Report

Share

•4 likes•1,895 views

•4 likes•1,895 views

Report

Share

This paper presents the study of the dynamics and control of an axial variable structure satellite (asymmetric platform and an axisymmetric rotor). Inertia moments of the rotor change slowly over time. The dynamics of the satellite is described by using ordinary differential equations with Serret-Andoyer canonical variables. For undisturbed motion, the stationary solutions are found, and their stability is studied. The control law is obtained for the satellite with variable structure on the basis of the stationary solutions. By means of computer numerical simulations, we have shown that the motion of the satellite controlled by founded internal torque is stable.

- 1. Vladimir S. Aslanov aslanov_vs@mail.ru THE DYNAMICS AND CONTROL OF VARIABLE STUCTURE AXIAL SATELLITE GYROSTAS Theoretical Mechanics Department www.termech.ru Samara State Aerospace University, Russia www.ssau.ru 2012
- 2. Statement of the problem • We study dynamics and control of an axial satellite gyrostat with variable structure and free of external torques. • Depending on the relationship of inertia moments the paper discusses three basic types of gyrostats: oblate, prolate and intermediate and the two boundary types: oblate-intermediate, prolate-intermediate. • During the motion of a satellite the inertia moments of the rotor change slowly in time, which may be related to the deployment of solar panels, solar sails and other constructions. In this case, the satellite gyrostat can take place all the types from prolate to oblate or vice versa. The dynamics of a rotating body studied famous mathematicians of all time as Euler, Cauchy, Jacobi, Poinsot, Lagrange and Kovalevskaya. The research of the dynamics of rotating bodies is very important for numerous applications such as the dynamics of satellite-gyrostat and spacecraft. In this area we note the papers scientists as Rumyantsev, Sarychev, Wittenburg, Cochran, Hall, Rand, Hughes, Kinsey, Elipe and Lanchares , Kuang,Tong et al. 2
- 3. Statement of the problem The purpose of this report is to find the control for the satellite gyrostat. The control law should allow keeping a stable motion in the vicinity of the equilibrium position for slowly changing of the rotor inertia moments in time. The main idea of the stabilization method is conservation of the stable position by selecting the internal torque. We solve the following tasks: • The dynamics of the satellite is described by using ordinary differential equations with Serret-Andoyer canonical variables. • The equations of motion have a simple dimensionless form and contain a small parameter. • For undisturbed motion, when the inertia moments of the satellite gyrostat aren’t changed and the internal torque is equal to zero the stationary solutions are found, and their stability is studied. • For disturbed motion of the gyrostat with variable structure the control law obtained on the basis of the stationary solutions. • Several numerical simulations are given to confirm effectiveness of the founded control law. 3
- 4. The motion equations The equations of the motion for the angular momentum variables of an axial gyrostat with zero external torque may be written as dh1 I 2 I3 dh2 I3 IP h3 h2 h3 , h1 ha , dt I 2 I3 dt I3 IP (1) dh3 IP I2 h2 dha h1 ha , ga dt I2 IP dt where ei are principal axes; ga is the torque applied by P on R about e1; ha=IS( S+ 1) is the angular momentum of R about e1; h1=I1 1+Is s is the angular momentum of P+R about e1; hi=Ii i are the angular momentum of P+R about ei (i=2,3); Ii are the moments of inertia of P+R about ei i are the angular velocities of P about ei; s is the angular velocity of R about e1 relative to P. IP=I1 - IS is the moment of inertia of P about e1; Is is the moment of inertia of R about e1; IR is the moment of inertia of R about e2, e3 4
