Complexity of the Gaia astrometric least-squares problem and the (non-)feasibility of a direct solution method

A. Bombrun; L. Lindegren; B. Holl; S. Jordan

doi:10.1051/0004-6361/200913503

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A&A, 516 (2010) A77

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Issue		A&A Volume 516, June-July 2010


Article Number		A77
Number of page(s)		13
Section		Astronomical instrumentation
DOI		https://doi.org/10.1051/0004-6361/200913503
Published online		14 July 2010

A&A 516, A77 (2010)

Complexity of the Gaia astrometric least-squares problem and the (non-)feasibility of a direct solution method

A. Bombrun¹ - L. Lindegren² - B. Holl² - S. Jordan¹

1 - Astronomisches Rechen-Institut, Zentrum für Astromomie der Universität Heidelberg, Mönchhofstr. 12-14, 69120 Heidelberg, Germany
2 - Lund Observatory, Lund University, Box 43, 22100 Lund, Sweden

Received 19 October 2009 / Accepted 16 March 2010

Abstract
The Gaia space astrometry mission (to be launched in 2012) will use a continuously spinning spacecraft to construct a global system of positions, proper motions and absolute parallaxes from relative position measurements made in an astrometric focal plane. This astrometric reduction can be cast as a classical least-squares problem, and the adopted baseline method for its solution uses a simple iteration algorithm. A potential weakness of this approach, as opposed to a direct solution, is that any finite number of iterations results in truncation errors that are difficult to quantify. Thus it is of interest to investigate alternative approaches, in particular the feasibility of a direct (non-iterative) solution. A simplified version of the astrometric reduction problem is studied in which the only unknowns are the astrometric parameters for a subset of the stars and the continuous three-axis attitude, thus neglecting further calibration issues. The specific design of the Gaia spacecraft and scanning law leads to an extremely large and sparse normal equations matrix. Elimination of the star parameters leads to a much smaller but less sparse system. We try different reordering schemes and perform symbolic Cholesky decomposition of this reduced normal matrix to study the fill-in for successively longer time span of simulated observations. Extrapolating to the full mission length, we conclude that a direct solution is not feasible with today's computational capabilities. Other schemes, e.g., eliminating the attitude parameters or orthogonalizing the observation equations, lead to similar or even worse problems. This negative result appears to be a consequence of the strong spatial and temporal connectivity among the unknowns achieved by two superposed fields of view and the scanning law, features that are in fact desirable and essential for minimizing large-scale systematic errors in the Gaia reference frame. We briefly consider also an approximate decomposition method à la Hipparcos, but conclude that it is either sub-optimal or effectively leads to an iterative solution.

Key words: methods: data analysis - methods: numerical - space vehicles: instruments - astrometry - reference systems

1 Introduction

The Gaia mission (Lindegren et al. 2008; Perryman et al. 2001) has been designed to measure the astrometric parameters (positions, proper motions and parallaxes) of around one billion objects, mainly stars belonging to our Galaxy. Gaia is a spinning spacecraft equipped with two telescopes that point in directions orthogonal to the spin axis and that share the same focal plane composed of a large mosaic of CCDs. The spin axis is actively maintained at a a fixed angle of $45^\circ$ with respect to the satellite-Sun direction, while performing a precession-like motion around the Sun direction with a period of about 63 days (Jordan 2008). The elementary astrometric observations consist of quasi-instantaneous measurements of the positions of stellar images with respect to the CCDs, from which the celestial coordinates of the objects may be computed.

One challenging aspect of the Gaia mission is precisely how to build the catalogue of astrometric parameters from such elementary measurements. The image of each star will pass many times through the focal plane. In order to build the celestial map with the required accuracy (a few microarcsec, $\mu$ as), it is necessary to recover the attitude of the spacecraft and calibrate the instrument to the same accuracy. This can only be achieved by considering the strong interconnection between all the unknowns throughout all the observations. Effectively it means that all the data must be treated together in a single solution, which makes this task computationally difficult but also results in a numerically ``stiff'' solution, i.e., one in which observation noise cannot easily generate large-scale distortions of the celestial reference frame.

In this highly simplified description of the astrometric solution for Gaia we have ignored the complex pre-processing of the raw CCD data as well as its interaction with the photometric and spectroscopic data (e.g., in order to calibrate colour dependent image shifts) and the circumstance that a large fraction of the objects are resolved or astrometric binaries, solar system objects, etc., requiring special treatment. We are here concerned with the core astrometric solution of perhaps 10⁸ well-behaved ``primary sources'' which also provides the basic instrument calibration and attitude parameters. Following accepted nomenclature in the Gaia data processing community, the term ``source'' is here used to designate any (point-like) object detected by the instrument. The primary sources may include some extragalactic objects (AGNs or quasars) in addition to stars.

