Research Article Variation of the Equator due to a Highly Inclined and Eccentric Disturber

Hindawi Publishing Corporation Mathematical Problems in Engineering Volume 009, Article ID 467865, 10 pages doi:10.1155/009/467865 Research Article Variation of the Equator due to a Highly Inclined and Eccentric Disturber Clair do Nascimento and adashi Yokoyama Universidade Estadual Paulista, IGCE-DEMAC Caixa Postal 178, CEP 13.500-970 Rio Claro, SP, Brazil Correspondence should be addressed to adashi Yokoyama, tadashi@ms.rc.unesp.br Received 18 June 009; Accepted 19 October 009 Recommended by Dane Quinn he New Horizons project is currently in progress, but until recently years ago, a mission to Neptune-riton System predicted in the mid term 008 013 was one of the priorities of NASA s Solar System Exploration theme. Any way, it is important to increase our knowledge on the dynamics of the inner satellites of Neptune, since according to some authors, this was a key question in the mission to Neptune-riton system. In a previous work, we presented the expansion of the disturbing function for the dynamics of this system. Here we derive the averaged classical equations of the precession of the equator for this problem. he highly inclined and retrograde orbit of riton makes this problem very unusual. herefore, the classical truncations in the inclinations are not acceptable, so that the precession equations must be obtained in closed form for the inclination. With a significant mass and due to its distance from Neptune, which is continuously decreasing, riton should exert in the future, important precession on Neptune s equator. he effects of this precession on the inner satellites are shown, including some resonant cases predicted in the future. Although riton s orbit is almost circular, no expansion in the eccentricity is needed. Copyright q 009 C. do Nascimento and. Yokoyama. his is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. 1. Introduction Some years ago, the exploration of the Neptune system in the next ten years was posed as an important priority of NASA s Solar System Exploration theme 1. Although the New Horizons project is now the top priority for the far reaches of the solar system, most probably, to design a mission to explore the Neptune-riton system will be just a mater of time. he authors 1 raised some important questions about the dynamics stability of the arcs and inner satellites of Neptune. In order to give support to the mission, we must increase our knowledge on the dynamics of this system. In this work we derive the classical equations of the precession for the equator of Neptune. Basically, this equator is disturbed by the presence of riton since it has a remarkable mass: m /M N.09 10 4. m, M N are

Mathematical Problems in Engineering z Z Ĩ Equator y Y X Ω χ x Reference plane Figure 1: XYZ:inertialsystem,xyz: moving system fixed on the equator. the masses of riton and Neptune, resp.. Moreover, riton s inclination with respect to Neptune s equator is quite unusual 157.35 0. In a short time span, this precession should not be so important on the dynamics of the inner satellites. However, for a longer time more than 600 years, thiseffect must be investigated. his work is organized in the following way: in Section the averaged precessional equations for Neptune s equator considering arbitrary inclination obtained. Some authors hypothesize that in the past, the eccentricity of riton e, might have been very high. herefore, the precessional equations are also obtained for arbitrary e.insection 3, we discuss the definition of the invariable plane and the existence of a corresponding equilibrium solution when we assume circular orbit for riton. Considering the current dynamics of Neptune-riton system, several authors have improved the ephemerides and data of the small satellites e.g., Owen et al. 3. Here, some numerical simulations showing the effects of the precession, particularly for the future : 1 and 3 : 1 resonances involving riton and Proteus, are presented. Section 4 is devoted to the conclusions.. he Ĩ and Ω equations Let XYZ be an arbitrary reference system inertial and a moving system xyz fixed on the equator of Neptune see Figure 1. We define Ĩ inclination of the equator and Ω node of the equator 4. Due to the presence of a massive satellite riton, the equator of Neptune will be disturbed. Let be the associated torque due to riton and let W be the corresponding oblateness potential of Neptune: W GM Nm J R N r 3 1 3sin β,.1 where G is the gravitation constant, M N and m are the masses of Neptune and riton, respectively. he oblateness constant is J, β is the riton s latitude and r is the radial distance

