Research Article  Open Access
Martin Lara, Jesús F. Palacián, "Hill Problem Analytical Theory to the Order Four: Application to the Computation of Frozen Orbits around Planetary Satellites", Mathematical Problems in Engineering, vol. 2009, Article ID 753653, 18 pages, 2009. https://doi.org/10.1155/2009/753653
Hill Problem Analytical Theory to the Order Four: Application to the Computation of Frozen Orbits around Planetary Satellites
Abstract
Frozen orbits of the Hill problem are determined in the doubleaveraged problem, where short and longperiod terms are removed by means of Lie transforms. Due to the perturbation method we use, the initial conditions of corresponding quasiperiodic solutions in the nonaveraged problem are computed straightforwardly. Moreover, the method provides the explicit equations of the transformation that connects the averaged and nonaveraged models. A fourthorder analytical theory is necessary for the accurate computation of quasiperiodic frozen orbits.
1. Introduction
Besides its original application to the motion of the Moon [1], the Hill problem provides a good approximation to the real dynamics of a variety of systems, encompassing the motion of comets, natural and artificial satellites, distant moons of asteroids, or dynamical astronomy applications [2–4]. Specifically, the Hill model and its variations [5–9] are useful for describing the motion about planetary satellites. In addition, the Hill problem is an invariant model that does not depend on any parameter, thus, giving broad generality to the results, whose application to different systems becomes a simple matter of scaling. Note that Hill's case of orbits close to the smaller primary is a simplification of the restricted threebody problem, which in turn is a simplification of real models.
A classical result shows that low eccentricity orbits around a primary body are unstable for moderate and high inclinations due to thirdbody perturbations [10]. Almost circular orbits close to the central body remain with low eccentricity in the longterm only when the mutual inclination with the perturbing body is less than the critical inclination of the thirdbody perturbations (see [11] and references therein). Because of their low eccentricity, high inclination orbits are precisely the candidate orbits for science missions around natural satellites. Therefore, a good understanding of the unstable dynamics of the Hill problem is required.
The study of the longterm dynamics is usually done in the doubleaveraged problem. After removing the short and longperiod terms, and truncating higherorder terms, the problem is reduced to one degree of freedom in the eccentricity and the argument of the periapsis. As the doubleaveraged problem is integrable and the corresponding phase space is a compact manifold, the solutions are closed curves and equilibria. The latter are orbits that, on average, have almost constant eccentricity and fixed argument of the periapsis, and are known as frozen orbits.
To each trajectory of the doubleaveraged problem it corresponds a torus of quasiperiodic solutions in the nonaveraged problem. The accurate computation of initial conditions on the torus requires the recovery of the short and longperiod effects that were eliminated in the averaging. This is normally done by trial and error, making iterative corrections on the orbital elements, although other procedures can be applied [12].
Our analytical theory is computed with Deprit's perturbation technique [13]. The procedure is systematic and has the advantage of providing the explicit transformation equations that connect the averaged analysis with proper initial conditions of the nonaveraged problem. A secondorder truncation of the Hamiltonian shows that there are no degenerate equilibria and, therefore, it is sufficient to give the qualitative description of the reduced system. However, the secondorder truncation introduces a symmetry between the direct and retrograde orbits that is not part of the original problem, and a thirdorder truncation is required to reveal the nonsymmetries of the problem.
While, in general, the thirdorder theory provides good results in the computation of quasiperiodic, frozen orbits, its solutions are slightly affected by longperiod oscillations. This fact may adversely affect the longterm evolution of the frozen orbits and it becomes apparent in the computation of science orbits about planetary satellites, a case in which small perturbations are enough for the unstable dynamics to defrost the argument of the periapsis. Then, the orbit immediately migrates along the unstable manifold with an exponential increase in the eccentricity.
We find that a higherorder truncation is desirable if one wants to use the analytical theory for computing accurate initial conditions of frozen orbits. The computation of the fourthorder truncation removes almost all adverse effects from the quasiperiodic solutions, and shows a high degree of agreement between the averaged and nonaveraged models even in the case of unstable orbits.
Whereas the thirdbody perturbation is the most important effect in destabilizing science orbits around planetary satellites, the impact of the nonsphericity of the central body may be taken into account. The previous research including both effects has been limited up to thirdorder theories (see [14] and references therein), but from the conclusions of this paper it may worth to develop a higherorder theory including the inhomogeneities of the satellite's gravitational potential.