In the core astrometric solution all the calibration, attitude and primary source parameters must therefore be adjusted to fit all the measurements as best as possible. From a mathematical point of view the adjustment can be understood as a least-squares problem. The resulting large, sparse system of equations has superficial similarities with many other problems, for example in geodesy and finite element analysis - an analogue in classical astrometry is the plate-overlap technique (Jefferys 1979). However, the actual structure of the system is in each case intimately connected to the physics of the problem and this strongly influences the possible solution methods. The idea of using a spinning spacecraft to measure the large angles between stars, using two telescopes with a common focal plane, is due to Lacroute (1975,1967). This genial design principle, first used for Hipparcos, has been adopted for Gaia too and has a strong impact on the structure of the observed data.

In this paper we investigate the structure of the equations resulting from a simplified formulation of the astrometric adjustment problem and demonstrate how it is directly connected with the Gaia instrument design and scanning law. The purpose of this exercise is to motivate a posteriori the use of iterative methods to the numerical solution of the adjustment problem. The method actually adopted for the Gaia data processing (Mignard et al. 2008) is the iterative, so-called Astrometric Global Iterative Solution (AGIS), fully described by Lindegren et al. (in prep.) and O'Mullane et al. (in prep.). The original Hipparcos solution (Kovalevsky et al. 1992; Lindegren et al. 1992; ESA 1997, Vol. 3) used an approximate decomposition method, while the recent re-reduction of the main Hipparcos data by van Leeuwen (2007) used the iterative method.

It is a well know paradigm (Björck 1996, Sect. 7.1.1) that there does not exist an ``optimal'' algorithm capable of solving efficiently any large and sparse least-squares problem. Given the unknowns and the structure of their interdependencies, each problem requires its specific algorithm and software in order to be solved with a reasonable computational effort. Direct methods are suitable for certain problems, whereas for others an iterative method can be much more efficient. Iterative methods with a pre-conditioner can be seen as a hybrid between direct and iterative schemes. But, whereas a direct method by definition achieves its result in a finite number of arithmetic operations, an iterative method depends on some stopping criterion, i.e., the required number of iterations is not known a priori. Furthermore, direct methods may provide direct estimates of the statistical properties of the solution (e.g., from selected elements of the covariance matrix), which are not so easily obtained from an iterative solution.

In this study, we derive an estimate of the number of operations required for a direct solution based on normal equations by taking advantage of their special structure in the most straightforward manner. We argue that the complexity of the Gaia astrometric problem renders such a direct method, and simple variants of it, likely unfeasible in the foreseeable future. Apart from this negative result, the study provides new insights into the design principles of the Gaia mission.

In the context of solving large, sparse systems of equations it is necessary to make a clear distinction between the sparseness as such and the complexity of the sparseness structure. Sparseness refers to the circumstance that most of the elements in the large matrices that appear in these problems are zero, and therefore need not be stored. Complexity refers to the circumstance that the structure of non-zero elements is non-trivial in some sense that is difficult to define precisely. However, one possible way to quantify complexity, which we adopt for this paper, is simply by the number of floating-point operations required to solve the system (essentially the total number of additions and multiplications), assuming a reasonably efficient method that takes into account its sparseness. We argue that the Gaia astrometric least-squares problem is both very sparse and very complex.

The paper is organized as follows. In Sect. 2 we present the basic observation equations and normal equations of the least-square problem associated with the astrometric data reduction process. We give these equations in an abstract form, emphasizing the connection between different data items, but without going into the mathematical details. In the subsequent sections we discuss and compare the different approaches to the astrometric solution (Sects. 3-5.3) and draw some general conclusions (Sect. 6). Appendix A and B give further details on the sparseness structure and fill-in of the normal equations for the direct method, based on simulated observations.

2 The astrometric equations

2.1 Input data for the astrometric solution

The astrometric solution links the astrometric parameters (i.e., the positions, parallaxes and proper motions) of the different sources by means of elementary measurements in the focal plane of Gaia. These measurements, which thus form the main input to the astrometric solution, consist of the precisely estimated times when the centres of the star images cross over designated points on the CCDs. They are the product of a complex processing task, known as the initial data treatment (IDT; Mignard et al. 2008), transforming the raw satellite data into more readily interpreted quantities. Although the details of this process are irrelevant for the present problem, a brief outline is provided for the reader's convenience.