- 5. The motion equations The equations of the motion can be simplified by using two canonical Serret-Andoyer (S-A) variables: l, L (Figure 1). Using the change of variables h1 L, h2 G2 L2 sin l , h3 G2 L2 cos l (2) We obtain the equations of the motion in terms of the S-A variables dl 1 1 L ha L a b (b a ) cos 2l , dt IP 2 dL 1 (b a) G 2 L2 sin 2l , (3) dt 2I P dha ga dt IP IP where a , b . (4) I2 I3 Assume that I2 I3 , b a (5) Fig. 1 The axial gyrostat 5
- 6. The motion equations The transformation of the Equations (3) to a dimensionless form is obtained by using four parameters: L ha G ga I p s , d , t , ga 2 abs s 1 (6) G G Ip G The change of variables (6) leads to the equivalent set of dimensionless equations dl s s d a b (b a) cos 2l , d 2 ds 1 (b a) 1 s 2 sin 2l , (7) d 2 d d ga d Let us assume the inertia moments of the axisymmetric rotor R about e1, e2, e3 are continuous functions of the dimensionless time (8) IS I S ( ), I R IR ( ) A separate study is showed that the form of the motion Equations (7) doesn’t change in this case. We assume the derivative of the rotor inertia moments and the internal torque by small dI S dI R , , ga O (9) d d where is a small parameter. 6
- 7. The undisturbed motion At ε=0 the disturbed Equations are reduced to an undisturbed canonical system H s l s d a b (b a ) cos 2l , s 2 (10) H 1 s (b a ) 1 s 2 sin 2l l 2 a, b, d const where H is Hamiltonian by 1 s2 s2 H l, s a b (b a) cos 2l sd h const. (11) 4 2 Solving the Eq. (11) with respect to cos2l, we get an equation of the phase trajectory: a b 2 s 2 4ds 4h a b (12) cos 2l 1 s2 b a 7
- 8. The undisturbed motion Canonical Eq. (10) have four stationary solutions: cos 2l* 1, s* d/ 1 b , (13) cos 2l* 1, s* d/ 1 a , (14) cos 2l* 2 a b 2d / b a , s* 1, (15) cos 2l* 2 a b 2d / b a , s* 1 (16) Determined by the stability of the solutions. It’s proved12 that the stationary solution (14) is stable if b 1 IP I3 and unstable if b 1 IP I3 (17) the stationary solution (15) is stable if a 1 IP I2 and unstable if a 1 IP I2 the stationary solutions (16) and (17) are unstable always. 8
- 9. The undisturbed motion Let us give complete classification of all types gyrostats depending on the ratio of the inertia moments: 1. Oblate Gyrostat: Ip I2 I3 b a 1 2. Oblate-Intermediate Gyrostat: Ip I2 I3 b a 1 3. Intermediate Gyrostat: I2 Ip I3 b 1 a 4. Prolate-Intermediate Gyrostat: I2 Ip I3 b 1 a 5. Prolate Gyrostat: I2 I3 Ip 1 b a Gyrostats 1, 3 and 5 correspond to areas with the same numbers in Figure 2. Gyrostat 2 corresponds to the border between areas 1 and 3 and Gyrostat 4 – to the border between areas 3 and 5. FIGURE 2. Partition of the parameter plane a 1, b 1 9
- 10. The undisturbed motion Five gyrostat types determined by ratio of the inertia moments for different kinematic conditions # Type Subtype Conditions Kinematic conditions a IP>I2>I3 |d/(1-a)|<1 1 Oblate b (b>a>1) |d/(1-a)|≥1 Oblate- IP=I2>I3 (b>a=1) |d/(1-a)| 2 intermediate a |d/(1-a)|≥1 I2>IP>I3 3 Intermediate b |d/(1-a)|<1, |d/(1-b)|<1 (b>1>a) c |d/(1-b)|≥1 Intermediate- I2>IP=I3 (b=1>a) |d/(1-b)| 4 prolate a I2>I3 >IP |d/(1-b)|≥1 5 Prolate b (1>b>a) |d/(1-b)|<1 10
- 11. Phase space: Oblate gyrostat There are two types of the phase space when I p I2 I3 b a 1 d d If 1 (1a case) the critical points are defined as If 1 (1b case) 1 a 1 a saddles: saddles: ls k , ss d / (1 a) 2 a b 2d 2 cos 2ls , ss sgn d b a centers: centers: lc k , sc d/ 1 b lc k , sc d/ 1 b 11
- 12. Phase space: Oblate-intermediate (2), Intermediate (3.a) There is the same phase space for the oblate-intermediate and intermediate gyrostats abs s 1 Oblate-intermediate (case 2) Intermediate (case 3.a) IP I2 I3 (b a 1) I2 IP I3 (b a 1), d / (1 a) 1 Critical points Critical points saddles saddles 2 a b 2d 2 a b 2d cos 2ls , ss sgn d cos 2ls , ss sgn d b a b a centers centers lc k , sc d/ 1 b lc k , sc d/ 1 b 12