2. DoubleAveraged Hill Problem to the FourthOrder
The equations of motion of the Hill problem are derived from the Hamiltonian
where, in the standard coordinate system of Hill's model, is the position vector, is the vector of conjugate momenta, , and both the rotation rate of the system and the gravitational parameter of the primary are set to 1 in appropriate units.
The problem is of three degrees of freedom, yet admitting the Jacobi constant . Despite its nonintegrability, approximate solutions that explain the longterm dynamics can be found by perturbation methods. Close to the central body the Hill problem can be written as the perturbed twobody problem
where the first three terms of Hamiltonian (2.2) correspond to the Keplerian motion in the rotating frame and is a formal parameter introduced to manifest the importance of each effect. Thus, the Coriolis term is a first order effect and the thirdbody perturbation appears at the secondorder .
To apply perturbation theory, we formulate the problem in Delaunay variables , where is the mean anomaly, is the argument of the periapsis, the argument of the node in the rotating frame, is the Delaunay action, is the modulus of the angular momentum vector, is its polar component, and are usual orbital elements: semimajor axis, eccentricity, and inclination.
Our theory is based on the use of Lie transforms as described by Deprit [13, 15]. It has the advantage of connecting the averaged and original problems through explicit transformation equations. After removing the short and longperiod terms we get the transformed Hamiltonian
where ,
and , is the eccentricity function, and we use the abbreviations ,. Details on the perturbation method and expressions to compute the transformation equations of the averaging are given in the appendix.
The doubleaveraged Hamiltonian (2.3) depends neither on the mean anomaly nor on the argument of the node. Therefore, the corresponding conjugate momenta, and , are integrals of the reduced problem and the Hamiltonian (2.3) represents a one degree of freedom problem in and . The equations of motion are computed from Hamilton equations ,,
Once and are integrated for given initial conditions, the secular variations of and are computed from simple quadratures derived from Hamilton equations ,
3. Qualitative Dynamics
The flow can be integrated from the differential equations mentioned previously, (2.5). However, since the system defined by (2.5) is integrable, the flow is made of closed curves and equilibria, and it can be represented by contour plots of Hamiltonian (2.3). Thus, for given values of the dynamical parameters and —or and —we can plot the flow in different maps that are function of , . Figure 1 shows an example in semiequinoctial elements , where we note a hyperbolic point corresponding to an unstable circular orbit, and two elliptic points corresponding to two stable elliptic orbits with and periapsis at respectively.
Delaunay variables are singular for zero eccentricity orbits, where the argument of the periapsis and the mean anomaly are not defined, and for equatorial orbits, where the argument of the node is not defined. Hence, it is common to study the reduced phase space in the variables introduced by Coffey et al. [16], see also [8]:
that define the surface of a sphere
of radius (the sphere representation misses the case , irrelevant in astrodynamics.)
Then, after dropping constant terms and scaling, Hamiltonian (2.3) writes
The flow on the sphere is obtained from Liouville equations , , where the dot means derivative in the new time scale. Then,
with the constraint , derived from (3.2).
Equations (3.4)–(3.6) show that circular orbits (, , the “north” pole of the sphere) are always equilibria. Equations (3.5) and (3.6) vanish when ,, but (3.4) vanishes only when
Equation (3.7) is a polynomial equation of degree 8 in , therefore admitting eight roots. Note that, for the accepted values of , (3.7) is of the form that admits a maximum of three real roots, according to Descartes' rule of signs.
The real roots of (3.7) verified by the dynamical constraint are also equilibria. The root marks a change in the number of equilibria due to a “bifurcation” ( could be a root but not an equilibrium). Then, the number of equilibria changes when crossing the line
obtained setting in (3.7) that establishes a relation between the dynamical parameters and corresponding to bifurcations of circular orbits. Figure 2 shows that this line defines two regions in the parameters plane with different number of equilibria in phase space. Circular orbits in the outside region of the curve are stable. When crossing the line given by (3.8) the number of real roots of (3.7) with dynamical sense increases such that a pitchfork bifurcation takes place: circular orbits change to unstable and two stable elliptic orbits appear with periapsis, respectively at , as in the example of Figure 1.
Note that the curve given by (3.8) notably modifies the classical inclination limit for circular orbits' stability. However, we cannot extend the practical application of the analytical theory to any value of . It is common to limit the validity of the Hill problem approximation to one third of the Hill radius . Then , including most of the planetary satellites of interest. Figure 3 shows the bifurcation lines of circular orbits in the validity region of the parameters plane with the values of corresponding to low altitude orbits around different planetary satellites highlighted.
