Issue 
A&A
Volume 540, April 2012



Article Number  A21  
Number of page(s)  25  
Section  Celestial mechanics and astrometry  
DOI  https://doi.org/10.1051/00046361/201118564  
Published online  19 March 2012 
Specific effects of large asteroids on the orbits of terrestrial planets and the ASETEP database^{⋆}
Observatoire de Paris, SYRTE/CNRS UMR8630, 61 avenue de l’Observatoire, 75014 Paris, France
email: safwan.aljbaae@obspm.fr; jean.souchay@obspm.fr
Received: 2 December 2011
Accepted: 16 January 2012
The necessity to take into account the perturbations caused by a large number of asteroids on the terrestrial planets is fundamental in the construction of modern numerical ephemeris on the solar system. Therefore about 300 of the largest asteroids were taken into account in recent ephemeris. Yet, the uncertainty on the mass values of the great majority of these asteroids constitutes a crucial and the main limit of accuracy of this ephemeris. Consequently, it is important to conduct a specific and detailed study of their individual effects especially on the terrestrial planets, which are far more affected than the giant planets. This was already done explicitly, but only for Mars and for only two orbital elements (a and λ). We aim both to confirm these previous results and to extend the study to all orbital elements and to the other three terrestrial planets (Mercury, Venus and the Earth), which are priori less affected by asteroid perturbations. Our methodology consists in several steps: we carried out precise computations of the orbital motions of the planets at short (100 y) and longer (1000 y) time scales with numerical integration. For that purpose we included the eight planets and also considered 43 of the most powerful asteroids. These were added to the numerical integrations once separately and once combined to determine their specific effects on the orbital elements of the Earth and the three other terrestrial planets. This procedure also allowed us to assess the spatial geocentric coordinates of the three terrestrial planets. We determined the signal that represents the effects by simple subtraction. Then we systematically analyzed this signal by FFT (fast Fourier transform), and finally we adjusted the signal with a set of sinusoidal components. We analyzed in detail the variations of the six orbital elements a, e, i, Ω, and λ of Mercury, Venus, the EarthMoon barycenter (EMB) and Mars that are caused by the individual influences of the set of our 43 selected asteroids. We compared our results for Mars with the analytical ones on the semimajor axis and the longitude. The tow studies agree very well. All our results, consisting of 1032 different curves (43 asteroids × 4 planets × 6 orbital elements) and the related tables that provide the fitted Fourier and Poisson components are gathered the ASETEP database (asteroid effect on the terrestrial planets). Moreover, we include in this database the influence of our sample of 43 asteroids on three fundamental parameters: the distance and the bidimensional orientation vector (α, δ) from the EMB to each of the other terrestrial planets. This database, which will be regularly updated by taking into account more asteroids with improved mass determinations, constitutes a precious tool for understanding specifically the influence of the large asteroids on the orbital motion of the terrestrial planets, and also for better understanding how modern ephemeris can be improved.
Key words: gravitation / minor planets, asteroids: general / ephemerides / astronomical databases: miscellaneous / astrometry / celestial mechanics
Appendices A–C are available in electronic form at http://www.aanda.org
© ESO, 2012
1. Introduction
There are two main ways of computing the ephemeris of celestial bodies. One is semianalytical, which was used for the VSOP87 theory of the planets by Bretagnon et al. (1987) and the ELP2000 solution for the orbital motion of the Moon (Chapront et al. 1988). In these successful and complex works, the coordinates of the moving bodies are given in the form of Fourier series of fundamental arguments as the mean longitudes of the planets or the Delaunay arguments. The interest of these analytical theories is that they enable us to understand the origin of the countless sinusoidal terms that originate in the perturbing function. But these theories can no longer reach the necessary accuracy to match numerical determinations of the motions that constitute the second way of computation.
Indeed, today the stability and rapidity of the numerical integrators allow an accurate construction of the ephemeris of the solar system’s main bodies. As explained by Standish (2004), the accuracy of an ephemeris depends on three major factors. The first one is related to the equations of motion. These equations might be imperfect for instance because they do not take all the gravitational effects into account or because the underlying analytical model contains some errors. The second factor concerns the integration of motion, which inevitably contains uncertainties that have to be estimated. The last factor is the exact determination of basic parameters such as the initial conditions (positions, velocities, masses etc.), which are given by the observations, and therefore contain errors that are conditioning the results of the integration. The two first factors are generally believed to be satisfactory, because the equations of motion look correct and complete, whereas the errors accompanying the integration algorithms have been proved to be negligible. The third factor is still subject to various investigations and numerous recent developments, in particular those coming from the recent missions to Mars (Standish 2004; Fienga et al. 2009). The JPL ephemeris are undoubtedly used the most worldwide. Since the construction of an initial release DE200 in 1979, a lot of other versions have been constructed, such as DE405 in 1997, and DE409 in 2003. This last version in particular uses very recent VLBI observations of the MGS (Mars Global Surveyor) in 2001–2003 and Odyssey in 2002–2003, which leads to an accuracy for the determination of the position of Mars at the level of a few milliarcseconds. The comparisons between the various versions of JPL ephemerides give a clear insight into the improvements. DE405 for instance, showed an improvement of an order of magnitude over DE200, especially for the inner planets, as explained by Standish (2004).
To evaluate the accuracy limits in the ephemeris of the four inner planets, Standish et al. (2002) considered the presentday knowledge of the asteroid masses determined by various methods, and modeled the distributions of those masses. Then they carried out a MonteCarlo study, repeatedly adjusting the ephemeris to fit the observational data, by a suitable set of asteroid masses. the authors’ conclusion is that by combining accumulated data for more than two decades, the orbits become distorted both in right ascension and in declination by as much as 5 km or more. At the level of presenttime ephemerides accuracy, the influence of asteroids can no longes be neglected, as in the case of DE409. Many asteroids have enough mass to produce a significant gravitational effect on the inner planets. Nevertheless, because of the large uncertainty in the determination of asteroid masses, it is difficult or impossible to evaluate their effect with sufficient accuracy. Yet no specific study of the influence of each asteroid has been conducted to date. A pioneering work was carried out by Williams (1984), giving a list of the most influential asteroids on the orbit of Mars over a short period of time, roughly 50 years. Recently, Mouret et al. (2009) identified and provided a list of the main perturbers of Mars, which could cause significant disturbances over the next 50 years as well. Their analytical analysis is based on a harmonic decomposition of the perturbations on Mars as a function of the mean longitudes of the planet and the asteroid, to the first order in asteroid mass. Still, these two last studies (Williams 1984; Mouret et al. 2009) can be considered as incomplete because they concentrate mainly on two orbital elements, the semimajor axis and longitude of Mars. Moreover, they only focus on this planet.
We aim to carry out an extensive study of the subject in the present paper. In Sect. 2, after determining the asteroidal mass and its accuracy, we select a set of 43 asteroids. We explain in detail in Sect. 3 the theoretical framework and our methodology with which we calculated the perturbing effect of any specific asteroid on a terrestrial planet. In Sect. 4, we determine the effects of our 43 selected asteroids on the six Mars orbital elements, while the effects on the other telluric planets, the Earth (replaced in the following by the EMB (EarthMoon barycenter), Mercury and Venus are presented in Sect. 5. Thus we reconstruct the asteroidal perturbation as a combination of Fourier and Poisson components for each perturbing asteroid as well as each terrestrial planet and each orbital parameter. Moreover, as an important byproduct of these computations, we calculate in Sect. 6 the influences of each asteroid on two fundamental astrometric parameters namely the distance from the EMB to the barycenter of the other terrestrial planets (Mercury, Venus and Mars) and their twodimensional positioning (α,δ) in the celestial sphere. Finally we describe in Sect. 7 how we constructed our ASETEP (asteroidal effects on the terrestrial planets) database, which enables one to determine the influence of each asteroid on any of the four terrestrial planets precisely and in detail through their orbital elements and their geocentric positioning.
2. Mass determinations of the asteroids
Much information about the size, shape and pole direction of the leading asteroids has been obtained from analyses of light curves at different epochs, occultation, and/or images obtained through adaptive optics and speckle techniques. The mass is one of the important characteristics, necessary for describing the perturbations on other bodies. There are two methods of estimating the mass: one is dynamical, the other is astrophysical.