Mathematical Problems in Engineering 3 Neptune-riton in the xyz system. he equatorial radius of Neptune is indicated by R N. hen: L, M, N r W,. where is the usual gradient operator with respect to riton coordinates and L, M, andn are the components of the torque, that is: W L y W M x W N x z z y W z W z W y y, x, x,.3 where x,y and z are the cartesian coordinates of riton with respect to the moving system xyz. On account of the rotational symmetry, we can show that N 0. o this end, since β is the latitude we have: sin β z /r. hen a direct calculation shows that W depends on riton coordinates only through r and z /r, therefore: W W r, z W x r W r, r x y z 1/, x r, W y W r y r..4 Substituting these last two relations in N given in.3, wegetn 0. Now, let w p N,q N,w N be the rotation vector of Neptune. According to Euler s dynamical equations: ṗ N C A A w Nq N L A, q N C A A w Np N M A,.5 ẇ N N C 0, where A B and C are the moments of inertia of the planet. From the geometric equations, w can be expressed in terms of the inertial XYZ system: p N sinĩ sin χ Ω cos χ Ĩ, q N sinĩ cos χ Ω sin χ Ĩ,.6 w N cosĩ Ω χ.

4 Mathematical Problems in Engineering aking the time derivative of p N, ṗ N cosĩ Ĩ sin χ Ω sinĩ χ cos χ Ω sin χ Ω sin χ χ Ĩ cos χ Ĩ..7 Assuming that the polar component of the rotation of the planet is dominant, the following quantities: Ĩ Ω, Ĩ e Ω e Ω can be neglected when compared to χ 5, 6. hen, ṗ N sinĩ χ cos χ Ω sin χ χ Ĩ..8 Substituting ṗ N e q N in the first Euler s equation, L A Ω χ cos χ Ĩ sin Ĩ χ sin χ C A w N Ω sinĩ cos χ sin χ Ĩ w N Ω sinĩ cos χ sin χ Ĩ..9 Substituting w N cos Ĩ Ω χ and neglecting terms factored by Ω and Ĩ Ω, we have C A w N sinĩ cos χ Ω sin χ Ĩ L A..10 Similarly, putting q N and p N into the second Euler dynamical equation, we obtain: C A w N sinĩ sin χ Ω cos χ Ĩ M A..11 Now we can eliminate L and M in the above equations. Defining W 0 Gm M N J R N /, we have W W 0 3z r 5 1, r 3 [ W 3z W 0 y r r 5 1 r 3 ] y r,.1 [ W 3z W 0 z r r 5 1 r 3 ] z r W z,

Mathematical Problems in Engineering 5 and so, L W y z W z y W z y,.13 where W z 6W 0 z /r 5. Similarly, M W zx.from.10 and.11, Ĩ Ω sin W z y cos χ x sin χ, Cw N Ĩ W z Cw N x cos χ y sin χ..14 If a sequence of three rotations, Ω, Ĩ, isχ are applied on the system XYZ, it will coincide with xyz. herefore we can write x, y,andz in terms of the well-known elliptic orbital elements of riton. x r cos f w cos Ω r sin f w sin Ω cos I, y r cos f w sin Ω r sin f w cos Ω cos I,.15 z r sin f w sin I, where r, f, w, Ω, w,andi refer to classical orbital elements of riton referred to X, Y, Z inertial system. Finally, averaging the resulting equations with respect to the mean anomaly of riton, the precessional equations, without any restriction on the inclination I or on the eccentricity e,are Ĩ Ω F 0 4a 3 1 e F 0 4a 3 1 e ] 3/ [sinĩ sin I sin Ω Ω cosĩ sin I sin Ω Ω, 3/ 1 3 cos I sin I cos I cos Ĩ cos Ω Ω cosĩ sinĩ sin I cosĩ cos Ω Ω,.16 where F 0 3Gm M N R N J Cw N..17 Notice that, as expected in this approximation, these two equations are decoupled from χ equation.