A powerful test for estimating the quality of the analytical theory is to check the degree of agreement of the bifurcation lines of the analytical theory with those computed numerically in the nonaveraged problem. To do that we compute several families of threedimensional, almost circular, periodic orbits of the Hill (nonaveraged) problem that bifurcate from the family of planar retrograde orbits at different resonances. For variations of the Jacobi constant the almost circular periodic orbits evolve from retrograde to direct orbits through the 180 degrees of inclination. At certain critical points, almost circular orbits change from stable to unstable in a bifurcation phenomenon in which two new elliptic periodic orbits appear. The computation of a variety of these critical points helps in determining stability regions for almost circular orbits [17].
The tests done show that the fourthorder theory gives good results for . As presented in Figure 4, the bifurcation line of retrograde orbits clearly diverges from the line of corresponding critical periodic orbits for higher values of , and it may be worth developing a higherorder theory that encompasses also the case of Enceladus.
(a)
(b)
4. Frozen Orbits Computation
Hill's case of orbits close to the smaller primary is a simplification of the restricted threebody problem, which in turn is a simplification of real models. Therefore, the final goal of our theory is not the generation of ephemerides but to help in mission designing for artificial satellites about planetary satellites, where frozen orbits are of major interest.
For given values of the parameters, , determined by the mission, a number of frozen orbits may exist. A circular frozen orbit, either stable or unstable, exists always and the computation of real roots of (3.7), if any, will provide the eccentricities of the stable elliptic solutions with frozen periapsis at . To each equilibrium of the doubly reduced phase space it corresponds a torus of quasiperiodic solutions in the original, nonaveraged model. In what follows we present several examples that justify the effort in computing a fourthorder theory to reach the quasiperiodicity condition in the Hill problem.
4.1. Elliptic Frozen Orbits
We choose ,. If we first try the classical doubleaveraged solution, the Hamiltonian (2.3) is simplified to , and the existence of elliptic frozen orbits reduces to the case , . The eccentricity of the elliptic frozen solutions is then computed from —obtained by neglecting terms in in (3.7). Thus, for the given values of and , and taking into account that we are free to choose the initial values of the averaged angles , , we get the orbital elements of the first row of Table 1. The left column of Figure 5 shows the longterm evolution of the instantaneous orbital elements for this case, that we call “classical averaging,” in which we find longperiod oscillations of more than four degrees in inclination, more than fifteen in the argument of periapsis, and a variation of in the eccentricity.

(a)
(b)
When computing a secondorder theory with the LieDeprit perturbation method we arrive exactly at the classical Hamiltonian obtained by a simple removal of the shortperiod terms and the classical bifurcation condition that results in the critical inclination of the thirdbody perturbations [10, 11]. However, now we have available the transformation equations to recover the short and longperiod effects, although up to the first order only. After undoing the transformation equations we find the orbital elements of the second row of Table 1, where we see that all the elements remain unchanged except for the eccentricity and inclination. The longterm evolution of these elements is presented in the right column of Figure 5, in which we notice a significant reduction in the amplitude of longperiod oscillations: in inclination, around in the argument of the periapsis, and in eccentricity.
The results of the third and fourthorder theories are presented in the last two rows of Table 1 and in Figure 6. The higherorder corrections drive slight enlargements in the semimajor axis. While both higherorder theories produce impressive improvements, we note a residual longperiod oscillation in the elements computed from the thirdorder theory (left column of Figure 6). On the contrary, the orbital elements of the frozen orbit computed with the fourthorder theory are almost free from longperiod oscillations and mainly show the shortperiod oscillations typical of quasiperiodic orbits.
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(b)
4.2. Circular Frozen Orbits
If we choose the same value for but now , frozen elliptic orbits do not exist any longer and the circular frozen orbit is stable. Both the third and fourthorder theories provide good results, but, again, the thirdorder theory provides small longperiod oscillations in the eccentricity whereas the fourthorder theory leads to a quasiperiodic orbit (see Figure 7).
(a)
(b)
(c)
(d)
For and the circular frozen orbit is unstable. Due to the instability, a longterm propagation of the initial conditions from either the third or the fourth theory shows that the orbit escapes following the unstable manifold with exponential increase in the eccentricity. But, as Figure 8 shows, the orbit remains frozen much more time when using the fourthorder theory. A variety of tests performed on science orbits close to Galilean moons Europa and Callisto showed that the fourthorder theory generally improves by 50% the lifetimes reached when using the thirdorder theory.