The dynamical method is based on the analysis of perturbations of the studied asteroid on other celestial bodies. After a pioneering work by Williams (1984), studying how asteroid masses can be determined from their perturbations on Mars, Standish et al. (1989) showed that the measurements of Mars orbit perturbations can be conducted to estimate the masses of Ceres, Pallas and Vesta, with the intermediary of a leastsquares adjustment of all ephemeris parameters, including the relevant asteroid masses. This adjustment was compiled on the basis of observational data encompassing the highly accurate Viking Lander ranging data. The accuracy of mass determination through this method highly depends on the precision of positional observations used and on the number of the observations and their distribution.
The astrophysical method is based on the data about the asteroid size and the taxonomic classification. This method assumes that the body has a spherical shape, a homogeneous structure, is single, etc. This method, in contrast to the dynamical one, has the advantage that it can be applied to many objects even if there is no close encounter with other bodies (Kochetova 2004), but is generally marred by a large uncertainty.
2.1. The mass of Ceres, Pallas and Vesta
The masses of the three largest asteroids, Ceres, Pallas and Vesta obtained by Standish et al. (1989) starting from the perturbations on Mars orbital motion were (5.0 ± 0.2) × 10^{10} M_{S}, (1.4 ± 0.2) × 10^{10} M_{S} and (1.5 ± 0.3) × 10^{10} M_{S} respectively. They were updated by more recent studies, as we will show below. Hilton (1999) explained why the mass determination of Ceres is completely dependent on that of Pallas. The reason is the degeneracy between the two masses, which is in turn caused by the similarity of the semimajor axes of the two asteroids. In consequence, their mean motion is nearly the same, and their mutual synodic period is very long, around 2000 yr (Williams 1989). This amplifies the propagation of the errors on the mass of Pallas to the mass of Ceres, when the mass of the first asteroid is obtained starting from a series of close encounters with the second one. This explains why the mass estimations are highly dependent on old data with poor accuracy. Because of the high Pallas inclination and its high eccentricity, its close encounters with mainbelt asteroids occur only rarly, and when they occur, the relative velocity is high so that mass determination is not very efficient. For Vesta, the mass was obtained starting from perturbations of both Ceres and 197 Arete. The values obtained by Hilton (1999) were M_{Ceres} = 4.39(±0.04) × 10^{10} M_{S}, M_{Pallas} = 1.59(±0.05) × 10^{10} M_{S} and M_{Vesta} = 1.69(±0.11)) × 10^{10} M_{S}. Many new constraints for the masses of the three asteroids were obtained during one decade. For our computations, we have chosen the recent values determined by Pitjeva et al. (2009) from data of the Martian landers and spacecraft by fitting the planet ephemeris to observations. Their values are significantly different from the estimations above, i.e. 4.712(±0.006) × 10^{10} M_{S} for Ceres, 1.027(±0.007) × 10^{10} M_{S} for Pallas, and 1.344(±0.003) × 10^{10} M_{S} for Vesta.
2.2. The mass of the other large asteroids
We limit our study to the perturbations produced by asteroids with relatively large and wellconstrained masses. According to Mouret et al. (2009), we can rely on 36 asteroid masses derived from direct measurements with a precision better than 10 per cent, while only 54 reach the 50 per cent mark. These statistics come from Mouret et al. (2007), Baer et al. (2008a) and Baer database^{1}. All these masses were deduced from the gravitational pull exerted by the corresponding asteroid on other solar system objects, mainly smaller asteroids, and in special cases Mars or a spacecraft. In Table 1 we present the set of the 43 asteroids selected in this paper for which we will calculate the gravitational effects on the four terrestrial planets in the following, together with their mass determination and the relative uncertainty. Our choice was guided by two criteria: the asteroid must be big enough and its mass determination satisfactorily accurate. The data were taken from 12 different sources: Pitjeva et al. (2009), Fienga et al. (2009), Baer et al. (2008a), Baer et al. (2008b), Bange (1998), Marchis et al. (2008a), Marchis et al. (2008b), Kochetova (2004), Ivantsov (2008), Aslan et al. (2007), and Yeomans et al. (1997). Notice that in the near future, Gaia may significantly increase the number of favorable encounters to be analyzed for mass determination, as explained by Mouret et al. (2009).
3. Analytical expression of planet perturbations caused by an asteroid
After reviewing the classical theory of perturbations for a system of N planets orbiting the Sun, we show in this section how the individual effects of a given asteroid on one of these planets are determined analytically and explain our methodology of characterizing these effects with numerical integration.
3.1. Theoretical principles
Consider N planets P_{1},....,P_{N} orbiting around the Sun P_{0}, with mass m_{0}, according to Newton’s law. The heliocentric position vector r_{i} of a given planet in the frame of this N + 1 body problem is subject to the second order differential equation: (1)where i = 1,2,...,N and the parameters m_{i} and G are the mass of the ith. planet and the gravitational constant. R_{i}, usually called the disturbing function on the planet P_{i}, is written as follows: (2)This disturbing function causes a perturbation of the planet’s osculating orbital elements; in principle each of these perturbations can be calculated analytically according to the classical Lagrange equations for the osculating elements a,e,i,Ω,ϖ and λ (see for instance Murray & Dermott 1999) (for simplicity we did not take into account the index i in R_{i}) (3)We focus on the perturbation caused on a planet P (one of the P_{i}) by an asteroid P′ of mass m′ added to the N + 1 body system considered above. Let the position vector of the new body be denoted by r′. Generally we define the perturbation ΔX of one orbital element X of the planet induced by the asteroid as the difference , where stands for the perturbed element in the frame of the N + 2 body problem (with the asteroid) and X for perturbed element in the frame of the N + 1 body problem (without the asteroid). On an equivalent manner, the perturbing function ΔR can be written as (4)We can write the derivative of the perturbation induced by the extra body P′ on the elements of the planet in the following form (Kochetova 2010): (5)The development of the perturbing function as a function of eccentricities and inclinations enables one to obtain the expressions of the perturbations as a function of the orbital elements both of the perturbed body (here the planet) and the perturbing body (the studied asteroid). This development was continued up to the fourth order by Brouwer & Clemence (1961). To develop the disturbing function ΔR given in Eq. (4), we distinguished between its direct part R_{D} and its indirect part R_{E}. According to classical celestial mechanics (see for instance Laskar et al. 1995; or Murray & Dermott 1999) we have: (6)With , where a′ stands for the semimajor axis of the asteroid, and: (7)(8)where e′, λ′, ϖ′, Ω′ stand for the orbital elements of the asteroid. ψ is the angle between the position vectors r and r′, . The coefficients depend on the Laplace coefficients
The developments in (7) and (8) show that after integration of the variational Eqs. (5) we can expect that the variations of orbital elements be expressed as a series of linear combinations of λ and λ′, taking into account that the parameters , , and have a very low frequency with respect both to λ and λ′. Therefore, they can be considered as nearly constant during the interval of time considered (100 y or 1000 y). This explains why both Williams (1984) and Mouret et al. (2009) constructed their developments of a_{Mars} and λ_{Mars} only with the help of sinusoidal terms with high frequency, function of the arguments of the form jλ + j′λ′. Nevertheless this study is incomplete, because it does not take into account two longperiodic terms that can come from two different origins: first the resonant terms in (7) and (8) with very low frequency; and second the long periodic terms in the disturbing function with arguments as a linear combination of the sole , , and not shown in (7) and (8).
Mass estimation of the 43 asteroids selected in this paper, with their relative uncertainty.
The planetary orbital perturbations due to the asteroids were also discussed by Williams (1984) and Simon (1987), focusing exclusively on the planet Mars. Simon (1987) describes the analytical construction of programs to calculate the first and second derivatives of the Lagrange equations, and to express the theoretical perturbations due to an asteroid on the six ecliptical elements of a planet Δσ_{k}, where the variables σ_{k = 1,...,6} are: a, λ, the mean longitude (written as λ = λ_{0} + nt, n being the mean motion), k = ecosϖ, h = esinϖ, , . The method is based on a harmonic decomposition with respect to the mean longitudes of the planet and the asteroid . Finally the perturbations can be written as (9)as an extension of this work, Mouret et al. (2009) presented in a detailed manner the application of this decomposition for each perturbation of some selected asteroids on the Mars semimajor axis and longitude which were also the only two orbital elements studied by Williams (1984).
3.2. Methodology of studying asteroidal effects
For the studies mentioned above, the corresponding analytical developments of the perturbing function ΔR expressed in (6)–(8) from the orbital elements of the two bodies considered (the planet and the perturbing asteroid) are particularly cumbersome and complex, all the more so if we aim to include very longperiodic components, which are difficult to determine analytically, and could be treated as polynomial expansions. But it is possible to evaluate the perturbations in a straightforward manner from numerical integration. Therefore we computed the classical ninebody problem (the Sun and the eight planets), and then carried out the same integration with the sole addition of the perturbing asteroid (Ceres, Pallas, etc.). A simple substraction of the two corresponding signals of one orbital parameter of the planet gives a clear and direct determination of the effect of the asteroid on this parameter.
As mentioned above, the objective of this work is to try to assess the specific influence of ecah of the 43 big selected asteroids on the motion of the terrestrial planets. For that goal we focused our efforts in the following complementary steps:

we evaluated and then removed the quadratic variation of the differential signal, to isolate the periodic components;

we performed the frequency analysis of the signal, using fast Fourier transform to determine the leading frequencies;

we carried out a nonlinear regression in which the differential signal is modeled by the leastsquare method following an expression combining Fouriertype and Poissontype components in the form
(10)We evaluated the individual influence of the gravitational action of each asteroid listed in Table 1 on the six orbital elements of each of the four terrestrial planets. Because of the number of asteroids considered (43), of orbital elements (6) and of the terrestrial planets (4), we obtained atotal of 43 × 6 × 4 = 1032 curves, which are gathered together with the related tables of components A_{i}, B_{i}, C_{i}, D_{i} in a database called ASETEP (asteroid effects on the terrestrial planets), as detailed in Sect. 7. In addition, we also calculated and included in this data base the influences of each asteroid on the distance from the EMB to a given terrestrial planet (Mercury, Venus or Mars) and its orientation vector with respect to the EMB. This is of particular interest for the specific study of geocentric observations of the planets.
Because of the very huge number of results above, our purpose in the next section is only to present a few characteristic examples, and some generalizing tables, which aim to understand both the quality of our determinations and the impact of the gravitational effects of each asteroid on the orbital parameters of the terrestrial planets. Although these effects are included in the construction of modern ephemeris of planets, the individual signature of each asteroid is generally not explicitly given, and the effect of mass uncertainty is not fully characterized. One of the interests of our study is to give complete empirical tables of the asteroidal effects on the orbital elements of a given planet, which could be easily readjusted (by simple proportionality) after revision of the asteroial masses. Then we can classify the asteroidal effects by the range of amplitude or/and frequency.
4. Perturbation on the Mars orbital parameters
By using the methodology detailed in the previous section, we computed at first the effects of the asteroids on Mars orbital parameters with the help of a RungeKutta twelfth order integration, with a 0.01day stepsize. The rectangular coordinates obtained with respect to the ecliptic and equinox of J2000.0 are directly converted into orbital parameters with respect to this reference plane and point.
4.1. Perturbation on a_{Mars} and λ_{Mars}
As a basic and typical example of our computations, and to compare them with other authors, such as Mouret et al. (2009), we show in Figs. 1 and 2 the influence of the gravitational action of Ceres on the Mars semimajor axis and longitude. The time interval here is 1000 y starting from 2009 Sept. 26, i.e. between JD 2009.81 and JD 3009.81. For the clarity we plotted the figures for a 100 y time span. According to (10), we fitted the curves as a sum of Fourier (with coefficients A_{i} and B_{i}) and Poisson components (C_{i} and D_{i}).
Fig. 1 Effects of Ceres on a_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (black), fitting curve (red) and residuals (in green). 

Open with DEXTER 
Fig. 2 Effects of Ceres on λ_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER 
In both curves, with peaktopeak amplitudes of 400 m and 0.006′′ for a_{Mars} and λ_{Mars}, respectively, we observe the good quality of the fit resulting from the leastsquaresanalysis: the fitting curve can hardly be distinguished from the original one. The flat curve represents the residuals obtained after subtracting a combination of 27 sinusoids for the semimajor axis from the original signal, and 10 sinusoids for the longitude. These sinusoids are listed in Tables 2 and 3 in the typical ASETEP database format. Notice that similar tables have been generated automatically for the 1032 cases mentioned above.
Coefficients of Fourier and Poisson series for the effects of Ceres on a_{Mars}.
Coefficients of Fourier and Poisson series for the effects of Ceres on λ_{Mars}.
t is given in Julian year: its value is t = 2009.81 at the origin and not t = 0, so that the value of the Poisson coefficients contribution can be quite high all along the interval of time explored. Nevertheless, this high value is fully compensated by the high value of some Fourier components. In other words, to best fit the signal according to (10) requires introducing two contributions that can be very high individually compared with the signal itself but which give the best fit when mixed together. Therefore we should not refer directly to the values of A_{i}, B_{i}, C_{i} and D_{i} to evaluate the amplitude of a component at a given frequency f_{i} in (10) but to the peaktopeak amplitude of F_{i}(t) during the interval of time considered. This peaktopeak amplitude is given in the nexttolast columns of Tables 2 and 3, where each component has been ranged in decreasing order of period. For information and to avoid too many data in the paper, the results of the effects of Ceres on e_{Mars}, i_{Mars}, Ω_{Mars} and ϖ_{Mars} are given in Figs. A.1 to A.4 and Tables A.1 to A.4.
For comparison we also show in Figs. 3 and 4 the effects of Pallas and Vesta on the Mars semimajor axis for the same time interval as in Fig. 1. The peaktopeak amplitudes reach roughly 200 m and 400 m, this last value is roughly the same as for Ceres, but the nature of the three signals is quite different from each other. For the sake of clarity the tables characterizing the adjustment are presented in Tables A.5 and A.6.
Fig. 3 Effects of Pallas on a_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER 
Fig. 4 Effects of Vesta on a_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER 
4.2. Comparison with the analytical results in Mouret et al. (2009)
It is interesting and challenging to compare our numerical results with the analytical ones found by Mouret et al. (2009) when using developments as in (7) and (8). For that purpose it is necessary to choose the same time interval as these authors, that is to say 1000 y, because the developments in series are highly dependent on this time interval. In Tables 4 and 5 we show this comparison for the variation of the Mars semimajor axis and mean longitude due to the gravitational influence of Ceres, Pallas and Vesta. We can notice the remarkable general agreement between our numerical determination of the periods and amplitudes of the sinusoidal components that characterize the signal, and the analytical terms developed by Mouret et al. (2009), whose the arguments are a linear combination of the mean longitudes of Mars and the asteroid.
For the effect of Ceres on a_{Mars} (Table 4) a small but significant discrepancy arises only for the leading term with period 44.33 y and amplitude 57.57 m, which seems to correspond to the component with the period 45.77 y and 60.59 m amplitude in the above paper. This discrepancy probably arises because we used a quadratic regression and removed it from the signal to isolate the periodic parts, which should affect the determination of lowfrequency terms. We also notice components in our calculations that are not mentioned in the paper above, with significant amplitudes 19.56 m, 8.52 m, 5.63 m and 4.78 m and periods 1.12 y, 0.75 y, 76.55 y and 0.56 y. the reason for this could be that analytical developments, even at a low order of masses and eccentricities, are cumbersome with a mixing of many sinusoidal contributions involving the mean longitudes. Therefore some components may be missing.
For the effect of Ceres on λ_{Mars}, the comparison between our results and Mouret et al. (2009) still agrees very well for the majority of components both in amplitudes and periods. Differences similar to those noted for a_{Mars} concern the leading term with period 44.33 y instead of 45.77 y and amplitude 1.77 mas (milliarcsecond).
The agreement is almost perfect for the influences of Pallas and Vesta, if we excludee large amplitudes without counterparts in the analytical developments, such as the component with amplitude 19.02 m and period 1.12 y for a_{Mars} and the secondlargest component with amplitude 0.333 mas and period 59.79 y for λ_{Mars}.
Comparisons of the amplitude of the sinusoids found in this paper with the analytical ones of Mouret et al. (2009) of the effects of Ceres, Pallas and Vesta on a_{Mars}.
Comparisons of the sinusoids found in this paper with those in Mouret et al. (2009) of the effects of Ceres, Pallas and Vesta on λ_{Mars}.
4.3. Perturbations on the other orbital parameters e, i, Ω,
The gravitational effects of Ceres and other leading asteroids on Mars orbital parameters e_{Mars}, i_{Mars}, Ω_{Mars}, have not been explicitly given either by Williams (1984) or by Mouret et al. (2009) although their relative amplitude is of the same order (and sometimes even larger) than the corresponding effects on a_{Mars} and λ_{Mars} described above.
Two important remarks about the curves plotted for Ceres, Pallas and Vesta in Figs. 5 to 8 need to be made. First of all, in contrast to what happens for the semimajor axes (see Fig. 1), long periodic effects that can be characterized by linear or quadratic expressions appear clearly, in particular for i_{Mars} (Fig. 5) and Ω_{Mars} (Fig. 7), for which they dominate the periodic oscillations, even during the short time span considered here (100 y). Second, we can observe that although its mass is considerably smaller than that of Ceres (with a ratio roughly 1/3), the effect of Vesta on the Mars orbital elements can be significantly stronger, as is the case for e_{Mars} (Fig. 6) and (Fig. 8). For the three asteroids considered here, the peaktopeak amplitudes are on the order of 10^{8} for e_{Mars}, 1 mas (milliarcsecond) for i_{Mars}, 005 for Ω_{Mars} and 001 for , in the 100 y time interval considered.
Fig. 5 Effects of Ceres, Pallas and Vesta on i_{Mars}, for a 100 y time interval, starting from JD 2009.81. 