6 Mathematical Problems in Engineering R n 1 R n 1 Invariable plane t 1 S Ĩ Equator a riton s orbit t 1 π I b Figure : t 1 is perpendicular to the orbital plane of riton, n 1 is perpendicular to Neptune s equator, and R is the resulting vector which defines the invariable plane. 3. he Invariable Plane In this section, we define the reference plane. Let t 1 and n 1 be the orbital angular momentum of riton and rotation angular momentum of Netpune, respectively. hen R t 1 n 1 is a constant vector. herefore, the plane perpendicular to the direction of R is invariable see Figure, and it will be adopted as our reference plane. he dynamics of the system involving Ĩ, Ω, Ω,andI shows an interesting solution in this invariable plane. o see that, let us assume riton in a circular Keplerian orbit. In this case, we have t 1 m n a, where n is the mean motion, and m is the riton s mass. On the other hand, n 1 Cw N, where C is the polar moment of inertia of Neptune and w N is its angular velocity of rotation spin rate. Now,fromFigure, we have s sin π I, sin Ĩ scw m n a N 3.1 that is, the inclination Ĩ of the invariable plane is given by: sin Ĩ m n a sin I Cw N. 3. In order to have the complete set of equations that govern the motion of the equator, we have to consider.16 and also the corresponding equations for I and Ω. hey are di dt dω dt 1 R J n a sin I, Ω 1 n a sin I R J I, 3.3

Mathematical Problems in Engineering 7 where R J is the disturbing function due to the oblateness of Neptune which is written with respect to the following invariable plane: R J S 0 [ 1 1 3 sin Ĩ 1 3 sin I 3 Ĩ 8 sin sin I cos Ω Ω 3 8 sin Ĩsin I cos Ω Ω ], 3.4 where GM N R N S 0 J [ a 3 1 e 3/ ]. 3.5 For Ω Ω π, we easily see that Ω S İ Ĩ 0, sinĩ sin Ĩ I, 3.6 Ω 3 GM N R N J 4 n a 5 sin I sin Ĩ I, where S 3Gm M N R N J. 3.7 4Cw N a 3 herefore, Ω Ω 3GM NR N J 4a 3 sin 1 Ĩ I n a sin I m, 3.8 Cw N sinĩ that is, the term inside the brackets is automatically zero provided the reference plane is the invariable plane see 3.. In this case; Ω Ω 0, I and Ĩ are constants; Ω and Ω are synchronous. his means that the precession rate of the Neptune s equator is the same of the riton s node on the invariable plane 688 years. Itisalsoeasytoshowthat Ω Ω π defines a stable periodic solution of the system simple calculations show that such solution does not exist for Ω Ω 0. his means that it is very convenient to choose the invariable plane as the reference for our purposes.

8 Mathematical Problems in Engineering 1. 1 Inclination 0.6 Eccentricity 0.5 0 0 1000 000 Years 0 0 40000 80000 Years a b 10.5 90 Inclination 9 Inclination 45 7.5 0 500 1000 Years 0 0 40000 80000 Years c d Figure 3: a, c : the lighter points were obtained taking into account the Ĩ and Ω equationsinthe integration, while in the thick points these contributions were neglected. b, d : time variation of the eccentricity b and inclination d for two orbits. Initially their paths are similar, but when their semimajor axes enter the : 1 resonance region, a jump appears in the eccentricity b, first in the orbit which contains the effect of the precession. he same occurs for the inclination d, that is, the precession accelerates the onset of the jump of the inclination. 4. Some Effects on the Inner Satellites Initially we tested our.16 for the case of Earth and Mars. As expected, the results agree quite well with very known values 6000 and 175000 years for Earth and Mars, resp.. For the Neptune s equator, considering a 14.063R N, our numerical experiments show 688 years for the period of precession, referred to the invariable plane Neptune-riton. his period is rather sensitive for the adopted value of the semimajor axis of riton. In this section we test the effect of the precession of Neptune s equator on an inner satellite of this planet. In Figure 3, we always integrate two orbits. he lighter points in the left panels, correspond to the orbits when we include the precessional effect, while the thick points come from the orbit

