Transneptunian Orbit Computation 25

Virtanen et al.: Transneptunian Orbit Computation 25 Transneptunian Orbit Computation Jenni Virtanen Finnish Geodetic Institute Gonzalo Tancredi University of Uruguay G. M. Bernstein University of Pennsylvania Timothy Spahr Smithsonian Astrophysical Observatory Karri Muinonen University of Helsinki We review the orbit computation problem for the transneptunian population. For these dis- tant objects, the problem is characterized by their short observed orbital arcs, which are known to be coupled with large uncertainties in orbital elements. Currently, the observations of even the best observed objects, such as the first-ever transneptunian object (TNO), Pluto, cover only a fraction of their revolution. Furthermore, of the some 1200 objects discovered since 1992, roughly half have observations from only one opposition. To ensure realistic analyses of the population, e.g., in the derivation of unbiased orbital distributions or correlations between orbital and physical properties, realistic estimation of orbital uncertainties is important. We describe the inverse problem of orbit computation, emphasizing the short-arc problem and its statistical treatment. The complete solution to the problem can be given in terms of the orbital- element probability density function (p.d.f.), which then serves as a starting point for any fur- ther analysis, where knowledge of orbital uncertainties is required. We give an overview of the variety of computational techniques developed for TNO orbital uncertainty estimation in the recent years. After presenting the current orbital distribution, we demonstrate their application to several prediction problems, such as classification, ephemeris prediction, and dynamical analysis of objects. We conclude with some future prospects for TNO orbit computation concerning the forthcoming next-generation surveys, including the anticipated evolution of TNO orbital uncertainties over the coming decades. 1. INTRODUCTION in the pencil-beam surveys (e.g., Gladman et al., 1998), a large portion of observing efforts have subsequently been After over a decade of dedicated observations, the trans- carried out by the Deep Ecliptic Survey (Millis et al., 2002; neptunian population of small bodies has recently passed Elliot et al., 2005). While the number of well-observed ob- the landmark of 1000 known objects. The observational data jects has been steadily increasing, so has the number of un- for individual objects extend over several decades, but as a followed discoveries: In the 2000s, roughly half the TNOs population the transneptunian objects (TNOs) are still char- discovered each year have remained as one-apparition ob- acterized by their short observed orbital arcs. jects, which is also the fraction of one-apparition objects in Due to their distance from the observer as well as their the current population (as of May 2006). It is worth noting long orbital periods, observing the population can be both that one of the earliest TNO discoveries, 1993 RP, remains costly and tedious. Both discovery and followup observa- lost some 13 years after discovery. tions have mostly been acquired in dedicated surveys that In the chain of efforts to analyze the observed popula- have been adapted to the slow motions and faint magnitudes tion, orbit computation is in practice the first task to be of the targets. While many of the first discoveries were made accomplished. It is also a critical one, since all followup 25 26 The Solar System Beyond Neptune questions depend, in one way or the other, on the orbital with several prediction problems, such as classification and elements, which need to be derived already from the often- ephemeris prediction. In section 5, we conclude with some limited discovery data. For the individual objects, ephemeris future prospects for TNO orbit computation. predictions for followup observations require reasonable estimates for the orbital elements as well as their uncertain- 2. ORBITAL INVERSION AND ties. For the population, realistic evaluation of uncertainties UNCERTAINTY ESTIMATION from astrometric data offer the starting point for the derivation of unbiased orbital distributions (see the chapter by In orbital inversion, we want to derive information on the Kavelaars et al.) and for analyzing the dynamical structure orbital parameters from astrometric observations. Through of the transneptunian region (chapter by Gladman et al., the awareness of the existing uncertainty in observed as- hereafter G07). teroid positions, orbits are today treated in a probabilistic The short-arc orbit computation problem has been ex- fashion. A fundamental question in orbital inversion is the tensively studied for the inner solar system, particularly in accuracy of the parameters derived. The orbital elements