Open with DEXTER 
In Figs. A.1–A.4 we show the effects of Ceres after the quadratic regression is removed. For each of the parameters, leading sinusoidal signatures appear clearly and the same fitting method as previously can be applied. Results of the decomposition are shown in Tables A.1–A.4.
4.4. Amplitude of the perturbations for each parameter and each asteroid
As we already mentioned in Sect. 3.2, we extended our study to the 1032 cases (43 asteroids × 6 planets × 6 orbital elements). The output of our computations is presented in Table 6: we provide the peaktopeak amplitudes of the effects of each of the 43 asteroids listed in Table 1 on each Mars orbital element. This is done for a 1000 y time interval, beginning in 2009. The amplitudes stand for the total signal including secular trends and periodic components. Moreover, to compare the amplitudes of the effects on e_{Mars} to those on a_{Mars} with the same scale, we multiplied these effects by the nominal value a_{0} of the Mars semimajor axis. Thus we can remark that throughout, a_{0} × Δe is significantly higher than Δa with a ratio typically on the order of 2 or 3, but sometimes considerably more, as for Pallas and Vesta. The relatively large amplitude of the effects due to the asteroid 111 Ate compared to those due to these two last asteroid is remarkable. This is because the mass of Ate is comparable to that of these two big objects. For Ceres, during the 1000 y interval of time considered, the peaktopeak amplitudes are 416 m for Δa, 1300 m for a_{0} × Δe, 6.8 mas (millarcsec) for Δi, 0410 for ΔΩ and 0197 for Δλ. These effects of the biggest asteroid are surpassed by those of Vesta for Δa (546.7 m) and a_{0} × Δe (4666 m), by Pallas and 111 Ate for a_{0} × Δe (2025 m and 426 m).
Fig. 6 Effects of Ceres, Pallas and Vesta on e_{Mars}, for a 100 y time interval starting from JD 2009.81. 

Open with DEXTER 
Fig. 7 Effects of Ceres, Palass and Vesta on Ω_{Mars}, for a 100 y time interval, starting from JD 2009.81. 

Open with DEXTER 
Fig. 8 Effects of Ceres, Pallas and Vesta on , for a 100 y time interval, starting from JD 2009.81. 

Open with DEXTER 
Peaktopeak amplitudes of the variations of the six Mars orbital elements for a 1000 y time interval starting from JD 2009.81.
Uncertainty on the values of the six Mars orbital elements, for a 1000 y, because of the lack of accuracy in the measurements of the asteroid mass.
As a direct byproduct of our results, we present in Table 7 the uncertainty of each Mars orbital parameter due to the mass uncertainty of each selected asteroid. Indeed, according to (6), this uncertainty is directly dependent on the asteroid mass, it is sufficient for the purpose to multiply each number of Table 6 by the relative mass uncertainty ΔM/M, whose value has been already given for each object in Table 1. Because of its relatively large mass (17.7% that of Ceres) and its very high mass uncertainty (22.6%), the asteroid 111 Ate is by far the most problematic one, causing uncertainties higher than 93 times that of Ceres for a_{Mars}, 197 times for a_{0}Δe_{Mars}, 44 times for i_{Mars}, 23 times for Ω_{Mars}, 58 times for ϖ_{Mars} and 295 times for λ_{Mars}. Uncertainties on the same order can be observed for 6 Hebe (18.7% mass uncertainty), 7 Iris (8.6%), 9 Metis (23.3%) 19 Fortuna (14.0%), 20 Massalia (16.9%) and 46 Hestia (63%). We think that a table such as Table 7 shows in a very straightforward manner for which asteroid observational campaigns should be launched to minimize errors in the Mars ephemeris.
5. Perturbation on the EMB, Mercury and Venus
In this section we carry out the same kind of study as in the previous section for the terrestrial planets other than Mars. Instead of the Earth isolated, we consider the EMB. This facilitates our calculations noticably. A specific study of the asteroidal effects on the Earth and the Moon taken individually is scheduled for a future paper.
5.1. Effects on EMB
As an example we show in Figs. 9–11 the effects of the gravitational action of Ceres, Pallas and Vesta on the EMB semimajor axis. They are characterized by very stable and regular leading oscillations with peaktopeak amplitudes about 25 m for Ceres, 9 m for Pallas and 15 m for Vesta. The flat curves in each figure represent the residuals after substracting the fit with the help of Fourier and Poisson components. We were able to reconstruct the curve of Ceres with as many as 50 frequencies. The leading components are shown in Table 8. We note that the amplitudes and periods of the leading oscillations are significantly shorter for the EMB than for Mars.
Fig. 9 Effects of Ceres on a_{EMB}, for a 100 y time interval, from JD 2009.81. Residuals (in green) after removing the sinusoidal components from the leastsquares analysis. 