The astrometric focal plane of Gaia contains a mosaic of 62 CCDs, covering an area of 0.5 deg² on the sky. Two such areas, or fields of view, are imaged onto the focal plane by means of an optical beam combiner. On the celestial sphere these fields are separated by a fixed and very stable ``basic angle'' of $106.5^\circ$ . The slow spinning of the satellite (with a period of 6 hr) causes the star images from either field of view to flow through the focal plane, where they are detected by the CCDs. The measurements are one-dimensional, along the scanning direction defined by the spin axis perpendicular to the two fields of view. The optical arrangement allows sources that are widely separated on the sky to be directly connected through quasi-simultaneous measurements on the same detectors. This is a key feature for achieving Gaia's highly accurate, global reference frame; but, as we shall see, it is also an important factor for the complexity of the astrometric solution.

Each CCD has 4500 pixels in the along-scan direction, with a projected pixel size of 59 mas matching the theoretical resolution of the telescope. The charge image of a source is built up while being clocked along the pixels in synchrony with the motion of the optical image due to the satellite spin. As the optical stellar images move off the edge of the CCD, the charges are read out as a time series of pixel values, corresponding to the along-scan intensity profile of each stellar image. In the initial data treatment, a calibrated line-spread function is fitted to the pixel values, providing estimates of the along-scan position of the image centroid in the pixel stream, as well as of the total flux in the image.

While the total integration time of the charge build-up along the CCD is about 4.4 s, it is usually a good enough approximation to regard the resulting observation as instantaneous, and referring to an instant of time that is half the integration time earlier than the readout of the image (Bastian & Biermann 2005). Thus, we may represent the astrometric observation by the precisely estimated instant when the image centre crosses the CCD ``observation line'' nominally situated between the 2250th and 2251st pixel. This instant is called the CCD observation time and denoted t_l, where l is the index used to distinguish the different CCD observations obtained over the mission. The ensemble of CCD observation times, here formally represented by the vector $\vec{t}$ (of dimension $\sim\!10^{11}$ ; see Sect. 2.4), is the main data input for the astrometric solution. The timing observations provide accurate (typically $\sim~$ 0.1 to 1 mas) information about the instantaneous relative along-scan positions of the observed objects.

2.2 The general problem

In its most general formulation, the Gaia astrometric solution can be considered as the minimization problem

$\begin{displaymath} \min_{\vec{s},~\vec{a},~\vec{c},~\vec{g}} \left\vert \vec{t} - \vec{f}(\vec{s},~\vec{a},~\vec{c},~\vec{g}) \right\vert ~ , \end{displaymath}$

(1)

where $\vec{s}$ , $\vec{a}$ , $\vec{c}$ and $\vec{g}$ are parameter vectors related to the sources, instrument attitude, instrument calibration, and global model of the observations, and $\vec{f}$ is a vector function of calculated CCD observation times based on the given parameters. The function $\left\vert . \right\vert$ is the vector norm on a suitable metric, taking into account the different weights of the observations and the treatment of outliers. The function $\vec{f}$ is in principle highly non-linear, but the initial data treatment provides an initial approximation to all the unknowns which is good enough (e.g., with errors $\epsilon < 10^{-6}~\mbox{rad}\simeq 0.2$ arcsec) that effectively all subsequent calculations can work with the linearized function (resulting in errors of the order of $\epsilon^2 < 10^{-12}~\mbox{rad}\simeq 0.2~\mu$ as).

In Eq. (1) we distinguish between four categories of parameters because of their different physical origins and the way they appear in the equations. For example, each source (distinguished by index i) has its own set of astrometric parameters, represented by a sub-vector $\vec{s}_i$ . Similarly, while the instrument attitude (i.e., its precise spatial orientation with respect to a celestial reference system) is in principle a single continuous function of time, its numerical representation is for practical reasons (data gaps, etc.) subdivided into time segments (index j) with independent attitude parameter sub-vectors $\vec{a}_j$ . The instrument calibration (i.e., the precise geometry of the optics and focal-plane assembly including the CCDs) is also subdivided into units (index k), e.g., for the different CCDs, with independent calibration parameter sub-vectors $\vec{c}_k$ . By definition, the global parameter vector is not similarly subdivided: it contains parameters that affect all observations, such as the parameterized post-Newtonian (PPN) parameter $\gamma$ (Hobbs et al. 2009).

Each CCD observation l is therefore uniquely associated with a specific object i, an attitude time segment j, and a calibration unit k. This mapping is formally expressed by the functions i(l), j(l), k(l). Adopting a weighted L2 (Euclidean) norm in Eq. (1), the minimization problem can then be written

$\begin{displaymath} \min_{\vec{s},~\vec{a},~\vec{c},~\vec{g}} \sum_l \left\vert\... ...l)},~ \vec{c}_{k(l)},~\vec{g}) \right\vert\right\vert^2 W_l~ , \end{displaymath}$

(2)

where W_l is the statistical weight associated with CCD observation l. Subsequently we assume that the weights are fixed and known.