are the recent years in the quest for Earth-approaching aster- often not used as such, rather one wants to have an esti- oids. A great number of numerical techniques have been mate for their uncertainty that can then be propagated to developed to derive orbits for asteroids since the discovery another epoch in time or to different parameter space (e.g., of asteroid Ceres in 1801. We refer to Bowell et al. (2002) to sky-plane coordinates). According to statistical inverse and Milani et al. (2002) for general reviews of the progress theory (e.g., Lehtinen, 1988; Menke, 1989), the complete made in the past decade and restrict ourselves to those ad- solution to the inversion is given in terms of an orbital-el- vances particularly relevant for TNOs. The most important ement probability density function (p.d.f.). While the evalu- development has been the change in viewpoint from deter- ation of the p.d.f. can be a complicated task, the advantage mination of orbits to estimation of orbital uncertainty. Many is that, once derived, there is no need for additional error of the advances are related to nonlinear uncertainty estima- analysis, which is sometimes a major obstacle in traditional, tion, which is essential for short arcs, or to specific use of deterministic approaches. Access to the full p.d.f. is useful, the linear approximation, particularly for TNOs. if not crucial, in many applications. This is the case when This active research has resulted in new tools for the evaluating collision probabilities, which rely on knowledge users of the end product, the orbital elements, either by of the orbital-element p.d.f., or when analyzing the orbital means of software or orbital databases, both of which we characteristics of small bodies as a population, as in the describe in the current chapter. The orbits of TNOs are present paper. nowadays made available, in essence, through four well- established web-based services: at the Minor Planet Cen- 2.1. Statistical Inverse Problem ter (MPC), at Lowell Observatory, at the University of Pisa (“AstDys”), and at the Jet Propulsion Laboratory (JPL). The In the following, we will summarize the formulation of MPC maintains a database of TNO orbits together with all orbit computation in the framework of statistical inverse their astrometric data. Careful checking of incoming obser- theory following Muinonen and Bowell (1993). The prin- vations and putative identifications by MPC staff limits the cipal idea is that all the available information involved in number of incorrect observations or identifications for these the inversion can be presented with the a posteriori prob- objects, and as a result the MPC database is probably >99% ability density for the orbital elements. accurate in terms of matching the proper observations and There are several choices for the parameterization of orbits. It is worth noting that with such sparsely observed orbits; we denote the osculating orbital elements of an as- P objects, bad linkages can occur at fairly high rates, and these teroid at a given epoch t0 by .the. six-vector. The Carte- linkages can often result in an acceptable differential cor- sian elements P = (X, Y, Z, X, Y, Z)T are well-suited for rection but also a spurious orbit. Of the four services, the numerical computations; in a given Cartesian reference T AstDys and JPL databases provide also formal orbital un- frame, the coordinates. (X, Y, Z) denote the position and certainties for the objects in terms of covariance matrices. the coordinates (X, Y, Z)T the velocity (T is transpose). For In addition, AstDys also offers proper elements for outer- illustrative purposes, we use Keplerian elements, P = (a, e, Ω ω T solar-system objects. Ephemeris prediction service TNOEPH i, , , M0) and the elements are, respectively, the semi- (Granvik et al., 2003) is on the other hand the first web- major axis, eccentricity, inclination, longitude of ascending based realization of nonlinear uncertainty propagation. node, argument of perihelion, and mean anomaly. The three The chapter is organized as follows. We first describe angular elements i, Ω, and ω are currently referred to the the inverse problem of orbit computation, emphasizing the ecliptic at equinox J2000.0. The equations describing the short-arc problem and its statistical treatment. We demon- inverse problem are the observation equations strate the use of various computational techniques developed for TNOs (section 2) and evaluate the current orbital ψ = Ψ(P,t) + ε (1) uncertainties for the observed population (section 3). In ψ α δ section 4, we discuss the orbital distributions in connection which relate the astrometric observations = ( 1, 1; . .; Virtanen et al.: Transneptunian Orbit Computation 27 α δ T T Ψ Λ N, N) made

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