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4.3. Fourier Analysis
Alternatively to the temporal analysis mentioned previously, a frequency analysis using the Fast Fourier Transform (FFT) shows how initial conditions obtained from different orders of the analytical theory can be affected of undesired frequencies that defrost the orbital elements.
Thus, Figure 9 shows the FFT analysis of the instantaneous argument of the periapsis of the elliptic orbit in the example mentioned previously. Dots correspond to initial conditions obtained from the doubleaveraged phase space after a classical analysis—that is equivalent to the secondorder analytical theory—and the line corresponds to initial conditions obtained from the fourthorder analytical theory after undoing the transformation. While most of the frequencies match with similar amplitudes, in the magnification of the right plot we clearly appreciate a very low frequency of 0.15 cycles/year with a very high amplitude in the classical theory that is almost canceled out with the fourthorder approach. The semiannual frequency remains in both theories because it is intrinsic to the problem. It is due to the thirdbody perturbation and it cannot be avoided.
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Figure 10 shows a similar analysis for the instantaneous eccentricity of the stable circular orbit mentioned previously. Now, dots correspond to the fourthorder theory and the line to the thirdorder one (both after undoing the transformation equations). While the thirdorder theory provides good results, reducing the amplitude of the undesired frequency to low values, the fourthorder theory practically cancels out that frequency.
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An FFT analysis of unstable circular orbits has not much sense because of the time scale in which the orbit destabilizes.
5. Conclusions
Frozen orbits computation is a useful procedure in mission designing for artificial satellites. After locating the frozen orbit of interest in a doubleaveraged problem, usual procedures for computing initial conditions of frozen orbits resort to trialanderror interactive corrections, or require involved computations. However, the explicit transformation equations between averaged and nonaveraged models can be obtained with analytical theories based on the LieDeprit perturbation method, which makes the frozen orbits computations straightforward.
Accurate computations of the initial conditions of frozen, quasiperiodic orbits can be reached with higherorder analytical theories. This way of proceeding should not be undervalued in the computation of science orbits around planetary satellites, a case in which thirdbody perturbations induce unstable dynamics.
Higherorder analytical theories are a common tool for computing ephemeris among the celestial mechanics community. They are usually developed with specific purpose, sophisticated algebraic manipulators. However, the impressive performances of modern computers and software allow us to build our analytical theory with commercial, generalpurpose manipulators, a fact that may challenge aerospace engineers to use the safe, wellknown techniques advocated in this paper.
Appendix
Let , where are coordinates and their conjugate momenta, be a Lie transform from “new” (primes) to “old” variables. If is its generating function expanded as a power series in a small parameter , a function can be expressed in the new variables as the power series whose coefficients are computed from the recurrence
where , is the Poisson bracket. Conversely, the coefficients of the generating function can be computed step by step from (A.1) once corresponding terms of the transformed function are chosen as desired. In perturbation theory it is common to chose the as an averaged expression over some variable, but it is not the unique possibility [18]. Full details can be found in the literature [19, 20].
To average the shortperiod effects we write Hamiltonian (2.2) in Delaunay variables as
where , , , and . Note that the true anomaly is an implicit function of .
Since the radius never appears in denominators, it results convenient to express Hamiltonian (A.2) as a function of the elliptic—instead of the true—anomaly by using the ellipse relations , , .
After applying the Delaunay normalization [21] up to the fourthorder in the Hamiltonian, we get
where, omitting primes,
The generating function of the transformation is , where
We shorten notation calling .
The Lie transform of generating function can be applied to any function of Delaunay variables Since , up to the thirdorder in the small parameter recurrence (A.1) gives
Specifically, this applies to the transformation equations of the Delaunay variables themselves, where and for .
A new application of the recurrence (A.1) to the Hamiltonian , where of (A.3), allows to eliminate the node up to the fourthorder, obtaining the doubleaveraged Hamiltonian (2.3). Note that corrects previous results in [22]. The generating function of the transformation is , where, omitting double primes,
The new Lie transform of generating function can be applied to any function of Delaunay variables, and, specifically, to the Delaunay variables themselves. For any the transformation equations of the Lie transform are computed, up to the thirdorder, from
where
Acknowledgments
This work was supported from Projects ESP 200764068 (the first author) and MTM 200803818 (the second author) of the Ministry of Science and Innovation of Spain is acknowledged. Part of this work has been presented at 20th International Symposium on Space Flight Dynamics, Annapolis, Maryland, USA, September, 24–28 2007.
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Copyright
Copyright © 2009 Martin Lara and Jesús F. Palacián. This 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.