The attitude parameters define the spatial orientation of the instrument as function of time, relative to the celestial reference system. For AGIS, the instantaneous attitude is represented by a unit quaternion (Wertz 1978), and the four components of the quaternion are represented as continuous functions of time by means of cubic spline functions on a (more or less regular) knot sequence. Since the quaternion is normalized to unit length, the model has three degrees of freedom per knot. In general, three independent quantities are needed to describe the orientation at any time, and we may assume that one of them to represent the rotational state around the satellite spin axis. Information about this (along-scan) attitude component is provided by the CCD observation times. Some of the CCD observations will give an additional measurement of the across-scan coordinate of the source image at the time of the observation. These observations are obtained with a lower accuracy than the along-scan (timing) observations, but are crucial for determination of the remaining two components of the attitude, representing orientation about two axes perpendicular to the spin axis. These measurements have to be included in the actual minimization problem (2), but they can be neglected here because they do not change the formal structure of the problem (i.e., they do not create additional links between the unknowns). For the present discussion it is useful to think of the instantaneous attitude as represented by three angles, one of which describing the along-scan orientation of the instrument and the other two being across-scan components of the attitude.

2.3 The simplified problem

In order to simplify the description of the astrometric problem, we will subsequently assume that the instrument is perfectly calibrated and that the global parameters are perfectly known, so that in effect we can ignore $\vec{c}$ and $\vec{g}$ in Eq. (1). The resulting simplified problem is therefore

$\begin{displaymath} \min_{\vec{s},~\vec{a}} \sum_l \left\vert \left\vert t_l - f_l(\vec{s}_i,~\vec{a}_j) \right\vert\right\vert^2 W_l~ , \end{displaymath}$

(3)

where, for conciseness, the dependence of i and j on l is not explicitly written out but is implied in this and the following equations.

There are several reasons for introducing the simplification of neglecting $\vec{c}$ and $\vec{g}$ . Concerning the global parameters, they are typically of such a nature that they can be considered known from first principles; e.g., the PPN parameter $\gamma=1$ according to General Relativity. Furthermore, there are much fewer calibration ( ${\la}10^6$ ) and global parameters ( ${\la}10^2$ ) than attitude ( ${\ga}2\times 10^7$ ) and source parameters ( ${\simeq}5\times 10^8$ for the primary sources). More importantly, experience both from the Hipparcos reductions and simulated Gaia data processing shows that the geometrical instrument calibration (e.g., determination of the effective field distortion) is quite straightforward and well separated from the determination of source and attitude parameters (e.g., by accumulating a map of average positional residuals across the field of view). The real problem lies in separating the source and attitude parameters. This can be qualitatively understood from a consideration of how the calculated observation times depend on the different parameters. Because each global or calibration parameter affects a very large number of observations spread over the whole celestial sphere, or a large part of it, its determination is not greatly affected by localized errors related to the source and attitude parameters. By contrast, both the attitude and source parameters may have a very local influence function on the sky, which could render their disentanglement more difficult (cf. van Leeuwen 2007, Sect. 1.4.6).

One further reason for considering the simplified problem is that we want to study the feasibility of a direct solution of the least-squares problem. It is then necessary that an efficient direct algorithm should first work for the simplified problem. Adding the calibration and global parameters can only make the problem more difficult.

2.4 Observations (data) and unknowns (parameters)

The simplified least-squares problem involves three very large vectors: $\vec{t}$ containing the observations (CCD observation times), $\vec{s}$ containing the unknown source parameters, and $\vec{a}$ containing the unknown attitude parameters.

To give an idea of the number of observations and unknowns we give rough approximations based on the current (and final) Gaia design. Gaia will observe a total of about 10⁹ objects, but only a fraction of them will be used for the astrometric solution, i.e., as ``primary sources''. (Astrometric parameters for other objects can be calculated off-line, one object at a time, once the attitude and calibration parameters have been determined by means of the primary sources.) The primary sources are selected iteratively for their astrometrically benign nature, e.g., avoiding all known or suspected double stars as well as sources showing unexpectedly large residuals in the astrometric solution. Apart from these constraints it is advantageous to use as many primary sources as possible because that will increase the accuracy of the instrument calibration and attitude determination. It is not known how many primary sources will eventually be used for Gaia, but a design goal for AGIS is to be able to handle at least 10⁸ primary sources, covering the full range of magnitudes and colours, with a not too uneven distribution on the sky, and being observed throughout the duration of the mission.

Neglecting observational dead time, the average number of CCD observations per object is directly given by the number of superposed fields (=2), the number of astrometric CCDs that the object successively crosses in each field of view (=9), the transverse (across-scan) size of the field of view ( $\Phi=0.676^\circ$ ), the mission length (T=5 years), and the satellite spin rate ( $\omega=60$ arcsec s^-1). The result is $2\times 9\times\Phi T\omega/(4\pi)\simeq 776$ CCD observations per object. With n=10⁸ primary sources the total number of observations is $o=\dim(\vec{t})\simeq 8\times 10^{10}$ .