Open with DEXTER 
In Table 9 we present the peaktopeak amplitudes of the effects of each asteroid on the orbital parameters of the EMB for a 1000 y time interval. They are generally, but no systematically smaller than the corresponding effect on Mars. This is because the mass of Mars is much smaller than the mass of our planet (M_{Mars}/M_{Earth} ≈ 0.107) and its orbit is much closer to the asteroid main belt.
5.2. Effects on Mercury and Venus
The effects of the asteroids on the orbital parameters of the two internal planets Mercury and Venus are presented in Tables 10 and 11 also for a 1000 y time span. The peaktopeak amplitudes for a_{Mercury} and a_{Venus} do not exceed 1 m and 10 m, i.e. roughly 400 times and 40 times less than for a_{Mars}. Nevertheless, the ratio is significantly lower for other parameters, also because of the predominance of longterm components, which can be characterized by quadratic or polynomial expressions in the interval of time considered.
Coefficients of Fourier and Poisson series for the effects of Ceres on a_{EMB}.
6. Influences of asteroid on the EMBMars distance and Mars orientation
In view of the groundbased observations of Mars, the fundamental parameters are both the distance d_{Mars} from the Earth geocenter (or the EMB in an alternative case considered here) to the planet geocenter, and the geocentric direction of the planet generally given through the set of its geocentric coordinates (α_{Mars}, δ_{Mars}). Thus the gravitational effect of a given asteroid on these parameters comes directly from the combination of the influences of the asteroid on the orbital elements of the EMB and the planet, which we studied above. As for these influences, the uncertainty of the asteroid masses directly affects the accuracy of the determination of d_{Mars}, α_{Mars} and δ_{Mars}. Moreover, the analytical characterization of the asteroidal effects on these three geocentric parameters is still much more complicated than for the heliocentric orbital parameters, because the determination of the vector from the EMB to planet, even assuming that the two bodies follow a Keplerian trajectory, is a much more complex function that involves Legendre polynomials, than for the heliocentric vector of the planet.
We recall that to facilitate the computations, we replaced the Moon and the Earth by the EMB, i.e. a single point whose mass is the sum of the masses of the two bodies, and which is located at their barycenter. We will calculate in a future paper the differential effects of our asteroids on the Earth to Moon distance, which likely has some interesting implications on lunar laser ranging (LLR) measurements. We calculated the geocentric coordinates of Mars by simply substracting the heliocentric vector of the EMB from that of Mars. The effects of the leading asteroids Ceres, Pallas and Vesta on the EMBMars distance are plotted in Figs. 12–14. In any case the signal is dominated by a single wave with increasing amplitude and a period that slightly varies at each oscillation, which makes the adjusment through a leastsquares analysis uneasy, indeed even inadequate. As expected, the period is clearly close to the synodic period of the planet, which changes slightly at each synodic cycle. The increase of amplitudes with respect to the time are undoubtedly caused by the secular effects of the asteroid on the EMB and Mars orbital parameters, characterized by quadratic trends as studied in Sect. 4.3. These secular effects gradually enhance the effects on the EMBMars vector. The peaktopeak amplitudes of the effects of Ceres, Pallas and Vesta on the EMBtoMars distance are, 34 km, 31 km and 116 km respectively during the 100 y time interval considered.
In Figs. 15 and 16, we present the influence of Ceres on Mars geocentric right ascension and declination. Their peaktopeak amplitudes reach 0.08 and 0.05 arcseconds during the 100 y time interval. The peaks correspond to Mars oppositions, for which the relatively close distance of the planet from the Earth enhances the angular effects of the perturbations. In parallel we can observe the asymmetrical nature of the two curves originating from the fact that the effects are proportional to the distance from the Earth to Mars, which varies roughly from 0.5 to 2.5 AU.
Fig. 10 Effects of Pallas on a_{EMB}, for a 100 y time interval, from JD 2009.81. Residuals (in green) after removing the sinusoidal components from the leastsquares analysis. 

Open with DEXTER 
7. ASETEP database
7.1. Construction of the ASETEP database.
As a result of all our computations, we constucted the ASETEP (asteroid effects on the terrestrial planets) database, which contains at its present extent the curves showing the individual effects of each of the 43 asteroids listed in Table 1 on each of the 6 orbital elements for any of the 4 terrestrial planets (Mercury, Venus, the EMB, Mars) both for a 100 y time interval and a 1000 y time interval from JD 2009,7. In parallel we deliver for each of the curves the corresponding tables giving the Fourier and Poisson components for fitting these curves. This ASETEP database will be subject to regular and continuous updates with an increasing number of new asteroids taken into account, if their mass is determined with a satisfactory accuracy, i.e. better than 65% uncertainty, as for the 43 asteroids listed in Table 1. One of the advantages of the ASETEP database is that the figures and tables already produced for a given asteroid can be updated immediately each time a new and more accurate determination of the mass of this asteroid is reached, by simple proportionnality.
7.2. Individual and combined asteroidal effects
In all computations we considered the effect of each asteroid taken individually, which neglects the effects from the combined gravitational attraction of the asteroids themselves. A priori these effects which result principally from the reciprocal gravitational interactions of the asteroids affecting their positions, are of second order because of the smallness of asteroid masses. They can be neglected at first approximation as long as the interval of time of the study Δt is short, as for Δt = 100 y. To obtain some information about the error caused by neglecting the effects due to the combination of asteroids, we carried out a test with numerical integration: it consists of studying the difference between two numerical computations: first we summed up the individual effects of the 43 asteroids considered here on the Mars orbital parameters, each of which was obtained in the frame of an nbody problem with n = 10 (Sun + 8 planets + asteroid); second we included all asteroids in the frame of an nbody problem with n = 52 (Sun + 8 planets + 43 asteroids).
Fig. 11 Effects of Vesta on a_{EMB}, for a 100 y time interval, from JD 2009.81. Residuals (in green) after removing the sinusoidal components from the leastsquares analysis. 

Open with DEXTER 
Peaktopeak amplitudes of the variations of the six EMB orbital elements due to each given asteroid for a 1000 y time interval starting from JD 2009.81.
Peaktopeak amplitudes of the variations of the six Mercury orbital elements due to each given asteroid for a 1000 y time interval starting from JD 2009.81.
Peaktopeak amplitudes of the variations of the six Venus orbital elements due to the action of each asteroid for a 1000 y time interval starting from JD 2009.81.
Fig. 12 Effects of Ceres on the distance from the EMB to Mars for a 100 y time interval from JD 2009.81. The curve in green corresponds to the postfit residuals. 

Open with DEXTER 
Fig. 13 Effects of Pallas on the distance from the EMB to Mars for a 100 y time interval from JD 2009.81. The curve in green corresponds to the postfit residuals. 

Open with DEXTER 
Fig. 14 Effects of Vesta on the distance from the EMB to Mars for a 100 y time interval from JD 2009.81. The curve in green corresponds to the postfit residuals. 

Open with DEXTER 
Fig. 15 Effects of Ceres on α_{Mars} for a 100 y time interval from JD 2009.81. The curve in green corresponds to the postfit residuals. 

Open with DEXTER 
Fig. 16 Effects of Ceres on δ_{Mars} for a 100 y time interval from JD 2009.81. The curve in green corresponds to a postfit residuals. 

Open with DEXTER 
In Fig. 17, we plot the combined effect of the 43 asteroids taken together on the Mars semimajor axis. The residuals of the two computation methods presented above do not exceed 2.5 m peaktopeak, as can be seen in Fig. 18. This is by two orders less than the signal itself (650 m peaktopeak), and the error caused by treating individual effects separately can be neglected in first approximation. This is still true for the other Mars parameters (see Appendix B), for which the errors are below 1.2 × 10^{11} for e (Figs. B.1 and B.2), 1.8 mas for i (Figs. B.3 and B.4), 10^{2} mas for Ω (Figs. B.5 and B.6), 5 × 10^{3} mas for (Figs. B.7 and B.8).
Fig. 17 Peaktopeak amplitude of the combined effects of the 43 asteroids on a_{Mars}. The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER 
Fig. 18 Zoom of the green curve of Fig. 17, showing the difference between two ways of computation. 