Mathematical Problems in Engineering 9 when we neglect.16. he inclinations are referred to the invariable plane. We consider a test particle Proteus disturbed by riton. In the integration of the equations of the motion, we used our averaged disturbing function R as described Yokoyama et al. 7 which is very efficient for this case. he initial conditions for Proteus are a 4.751, e 0.0005, w 0 0, Ω 90 0, I 1 0 Figure 3 a and I 10 0 Figure 3 c,andλ 90 0, while for riton we consider a 14.35, e 0.000016, w 0 0, Ω 70 0, I 157 0,andλ 70 0.heeffect of the precession is very clear: Figure 3 a, shows the variation of Proteus inclination which remains confined in a very narrow interval when precession equations are considered. In Figure 3 c, in opposition to the above panel, we take Proteus at high inclination 10 0. hen, although the periods are different, the inclinations of both orbits undergo a large variation. Moreover, there is quite clear a periodic oscillation of about 670 years, which is related to the precession of the node Ω. Panels on the right, refer to the variation of the eccentricity Figure 3 b and inclination Figure 3 d of Proteus in the case of future : 1 resonance. As described by Yokoyama 8 and Yokoyama et al. 7, due to the tides, riton is falling down to the planet, so that, its orbital period will be in a 3 : 1 or : 1 orbital resonance with Proteus in the future. For these two panels, instead of the averaged equations, we integrated the exact equations and we applied a slow dissipation on the semimajor axis of riton in order to simulate the tidal effect. As pointed in Yokoyama et al. 7 the eccentricity suffers a strong variation and Proteus can be ejected. he effect of the precession is to anticipate the ejection. However, this is not a general rule, since some tests performed in the 3 : 1 resonance showed different results, that is, the precession can delay the ejection. More tests must be carried on in order to clarify these details. 5. Conclusion In this work, we derived the classical averaged equations for the precession of the Neptune s equator, extending for the case of arbitrary inclination and eccentricity of the disturber. Due to the high retrograde inclination of riton, these equations must be obtained in closed form for this inclination. If the invariable plane is chosen as the reference plane, the averaged equations of the precession in the case of e 0, satisfy an equilibrium solution where Ω and Ω remain synchronous while Ĩ and I are constants. he numerical experiments show that, when the precessional equations are considered, the inclination of an inner satellite of Neptune Proteus remains confined in a very narrow range, that is, the variation of the inclination with respect to the invariable plane is very small. However for high initial inclination 10 0 of the inner satellite, this confinement is not preserved anymore, that is, even considering the precessional effect, the amplitude of the variation of the inclination is significant. Additional simulations show that the precessional effects are also important in the future : 1 and 3 : 1 resonances, since the jump in inclination or eccentricity can be anticipated or delayed. Acknowledgments he authors thank FAPESP, CNPQ, and FUNDUNESP.

10 Mathematical Problems in Engineering References 1 H. B. Hammel, K. H. Baines, J. D. Cuzzi, et al., Exploration of the Netpune system, in he Future of Solar System Exploration, 003 013: Community Contributions to the NRC Solar System Exploration Decadal Survey, M. V. Sykes, Ed., vol. 7 of ASP Conference Series, pp. 97 33, 00. P. Goldreich, N. Murray, P. Y. Longaretti, and D. Banfield, Neptune s story, Science, vol. 45, pp. 500 504, 1989. 3 W. M. Owen Jr., R. M. Vaughan, and S. P. Synnott, Orbits of the six new satellites of Neptune, Astronomical Journal, vol. 101, no. 4, pp. 1511 1515, 1991. 4 E. K. Woolard, Astronomical Papers of American Ephemeris, vol. 15, part 1, 1953. 5 R. Kurth, Introduction to the Mechanics of the Solar System, Pergamon Press, London, UK, 1959. 6 D. Lazzaro, Semi-Analytical heory for the Motion of Neptune s Satellites, Doctor thesis, Universidade de São Paulo, São Paulo, Brazil, 1987. 7. Yokoyama, C. Nascimento, and M.. Santos, Inner satellites of Neptune I: the mutual disturbing function, Advances in Space Research, vol. 36, pp. 569 577, 005. 8. Yokoyama, Possible effects of secular resonances in Phobos and riton, Planetary and Space Science, vol. 50, no. 1, pp. 63 77, 00.