprise to a pilot. The question of what happens next is dependent upon the details of the aerodynamic forces, but just to comment on the historical record: in the first days of testing highperformance fighter aircraft, several test pilots lost control of their aircraft, in some cases with fatal results. This phenomenon, called roll coupling, is now well understand and incorporated into the design and testing of new fighter aircraft. ADDITIONAL READING J.L. Meriam and L.G. Kraige, Engineering Mechanics, DYNAMICS, 5th Edition 7/9 W.T. Thompson, Introduction to Space Dynamics, Chapter 5 J. H. Ginsberg, Advanced Engineering Dynamics, Second Edition, Chapter 8 J.B Marion and S.T. Thornton, Classical Dynamics, Chapter 10 J.C. Slater and N.H. Frank, Mechanics, Chapter 6 12 MIT OpenCourseWare http://ocw.mit.edu 16.07 Dynamics
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This note was uploaded on 05/02/2011 for the course DYNAM 101 taught by Professor Matuka during the Spring '11 term at MIT.
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