Open with DEXTER 
7.3. Use of ASETEP for ephemerides study
Most of these asteroids have a very large mass uncertainty, sometimes by far exceeding their nominal values, which is why it appears to be illadvised to include them individually in the ephemerides computations. But they can be assigned a reasonable distribution of masses according to some models such as the statistical asteroid model (Tedesco et al. 2005). The problem of mass undetermination of small asteroids was there partly solved by replacing all asteroids except for the 303 most perturbing ones by a ring. Through Monte Carlo experiments, where asteroids are assigned random but reasonable masses, it is possible to calculate the corresponding perturbations from the selected set of asteroids (Fienga et al. 2009) An estimate of the mass of the ring by Kuchynka et al. (2008) was M_{ring} = 1 ± 0.3 × 10^{10} M_{Sun} for a ring at 3.14 AU. Yet compared this statistical evaluation, the uncertainty concerning the largest asteroids looks like a sever limitation for the ephemeris accuracy. For instance, the mass evaluation of asteroid 111 Ate is 0.84 × 10^{10} M_{Sun}. This is very close to the evaluation of the mass of the ring above, and is accompanied by a 22% mass uncertainty (see Table 1). This is will cause a severe degradation of the accuracy in the Mars positioning in particular. To clearly demonstrate this degradation, we show in Fig. 19 the difference of the EMBtoMars distance from two types of planetary ephemeris DE405 (Standish 1998) and INPOP08 (Fienga et al. 2008). In the same figure we represent also the difference in the EMBtoMars distance due to the uncertainty on the sole mass of 111 Ate.
Fig. 19 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Ate’s mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER 
We point out the astonishing correspondence between the two curves in phase, frequency and amplitude. This suggests that the differences in the values of masses for this asteroid between the two ephemerides are highly responsible for their mutual discrepancy. For comparison we show in Figs. 20 to 22 the effects on the EMBMars distance of the mass uncertainty of 46 Hestia, 19 Fortuna, 1 Ceres, 2 Pallas, and 4 Vesta (Appendix C). We note that for these three last asteroids, which are the biggest ones, the effect is negligible, because of the very good mass accuracy. In contrast, for the first two the effect becomes clearly significant after a few years with an amplitude of roughly 1/8th and 1/16th that of 111 Ate (see Fig. 19) for a 100 y time interval, that is to say, 2 km and 1 km instead of 16 km.
Fig. 20 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Hestia’s mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER 
Fig. 21 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Fortuna’s mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER 
Fig. 22 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Ceres’ mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER 
In this context, our ASETEP database is an interesting and useful tool for understanding in a direct manner the limitations of modern ephemerides of terrestrial planets caused by the uncertainty on asteroid masses. It enables one to clearly indicate which asteroid would have to be observed preferentially in order to limitate its degradation on ephemeris accuracy. We limitated our study to a small sample of 43 asteroids for which the mass is known with relatively good accuracy, i.e. with less than 65% uncertainty, as we explained in Sect. 2. But we can easily extend this study to a much larger set of asteroids. To some extent our work is similar to that of Fienga et al. (2009), who constructed the INPOP08 planetary ephemeris: they also analyzed the individual effects of very many asteroids one by one, but without carrying out a Fourier and Poisson series decomposition of each signal as we did, and without comparing this decomposition with specific studies (Williams 1984). Indeed, the great advantage of such a decomposition is to understand, at a given period (or frequency) range, which asteroid is dominant both in terms of amplitude (related to the mass M) and amplitude uncertainty (related to δM/M).
Another use of ASETEP is the straightforward listing of asteroidal effects. In Table 12, we show the effects of the asteroid mass uncertainty on fundamental parameters such as the determination of the distance from the EMB to Mars, Venus and Mercury. For each planet, the value of the uncertainty on the EMPtoplanet distance is given in decreasing order of amplitude. The most problematic asteroids for Mars are 111 Ate, with a dramatic 139.0 km uncertainty, followed by 46 Hestia (22.0 km), 20 Massilia (14.0 km), 19 Fortuna (12.1 km), and 3 Juno (10.5 km). In the case of Venus, 46 Hestia is dominant with a 7.2 km amplitude uncertainty, followed by 111 Ate (4.2 km), 3 Juno (1.4 km), 7 Iris (1.3 km) and 16 Psyche (1.2 km) The leading uncertainties for Mercury come from 111 Ate (4.1 km), 46 Hestia (3.8 km) and 165 Loreley (0.9 km). Additional information of ASETEP is the ratio of the amplitude of the uncertainty of Mars to that of Venus and Mercury, respectively. Because of the proximity of Mars to the asteroids this ratio would a priori be significantly higher by one or two orders. This is indeed what we can notice except for a few cases. The minimum and maximum values of the ratio are 0.15 (47 Aglaja) and 186.27 (19 Fortuna) respectively for Venus; they are 0.32 (47 Aglaja) and 224.54 (31 Euphrosyne) for Mercury.
Fig. 23 Peaktopeak effects (black circles) and respective uncertainty (red circles) of the EMBtoMars distance for each asteroid mass. 

Open with DEXTER 
In Fig. 23 we represent as a function of the mass of each of the 43 asteroids both the amplitude of its effect on the EMBtoMars distance and the amplitude of the uncertainty of determination of this effect. Clearly, if we exclude 111 Ate which offers by far the largest uncertainty, the following asteroids in decreasing amplitude of effects are not the largest ones but constitute a cluster with mass ranging between 3 × 10^{12} M_{S} and 3 × 10^{11} M_{S}.
Uncertainty of the distances EarthMercury, EarthVenus, and EarthMars, due to the asteroids mass unaccuracy for a 1000 y time interval.
8. Conclusion and prospects
We have carried out detailed studies of the individual effects on the orbital parameters and geocentric positions of the terrestrial planets of a set of 43 of the most interesting asteroids, selected for their large mass and the relatively good accuracy of their mass determination, This continues previous research of Williams (1984) and Mouret et al. (2009) in a more systematic and extended way, These authors had restricted their results sole on the planet Mars and only two orbital parameters, i.e. a_{Mars} and λ_{Mars}.

1.
In contrast to these authors we performed a purely numericalstudy, based on the numerical integration of the nbody problem.To validate our method, we compared our results for the effects ofCeres, Pallas, Vesta and other leading asteroids ona_{Mars} and λ_{Mars} with Mouret et al. (2009). We characterized the signals by a set of Fourier and Poisson series, whose arguments and amplitudes fit the analytical tables of Mouret et al. (2009) very well, which were constructed as a Fourier series as a function of the mean longitudes of Mars and the asteroids. This both validates our methodology and confirms the analytical tables of Williams (1984) and Mouret et al. (2009).

2.
We extended our investigations to the other parameters e_{mars}, i_{Mars}, Ω_{Mars}, , and we summarized in a table the amplitude of the effect of each asteroid, and the uncertainty on the modelisation of this effect directly proportional to the relative mass uncertainty ΔM_{ast.}/M_{ast.}.

3.
Moreover, we studied the other terrestrial planets Mercury, Venus and the Earth (the EarthMoon barycenter) in the same way, gathering our results in recapitulative tables.

4.
We also evaluated the influences of each asteroid on the equatorial coordinates α, δ and the geocentric distance d of the three terrestrial planets Mercury, Venus and Mars, as well as the uncertainty on these parameters that are directly linked to the mass uncertainty of each asteroid. Our results will be compared, with those obtained recently by Kuchynka et al. (2010), in the case of common asteroids.