- 13. Phase space: Intermediate gyrostat I2 IP I3 (b 1 a) Intermediate gyrostat (3b case) has two sets of the critical points for each type saddles 2 a b 2d 2 a b 2d cos 2ls , ss sgn d cos 2ls , ss sgn d b a b a centers lc k , sc d/ 1 b lc /2 k , sc d/ 1 b 13
- 14. Phase space: Intermediate (3.c), Intermediate-prolate (4) There is the same phase space for the intermediate (3.c) and intermediate-prolate gyrostats Intermediate (3.c) Intermediate-prolate (4) I2 IP I3 (b a 1), d b 1 I2 IP I3 (b 1 a) Critical points Critical points saddles saddles 2 a b 2d 2 a b 2d cos 2ls , ss sgn d cos 2ls , ss sgn d b a b a centers centers lc k , sc d/ 1 b lc k , sc d/ 1 b 14
- 15. Phase space: Prolate gyrostat There are two types of the phase space when I 2 I3 I P (1 b a) d d Critical points for 5a case 1 Critical points for 5b case 1 1 b 1 b saddles saddles 2 a b 2d cos 2ls , ss sgn d ls 0, ss d / (1 b) b a centers centers lc k , sc d/ 1 a lc k , sc d/ 1 a 2 2 15
- 16. Variable moments of inertia We study the stabilization of the gyrostat with the axisymmetric rotor. Rotor has a variable inertia moments: I R = I R (t ), I S = I S (t ) (18) For example we can see deployment a solar sail IP IP Equations (10) for time-varying a ( ) , b( ) have the same form: I2 ( ) I3 ( ) H s l s d a b b a cos 2l s 2 H 1 s b a 1 s 2 sin 2l (19) l 2 d ' = ga where ga is internal torque (control) 16
- 17. Phase space deformation of gyrostat with variable moments of inertia Here you can see phase space deformation when gyrostat changes it’s type from oblate to prolate due to change (increase) in the inertia moments of the rotor. IS ( ) a( ) IR ( ) b( ) 17
- 18. Gyrostat stabilization We claim that s s* while I R = I R (t ) I S = I S (t ) • To keep stable point for I P I 2 (Oblate gyrostat) d s* const (20) 1 b • After differentiating d (1 b) s* we get a control law for the internal torque : IP IR ¢ d ' = g a = s* (1- b) ' = s* (21) I 32 • To keep stable point for I 2 I P (Prolate gyrostat) d s* const (22) 1 a • After differentiating d (1 b) s* we get a control law for the internal torque : IPIR¢ d ' = g a = s* (1- a ) ' = 2 s* (23) I2
- 19. Numerical example To confirm control efficiency we consider a numeric example. Suppose that the rotor has deployable construction (solar array or solar sail). This leads to time-dependent inertia moments of the rotor: I R (t ) = I R 0 - k2t , I S (t ) = kS I R (t ) - gyrostat changes its type from prolate to oblate. Uncontrolled gyrostat with variable moments of inertia s0=0.5, s0 = 0.2 s Relative angular velocity s • In this case gyrostat lose its orientation: the angle between e1 axis and angular momentum vector changes sufficiently. • Changes in inertia moments affect the angular velocities of R about e1 . 19
- 20. Numerical example Controlled gyrostat with variable inertia moments (s0=0.5, s0 = 0.2) IPIR¢ d ' = g a = s* (1- a ) ' = 2 s* I2 s remains practically constant: s=s0=0.5 (|s-s0|<2 10-7) Control torque ga( ) Relative angular velocity s • Angular velocities of R about e1 relative to P is decreased. • System preserves its state in phase space, despite to changes in the inertia moments of the rotor. 20
- 21. Numerical example • Here we can see how internal torque affects to the angular velocities of the gyrostat with variable inertia moments. Uncontrolled gyrostat has oscillations in angular velocities that can cause unwanted high accelerations of the gyrostat. • The angular velocities of the controlled gyrostat are monotonic functions of and we can expect that small accelerations. Platform angular velocities Case 1: Uncontrolled gyrostat Case 2: Controlled gyrostat 2 2 1 1 3 3 21