There are five astrometric parameters per primary source (two components for the position at the reference epoch, one for the parallax, and two proper motion components, Lindegren et al., in prep.); hence $\dim(\vec{s})=5n\simeq 5\times 10^8$ .

The number of free attitude parameters depends on the adopted attitude model. This, in turn, should be optimized by taking into account the nature and level of perturbations on one hand, and the number and quality of primary source observations on the other. The new Hipparcos reduction (van Leeuwen 2007) used a dynamical model of the satellite to reduce the number of attitude parameters and hence improve the accuracy of the solution. For Gaia, the attitude control using continuously active gas thrusters will introduce high-frequency perturbations that make it meaningless to dynamically predict the along-scan attitude motion over intervals longer than a few seconds - after that the new observations are more accurate than the prediction. This suggests that the attitude model should have one degree of freedom per axis for every 10-20 s. With the adopted (cubic) spline representation of the attitude components as functions of time (see Sect. 2.2), and assuming a maximum knot interval of about 20 s, the minimum number of scalar attitude parameters for a 5-year mission is $m=\dim(\vec{a})\simeq 2\times 10^7$ .

It is reasonable to ask whether cubic splines are the best choice for a direct solution. It might be that a different representation of the attitude could reduce the number of attitude unknowns, in particular if the noise level introduced by the control system is less than currently foreseen. However, splines have an important advantage from a computational viewpoint, namely that they are local in the sense that a change in the data at point t' has little effect on the fitted spline at t, provided that |t'-t| is large enough (typically spanning tens of knots). The use of a dynamical model or other approximation schemes is likely to cause a partial loss of this ``locality'', and it can be inferred from the present study that this would vastly modify the sparseness structure of the adjustment problem in the sense of making a direct solution even harder.

2.5 Observation equations

The weighted least-squares problem (3) corresponds to the over-determined system of non-linear observation equations

$\begin{displaymath} \forall l: \qquad t_l = f_l (\vec{s}_i,~\vec{a}_j) \qquad\textrm{(weight $W_l$ )}~ . \end{displaymath}$

(4)

Since the function f_l is non-linear but smooth, we use a linear expansion around some suitable reference values ${\vec{s}}^0_i$ , ${\vec{a}}^0_j$ . With $\vec{x}_{si}$ , $\vec{x}_{aj}$ denoting the displacements around the reference values, the over-determined system of linearized observation equations is

$\begin{displaymath} \forall l: \qquad \frac{\partial f_l}{\partial\vec{s}_i'}\ve... ...a}_j'}\vec{x}_{aj} = t_l-f_l \qquad\textrm{(weight $W_l$ )}~ , \end{displaymath}$

(5)

with f_l and partial derivatives evaluated at the reference point $({\vec{s}}^0_i,{\vec{a}}^0_j)$ . (The prime 'denotes matrix transpose or the scalar product of vectors.) Multiplying each equation by the square root of its statistical weight (or, equivalently, dividing by its standard error), and introducing $h_l = (t_l-f_l)\sqrt{W_l}$ , $\vec{S}_{l} = (\partial f_l/\partial\vec{s}_i')\sqrt{W_l}$ , and $\vec{A}_{l} = (\partial f_l/\partial\vec{a}_j')\sqrt{W_l}$ , we obtain a set of observation equations of equal (unit) weight,

$\begin{displaymath} \forall l: \qquad \vec{S}_{l}\vec{x}_{si} + \vec{A}_{l}\vec{x}_{aj} = h_l \qquad\textrm{(weight $1$ )}~ . \end{displaymath}$

(6)

The choice of spline functions for representing the attitude has a direct influence on the structure of the observation equations (6) through the definition of $\vec{a}_j$ . A spline of order M (e.g., M=4 for cubic splines) can be written as the linear combination of basis functions called B-splines (de Boor 1978) that are uniquely defined by M and the non-decreasing knot sequence $\vec{\tau}=\{\tau_0,\tau_1,\dots\}$ . The B-splines have minimal support; more precisely, at any time t_l there are at most Mnon-zero B-splines. If $\tau_\ell \le t_l < \tau_{\ell+1}$ , then the M non-zero B-splines may be denoted $B_{\ell-M+1}(t_l)$ , $B_{\ell-M+2}(t_l)$ , $\dots,~B_{\ell}(t_l)$ and the associated spline coefficients $a_{\ell-M+1}$ , $a_{\ell-M+2}$ , $\dots,~a_{\ell}$ . The sub-vector $\vec{a}_j$ of the attitude parameters will therefore consist of at least 3M scalar values, namely one spline coefficient for each of the three orientation angles in each of at least M adjacent knots.