5.
All results of our study are gathered in the ASETEP database (asteroid effects on the terrestrial planets), i.e. the tables of the decomposition of the signals with the leading components of the fit as a function of Fourier and Poisson series, and also the curves showing the asteroid effects and the residuals after substraction of the fit. These tables are available only for a 1000 y time span. The ASTEP database can be accessed at http://hpiers.obspm.fr/icrspc/. As a first step of construction of ASETEP we resticted our study on a limited set of 43 asteroids. But one of the advantages of this database is that it is generated automatically and can be updated each time a new and more accurate determination of the masses of selected asteroids is made or when a new asteroid is included. The ASETEP database enables one to characterize the influence of each asteroid on the orbital motion of the terrestrial planets in an accurate and detailed manner, and will guide the efforts toward improvements of the ephemeris. The case of 111 Ate is particularly significant, because we were able to show that the differences given by two types of ephemerides (DE405 and IPOP08) on the EMBMars distance is remarkably similar to the effect caused by the mass uncertainty on this asteroid, which suggests the choice of two different masses for 111 Ate in the ephemeris given above.
Acknowledgments
This work is supported for the first author by a Ph.D. fellowship from the Damsacus University, Syria.
References
 Aslan, Z., Gumerov, R., Hudkova, L., et al. 2007, ASP Conf. Ser., 370 [Google Scholar]
 Baer, J., URL: http://home.earthlink.net/~jimbaer1/astmass.htm [Google Scholar]
 Baer, J., & Chesley, R. S. 2008a, Cel. Mech. Dyn. Astr., 100, 27 [NASA ADS] [CrossRef] [Google Scholar]
 Baer, J., Milani, A., Chesley, S., & Matson, R. D. 2008b, DPS meeting, 40, 493 [Google Scholar]
 Bange, J. 1998, A&A, 340, L1 [NASA ADS] [Google Scholar]
 Bange, J. F., & BecBorsenberger, A. 1997, ESA, 402, 169 [Google Scholar]
 Bretagnon, P., & Francou, G. 1987, A&A, 202, 309 [NASA ADS] [Google Scholar]
 Brouwer, D., & Clemence, G. M. 1961, Methods of Celestial Mechanics (New York: Acadimic Press) [Google Scholar]
 ChaprontTouzé, M., & Chapront, J. 1988, A&A, 190, 342 [NASA ADS] [Google Scholar]
 Fienga, A., Manche, H., Laskar, J., & Gastineau, M. 2008, A&A, 477, 315 [NASA ADS] [CrossRef] [EDP Sciences] [Google Scholar]
 Fienga, A., Laskar, J., Morley, T., et al. 2009, A&A, 507, 1675 [NASA ADS] [CrossRef] [EDP Sciences] [Google Scholar]
 Hilton, J. L. 1999, AJ, 117, 1077 [NASA ADS] [CrossRef] [Google Scholar]
 Ivantsov, A. 2008, Planet. Space Sci., 56, 1857 [NASA ADS] [CrossRef] [Google Scholar]
 Kochetova, O. M. 2004, Sol. Syst. Res., 38, 66 [NASA ADS] [CrossRef] [Google Scholar]
 Kuchynka, P. 2010, Observatoire de Paris, Ph.D. [Google Scholar]
 Kuchynka, P., Laskar, J., Fienga, A., Manche, H., & Somenzi, L. 2008, Journees Astrometry, Geodynamics and Astronomical Reference Systems, ed. M. Soffel, & N. Capitaine (Dresden) [Google Scholar]
 Kuchynka, P., Laskar, J., Fienga, A., & Manche, H. 2010, A&A, 514, A96 [NASA ADS] [CrossRef] [EDP Sciences] [Google Scholar]
 Laskar, J., & Robutel, P. 1995, Cel. Mech. Dyn. Astron., 62, 193 [NASA ADS] [CrossRef] [MathSciNet] [Google Scholar]
 Marchis, F., Descamps, P., Berthier, J., et al. 2008a, Icarus, 195, 295 [NASA ADS] [CrossRef] [Google Scholar]
 Marchis, F., Descamps, P., Baek, M., et al. 2008b, Icarus, 196, 97 [NASA ADS] [CrossRef] [Google Scholar]
 Mouret, S., Hestroffer, D., & Mignard, F. 2007, A&A, 472, 1017 [NASA ADS] [CrossRef] [EDP Sciences] [Google Scholar]
 Mouret, S., Simon, J. L., Mignard, F., & Hestroffer, D. 2009, A&A, 508, 479 [NASA ADS] [CrossRef] [EDP Sciences] [Google Scholar]
 Murray, C. D., & Dermott, S. F. 1999, Solar System Dynamics (Cambridge University Press) [Google Scholar]
 Pitjeva, E. V., & Standish, E. M. 2009, Cel. Mech. Dyn. Astron., 103, 365 [NASA ADS] [CrossRef] [MathSciNet] [Google Scholar]
 Simon, J. L. 1987, A&A, 175, 303 [NASA ADS] [Google Scholar]
 Standish, E. M. 1998, IOM, 312.F, 98 [Google Scholar]
 Standish, E. M. 2004, A&A, 417, 1165 [NASA ADS] [CrossRef] [EDP Sciences] [Google Scholar]
 Standish, E. M., & Fienga, A. 2002, A&A, 384, 322 [NASA ADS] [CrossRef] [EDP Sciences] [Google Scholar]
 Standish, E. M., & Hellings, R. W. 1989, Icarus, 80, 326 [NASA ADS] [CrossRef] [Google Scholar]
 Tedesco, E. F., Cellino, A., & Zappala, V. 2005, AJ, 129, 2869 [NASA ADS] [CrossRef] [Google Scholar]
 Williams, J. G. 1984, Icarus, 57, 1 [NASA ADS] [CrossRef] [Google Scholar]
 Williams, J. G. 1989, Asteroid family identifications and proper elements, ed. R. P. Binzel, T. Gehrels, M. Matthews (Asteroids II, Univ. of Arizona Press), 1034 [Google Scholar]
 Yeomans, D. K., Barriot, J. P., Dunham, D. W., et al. 1997, Science, 278, 2106 [NASA ADS] [CrossRef] [PubMed] [Google Scholar]
Online material
Appendix A: Effects on the Mars orbital motion
Coefficients of Fourier and Poisson series for the effects of Ceres on e_{Mars}.
Fig. A.1 Effects of Ceres on e_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER 
Coefficients of Fourier and Poisson series for the effects of Ceres on i_{Mars}.
Fig. A.2 Effects of Ceres on i_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER 
Coefficients of Fourier and Poisson series for the effects of Ceres on Ω_{Mars}.
Fig. A.3 Effects of Ceres on Ω_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER 
Coefficients of Fourier and Poisson series for the effects of Ceres on .
Fig. A.4 Effects of Ceres on for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER 
Coefficients of Fourier and Poisson series for the effects of Pallas on a_{Mars}.
Coefficients of Fourier and Poisson series for the effects of Vesta on a_{mars}.
Appendix B: individual and combined asteroidal effects
Fig. B.1 Combined effects of the 43 asteroids on e_{Mars}. The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER 
Fig. B.2 Zoom of the green curve of Fig. B.1, showing the difference between two ways of computation. 

Open with DEXTER 
Fig. B.3 Combined effects of the 43 asteroids on i_{Mars}. The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER 
Fig. B.4 Zoom of the green curve of Fig. B.3, showing the difference between two ways of computation. 

Open with DEXTER 
Fig. B.5 Combined effects of the 43 asteroids on Ω_{Mars}. The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER 
Fig. B.6 Zoom of the green curve of Fig. B.5, showing the difference between two ways of computation. 

Open with DEXTER 
Fig. B.7 Combined effects of the 43 asteroids on . The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER 
Fig. B.8 Zoom of the green curve of Fig. B.7, showing the difference between two ways of computation. 