- 22. Conclusion 1. The dynamics of the dual-spin gyrostat spacecraft is described by using ordinary differential equations with Serret-Andoyer canonical variables. 2. The equations of motion have a simple dimensionless form and contain a small parameter. 3. For undisturbed motion the stationary solutions are found, and their stability is studied for the all the types of the gyrostats. 4. For disturbed motion of the gyrostat with variable structure the control law obtained on the basis of the stationary solutions. 5. It’s shown that uncontrolled gyrostat satellite can lose its axis orientation and because of change in moments of inertia of the rotor. 6. The oscillations of the angular velocities and accelerations of the gyrostat accompany changes in moments of inertia of the rotor. 7. Obtained internal torque keeps axis orientation of the gyrostat and get angular velocities and accelerations monotonic functions of time. 22
- 23. References [1] Cochran, J. E. Shu, P.-H. and Rew, S. D. “Attitude Motion of Asymmetric Dual-Spin Spacecraft” Journal of Guidance, Control, and Dynamics, V. 5, n 1, 1982, pp. 37-42. [2] Hall, C. D. and Rand, R. H.: “Spinup Dynamics of Axial Dual-Spin Spacecraft” Journal of Guidance, Control, and Dynamics. V. 17, n. 1, 1994, pp. 30-37. [3] Hall C.D. “Escape from gyrostat trap states” J. Guidance Control Dyn. V. 21. 1998. pp. 421-426. [4] A. Elipe and Lanchares “Exact solution of a triaxial gyrostat with one rotor” Celestial Mechanics and Dynamical Astronomy V. 101 (1-2). 2008. pp. 49-68. [5] Lanchares, V., Iñarrea, M., Salas, J.P. “Spin rotor stabilization of a dual-spin spacecraft with time dependent moments of inertia” Int. J. Bifurcat. Chaos 8. 1998. pp. 609-617. [6] Hughes, P.C. “Spacecraft Attitude Dynamics” Wiley, New York, 1986. [7] Kinsey K.J., Mingori D.L., Rand R.H. “Non-linear control of dual-spin spacecraft during despin through precession phase lock” J. Guidance Control Dyn. 19, 1996, 60-67. [8] Kane,T.R. “Solution of the Equations of rotational motion for a class of torque-free gyrostats” AIAA Journal. V. 8. n 6. 1970. pp. 1141-1143. [9] El-Gohary, A. I. “On the stability of an equilibrium position and rotational motion of a gyrostat” Mech. Res. Comm. 24. 1997. pp. 457-462. 23
- 24. References [10] Neishtadt A.I., Pivovarov M.L. “Separatrix crossing in the dynamics of a dual-spin satellite” J. of Applied Mathematics and Mechanics. 64. 2000. pp. 741-746. [11] Aslanov, V. S., Doroshin, A.V. “Chaotic dynamics of an unbalanced gyrostat” J. of Applied Mathematics and Mechanics 74. 2010. pp. 524-535. [12] Aslanov, V. S. “Integrable cases in the dynamics of axial gyrostats and adiabatic invariants” Nonlinear Dynamics, Volume 68, Issue 1 (2012), Page 259-273 (DOI 10.1007/s11071-011-0225-x). [13] Aslanov, V. S. “Dynamics of free dual-spin spacecraft” Engineering Letters (International Association of Engineers). 19. 2011. pp. 271–278. [14] Sarychev, V. A., Guerman, A. D., and Paglione, P. “The Influence of Constant Torque on Equilibria of Satellite in Circular Orbit” Celestial Mechanics and Dynamical Astronomy, Vol. 87, No. 3, 2003. [15] J. Wittenburg Dynamics of Systems of Rigid Bodies. B.G. Teubner Stuttgard, 1977. [16] V. A. Sarychev and S. A. Mirer “Relative equilibria of a gyrostat satellite with internal angular momentum along aprincipal axis” Acta Astronautica, 49(11). 2001. pp. 641–644. [17] Rumyantsev V. V. “On the Lyapunov’s methods in the study of stability of motions of rigid bodies with fluid-filled cavities” Adv. Appl. Mech. 8. 1964. pp. 183-232. [18] Serret, J.A., “Me moiresurl'emploi de la me thode de la variation des arbitrairesdans theorie des mouvementsde rotations”. Memoires de l’Academie des sciences de Paris, Vol. 35, 1866, pp. 585-616. [19] Andoyer H. “Cours de Mechanique Celeste” Vol. 1, Gauthier-Villars. 1923. 24