From Eq. (6) it is evident that observation equations for different sources involve disjoint source parameter sub-vectors $\vec{s}_i$ but may refer to the same attitude sub-vector $\vec{a}_j$ . Sorting all the observation Eqs. (6) by the source index i and collecting them in one matrix we get a non-square block angular matrix (see Björck 1996):

$\begin{displaymath} \left[\begin{array}{ccccc} \vec{S}_{i=1} & 0 & \cdots & 0 ... ...y}\right]\;\; \Leftrightarrow \; \; \vec{M}\vec{x} = \vec{h} , \end{displaymath}$

(7)

with n the number of primary sources (10⁸). The matrices $\vec{S}_i$ , $\vec{A}_i$ and vector $\vec{h}_{si}$ are the vertical concatenations of, respectively, $\vec{S}_{l}$ , $\vec{A}_{l}$ , and h_l for all observations l referring to source i; $\vec{x}_a$ is the vector of all the attitude parameter displacements $\vec{x}_{aj}$ .

In Eqs. (6)-(7) and all following equations, it is important to note our (slightly unconventional) use of indices in the subscripts. Since index l is exclusively used for the observations, and i, j respectively for the sources and attitude time segments, $\vec{S}_{l}$ and $\vec{S}_i$ signify different matrices, even when the indices l and i happen to have the same numerical value. $\vec{S}_{l}$ is the $1\times 5$ matrix containing the partial derivatives of f_l with respect to the five astrometric parameters of source number i(l), multiplied by the square root of the weight of observation t_l. Suppose that there are o_i observations of source i. $\vec{S}_i$ is then the $o_i\times 5$ matrix obtained by stacking $\vec{S}_{l}$ for every l such that i(l) = i. A similar distinction is made between $\vec{A}_{l}$ , referring to observation l, and $\vec{A}_i$ , obtained by stacking all $\vec{A}_{l}$ for which i(l)=i.

For example, consider the source i=1 with o₁=3 observations for l=7, 22 and 3999, each occurring at a different attitude interval with index j=11, 123 and 200, respectively. Then

$\begin{displaymath}\vec{S}_{i=1}= \left[ \begin{array}{c} \vec{S}_{l=7} \\ \vec... ...c} h_{l=7} \\ h_{l=22} \\ h_{l=3999} \\ \end{array}\right]. \end{displaymath}$

(8)

and

$\begin{displaymath}\vec{A}_{i=1}= \left[ \begin{array}{ccccccc} \cdots & (j\!=\!... ...} & \cdots & \vec{A}_{l=3999} & \cdots \\ \end{array}\right], \end{displaymath}$

(9)

where the column indices of the three non-zero columns are shown in the top row. Note that $\vec{A}_{i=1}$ in Eq. (7) is multiplied by $\vec{x}_a$ , which is the vertical concatenation of $\vec{x}_{aj}$ for the different attitude time segments j. The first row in Eq. (7) therefore only involves the attitude unknowns $\vec{x}_{aj=11}$ , $\vec{x}_{aj=123}$ and $\vec{x}_{aj=200}$ .

2.6 Normal equations

The system (7) is over-determined: there are more equations than unknowns. Due to measurement errors, there does not exist a solution that simultaneously satisfies all the equations. However the problem becomes mathematically well posed when we try to minimize the norm of the post-fit residual vector,

$\begin{displaymath} \min_{\vec{x}}\; \left\vert\left\vert\vec{h}-\vec{M}\vec{x}\right\vert \right\vert~ . \end{displaymath}$

(10)

This is the ordinary least-squares problem, which is classically solved by forming the normal equations

$\begin{displaymath} \vec{M}{'\!}\vec{M}\vec{x} = \vec{M}{'\!}\vec{h} ~ , \end{displaymath}$

(11)

or

$\begin{displaymath} \left[\begin{array}{ccccc} \vec{S}_1{'\!}\vec{S}_1 & 0 & \... ...] \sum_i \vec{A}_i{'\!}\vec{h}_{si} \\ \end{array}\right] , \end{displaymath}$

(12)

where the prime (') denotes matrix transpose and the numerical subscripts refer to the source index i. The full normal equations matrix $\vec{N}=\vec{M}{'\!}\vec{M}$ is symmetric of size 5n+m (equal to the total number of unknowns), with n the number of primary sources and $m=\dim(\vec{a})$ the number of attitude parameters. It has the doubly bordered block diagonal form (Björck 1996, Sect. 6.3.1) with block size 5 and border width m.