Open with DEXTER 
Fig. B.9 Combined effects of the 43 asteroids on λ_{Mars}. The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER 
Fig. B.10 Zoom of the green curve of Fig. B.9, showing the difference between two ways of computation. 

Open with DEXTER 
Appendix C: Use of ASTEP for ephemerides study
Fig. C.1 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Pallas’ mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER 
Fig. C.2 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Vesta’s mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER 
All Tables
Mass estimation of the 43 asteroids selected in this paper, with their relative uncertainty.
Comparisons of the amplitude of the sinusoids found in this paper with the analytical ones of Mouret et al. (2009) of the effects of Ceres, Pallas and Vesta on a_{Mars}.
Comparisons of the sinusoids found in this paper with those in Mouret et al. (2009) of the effects of Ceres, Pallas and Vesta on λ_{Mars}.
Peaktopeak amplitudes of the variations of the six Mars orbital elements for a 1000 y time interval starting from JD 2009.81.
Uncertainty on the values of the six Mars orbital elements, for a 1000 y, because of the lack of accuracy in the measurements of the asteroid mass.
Peaktopeak amplitudes of the variations of the six EMB orbital elements due to each given asteroid for a 1000 y time interval starting from JD 2009.81.
Peaktopeak amplitudes of the variations of the six Mercury orbital elements due to each given asteroid for a 1000 y time interval starting from JD 2009.81.
Peaktopeak amplitudes of the variations of the six Venus orbital elements due to the action of each asteroid for a 1000 y time interval starting from JD 2009.81.
Uncertainty of the distances EarthMercury, EarthVenus, and EarthMars, due to the asteroids mass unaccuracy for a 1000 y time interval.
Coefficients of Fourier and Poisson series for the effects of Ceres on e_{Mars}.
Coefficients of Fourier and Poisson series for the effects of Ceres on i_{Mars}.
Coefficients of Fourier and Poisson series for the effects of Ceres on Ω_{Mars}.
Coefficients of Fourier and Poisson series for the effects of Pallas on a_{Mars}.
Coefficients of Fourier and Poisson series for the effects of Vesta on a_{mars}.
All Figures
Fig. 1 Effects of Ceres on a_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (black), fitting curve (red) and residuals (in green). 

Open with DEXTER  
In the text 
Fig. 2 Effects of Ceres on λ_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER  
In the text 
Fig. 3 Effects of Pallas on a_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER  
In the text 
Fig. 4 Effects of Vesta on a_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER  
In the text 
Fig. 5 Effects of Ceres, Pallas and Vesta on i_{Mars}, for a 100 y time interval, starting from JD 2009.81. 

Open with DEXTER  
In the text 
Fig. 6 Effects of Ceres, Pallas and Vesta on e_{Mars}, for a 100 y time interval starting from JD 2009.81. 

Open with DEXTER  
In the text 
Fig. 7 Effects of Ceres, Palass and Vesta on Ω_{Mars}, for a 100 y time interval, starting from JD 2009.81. 

Open with DEXTER  
In the text 
Fig. 8 Effects of Ceres, Pallas and Vesta on , for a 100 y time interval, starting from JD 2009.81. 

Open with DEXTER  
In the text 
Fig. 9 Effects of Ceres on a_{EMB}, for a 100 y time interval, from JD 2009.81. Residuals (in green) after removing the sinusoidal components from the leastsquares analysis. 

Open with DEXTER  
In the text 
Fig. 10 Effects of Pallas on a_{EMB}, for a 100 y time interval, from JD 2009.81. Residuals (in green) after removing the sinusoidal components from the leastsquares analysis. 

Open with DEXTER  
In the text 
Fig. 11 Effects of Vesta on a_{EMB}, for a 100 y time interval, from JD 2009.81. Residuals (in green) after removing the sinusoidal components from the leastsquares analysis. 

Open with DEXTER  
In the text 
Fig. 12 Effects of Ceres on the distance from the EMB to Mars for a 100 y time interval from JD 2009.81. The curve in green corresponds to the postfit residuals. 

Open with DEXTER  
In the text 
Fig. 13 Effects of Pallas on the distance from the EMB to Mars for a 100 y time interval from JD 2009.81. The curve in green corresponds to the postfit residuals. 

Open with DEXTER  
In the text 
Fig. 14 Effects of Vesta on the distance from the EMB to Mars for a 100 y time interval from JD 2009.81. The curve in green corresponds to the postfit residuals. 

Open with DEXTER  
In the text 
Fig. 15 Effects of Ceres on α_{Mars} for a 100 y time interval from JD 2009.81. The curve in green corresponds to the postfit residuals. 

Open with DEXTER  
In the text 
Fig. 16 Effects of Ceres on δ_{Mars} for a 100 y time interval from JD 2009.81. The curve in green corresponds to a postfit residuals. 

Open with DEXTER  
In the text 
Fig. 17 Peaktopeak amplitude of the combined effects of the 43 asteroids on a_{Mars}. The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER  
In the text 
Fig. 18 Zoom of the green curve of Fig. 17, showing the difference between two ways of computation. 

Open with DEXTER  
In the text 
Fig. 19 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Ate’s mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER  
In the text 
Fig. 20 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Hestia’s mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER  
In the text 
Fig. 21 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Fortuna’s mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER  
In the text 
Fig. 22 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Ceres’ mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER  
In the text 
Fig. 23 Peaktopeak effects (black circles) and respective uncertainty (red circles) of the EMBtoMars distance for each asteroid mass. 

Open with DEXTER  
In the text 
Fig. A.1 Effects of Ceres on e_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER  
In the text 
Fig. A.2 Effects of Ceres on i_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER  
In the text 
Fig. A.3 Effects of Ceres on Ω_{Mars} for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER  
In the text 
Fig. A.4 Effects of Ceres on for a 100 y time interval from JJ 2009.81; raw signal (in black), fitting curve (in red) and residuals (in green). 

Open with DEXTER  
In the text 
Fig. B.1 Combined effects of the 43 asteroids on e_{Mars}. The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER  
In the text 
Fig. B.2 Zoom of the green curve of Fig. B.1, showing the difference between two ways of computation. 

Open with DEXTER  
In the text 
Fig. B.3 Combined effects of the 43 asteroids on i_{Mars}. The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER  
In the text 
Fig. B.4 Zoom of the green curve of Fig. B.3, showing the difference between two ways of computation. 

Open with DEXTER  
In the text 
Fig. B.5 Combined effects of the 43 asteroids on Ω_{Mars}. The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER  
In the text 
Fig. B.6 Zoom of the green curve of Fig. B.5, showing the difference between two ways of computation. 

Open with DEXTER  
In the text 
Fig. B.7 Combined effects of the 43 asteroids on . The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER  
In the text 
Fig. B.8 Zoom of the green curve of Fig. B.7, showing the difference between two ways of computation. 

Open with DEXTER  
In the text 
Fig. B.9 Combined effects of the 43 asteroids on λ_{Mars}. The curve in green represents the difference between two ways of computation: adding individual perturbations, or making a combined integration. 

Open with DEXTER  
In the text 
Fig. B.10 Zoom of the green curve of Fig. B.9, showing the difference between two ways of computation. 

Open with DEXTER  
In the text 
Fig. C.1 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Pallas’ mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER  
In the text 
Fig. C.2 Uncertainty of the EMBtoMars distance due to the lack of accuracy in Vesta’s mass (red curve) and difference in the EMBtoMars distance between DE405 and INPOP08 (black curve). 

Open with DEXTER  
In the text 
Current usage metrics show cumulative count of Article Views (fulltext article views including HTML views, PDF and ePub downloads, according to the available data) and Abstracts Views on Vision4Press platform.
Data correspond to usage on the plateform after 2015. The current usage metrics is available 4896 hours after online publication and is updated daily on week days.
Initial download of the metrics may take a while.