Thanks to the scanning law of Gaia, and provided that a sufficient number of sources are observed a sufficient number of times over the mission, it is found that each of the diagonal sub-matrices $\vec{S}_i{'\!}\vec{S}_i$ and $\sum_i\vec{A}_i{'\!}\vec{A}_i$ are positive-definite. Yet the complete system (12) is in principle singular (although rounding errors will in practice make it non-singular): it is expected to be positive-semidefinite with rank 5n+m-6, owing to the circumstance that all the observations are invariant with respect to the choice of celestial reference system. The 6-dimensional nullspace is in fact well known and corresponds to the undefined orientation and spin of the reference system in which both the source parameters and the attitude are expressed. This singularity is therefore of a benign nature and the associated numerical difficulties can easily be overcome (Lindegren et al., in prep.). For simplicity we subsequently ignore this particular feature of the problem and assume that the normal matrix $\vec{N}$ is positive-definite.

2.7 Sparseness structure

In this section we investigate the sparseness structure of the observation matrix $\vec{M}$ and the normal matrix $\vec{N}$ . In linear algebra the sparseness notion refers to matrices or systems of equations where only a (very small) fraction of the elements have non-zero values. We use $\eta(\vec{X})$ to denote the fill factor of the matrix $\vec{X}$ , i.e., the fraction of non-zero elements. The sparseness structure of the present equations is directly related to the design of Gaia: two telescopes separated by a large fixed angle, orthogonal to a spin axis, and a scanning law that has been optimized to maximize the sky coverage within given technology constraints, leading to a satellite spin period of 6 hr with a precession rate of approximately $4^\circ~\mbox{day}^{-1}$ (see Lindegren et al. 2008).

With $o_i=\dim(\vec{t}_i)$ denoting the number of observations of source i and $m=\dim(\vec{a})$ the number of attitude parameters, the dimensions (rows $~\times~$ columns) of the various sub-matrices in Eq. (7) are as follows:

$\begin{displaymath}\left. \begin{array}{lllll} \vec{S}_i~(o_i\times 5) && \vec{... ...}~(5\times 1) && \vec{x}_a~(m\times 1) \end{array}\right\} ~ , \end{displaymath}$

(13)

$\vec{S}_i$ are full matrices, while the $\vec{A}_i$ are very sparse, with element $[\vec{A}_i]_{\alpha\beta}\neq 0$ only if the $\alpha$ th observation of source i is linked to the $\beta$ th attitude parameter. As discussed in Sect. 2.5, a given observation is linked to 3M consecutive attitude parameters, where M is the order of the spline; thus $\eta(\vec{A}_i)=3M/m$ . For the total observation matrix we have $\eta(\vec{M})=(5+3M)/(5n+m)$ . Assuming, as in Sect. 2.4, n=10⁸, $m=2\times 10^7$ and M=4, we find $\eta(\vec{A}_i)\simeq 6\times 10^{-7}$ and $\eta(\vec{M})\simeq 3\times 10^{-8}$ .

For the normal equations (12) we have the dimensions:

$\begin{displaymath}\left.\begin{array}{lllll} \vec{S}_i{'\!}\vec{S}_i~(5\times ... ...\vec{A}_i{'\!}\vec{h}_{si}~(m\times 1) \end{array}\right\} ~ . \end{displaymath}$

(14)

$\vec{S}_i{'\!}\vec{S}_i$ is full, while the $\beta$ th column of $\vec{S}_i{'\!}\vec{A}_i$ is non-zero if at least one observation of source i is linked to the $\beta$ th attitude parameter. Typically, each field-of-view transit consists of nine CCD observations, spanning a time interval of $T\simeq 40$ s and thus linking on average $3(T/\Delta\tau+M)\simeq 18$ consecutive attitude parameters (M=4 is the order of the attitude spline and $\Delta\tau\simeq 20$ s the interval between knots). Since there are on average 86 field transits per source over the mission, we have in the mean $\eta(\vec{S}_i{'\!}\vec{A}_i)\simeq 18\times 86/m\simeq 8\times 10^{-5}$ . $\sum_i\vec{A}_i{'\!}\vec{A}_i$ is symmetric with non-zero elements only in a band along the diagonal; the half-bandwidth (maximum number of non-zero elements to the left or right of the diagonal) is 3M-1, but actually the non-zero part consists of $(3\times 3)$ -submatrices on the diagonal plus M-1 of them on each side of the diagonal. Thus $\eta(\sum_i\vec{A}_i{'\!}\vec{A}_i)\simeq 3(2M-1)/m \simeq 1\times 10^{-6}$ . For the full normal matrix we have $\eta(\vec{N})\simeq 310/n\simeq 3\times 10^{-6}$ .

3 Direct solution method

In this section we consider the possibility of computing a direct (i.e., non-iterative and algebraically exact) solution to the normal Eqs. (12). Already in the early phases of the Hipparcos project it was concluded that a direct solution of the corresponding (much smaller) problem would not be feasible, and the so-called three-step procedure was invented as a practical, albeit approximate workaround (Sect. 5.3). Since then, the available storage and computing power have increased by many orders of magnitude and it is not obvious that even the much larger Gaia problem is intractable by a direct method. However, as we shall see below, it appears that the direct method is still quite unfeasible, although it may be difficult to prove such an assertion in full mathematical rigour.

Let us start with a few general observations. The solution of a non-sparse system of normal equations with N unknowns in general requires a minimum of about N³/6 floating-point operations , where an operation typically involves one multiplication (or division) and one addition, plus some subscripting (Golub & van Loan 1996). For a sparse matrix there is no general formula, since the required effort depends critically on the detailed sparseness structure (i.e., the connectivity amongst the unknowns), the ordering of the unknowns, and the chosen solution algorithm. A lower bound is given by $\simeq\eta^2N^3/8$ , which applies to a banded matrix (George & Liu 1981). Considering the normal matrix $\vec{N}$ in Eq. (12) with $N=5n+m\simeq 5\times 10^8$ and $\eta(\vec{N})=3\times10^{-6}$ this gives operation counts from 10¹⁴ to a few times 10²⁵ flop. It is envisaged that the astrometric solution for Gaia will run on a computing system with a performance of about 10 TFLOPS, or 10¹³ floating-point operations per second (Lammers et al. 2009). Theoretically, this gives a computing time of tens of seconds for the lower bound, and tens of thousands of years for the upper bound, i.e., ranging from clearly feasible to clearly unfeasible. In order to refine the estimate we need to specify the solution method more precisely and take a closer look at the sparseness structure. In this section we consider a solution based on the elimination of the source parameters, which seems the most natural approach for the present problem. In Sect. 5 we briefly consider some possible alternative approaches to the direct solution.

3.1 Reduced normal matrix

A standard way to handle normal equations with the block-diagonal-bordered structure of Eq. (12) is to successively eliminate the unknowns along the block-diagonal (in our case the source parameters), leaving us with a ``reduced'' normal equations system for the remaining unknowns (in our case the attitude parameters). The gain is a huge reduction in the size of the system that has to be solved, at the expense of a much denser reduced matrix.

A straightforward computation shows that the solution of Eq. (12) can be accomplished by first solving the reduced normal equations for the attitude parameters,

$\begin{displaymath} \vec{R}_a \vec{x}_a = \sum_{i=1}^n \left(\vec{A}_i{'\!}\vec{... ...{'\!}\vec{S}_i\right)^{-1}\vec{S}_i{'\!}\vec{h}_{si}\right)~ , \end{displaymath}$

(15)

where

$\begin{displaymath} \vec{R}_a = \sum_{i=1}^n\left(\vec{A}_i{'\!}\vec{A}_i-\vec{A... ...\vec{S}_i{'\!}\vec{S}_i\right)^{-1}\vec{S}_i{'\!}A_i\right)~ , \end{displaymath}$

(16)

is the reduced normal matrix, and then forwarding the solution $\vec{x}_a$ to solve all the source equations

$\begin{displaymath} \vec{x}_{si} = \left(\vec{S}_i{'\!}\vec{S}_i\right)^{-1} \le... ..._i{'\!}\vec{A}_i\vec{x}_a\right)~ , \qquad i=1,~2,~\dots,~n ~. \end{displaymath}$

(17)

This well-known computational trick, tantamount to a block-wise gaussian elimination, was used e.g. for the Hipparcos sphere solution (see ESA 1997, Vol. 3, p. 208) and is also used for the one-day astrometric solution as part of the Gaia first look processing (see Bombrun 2008a; Jordan et al. 2009; Bernstein et al. 2005). The initial problem has been reduced to a smaller one. For the global space astrometry problem, the complexity essentially consists of solving the reduced normal equations (15), which involves the sparse symmetric positive-definite matrix $\vec{R}_a$ of size $m\times m$ , with $m\simeq 2\times 10^7$ for Gaia.

3.2 Complexity of the Cholesky factorization

In order to solve Eq. (15), we investigate the Cholesky factorization of the reduced normal matrix $\vec{R}_a$ . The Cholesky factorization is a useful and well-known method to solve linear equations involving a positive-definite matrix, see Appendix B. Moreover, the complexity of this factorization, which is strongly related to the sparseness structure of the matrix to be factored, can easily be computed. In Appendix A we present the sparseness structure of the reduced normal matrix. As we are here only concerned with the complexity of the factorization, not by the actual numerical values, we use symbolic computation. For sparse matrices this means that the indices of non-zero elements occurring during the computation are traced, which enables us to compute the number of floating-point operations required for the factorization, as well as the sparsity of the resulting factor.

Even using symbolic computation, $\vec{R}_a$ is far too large to be easily studied in full. Instead we consider sequences of increasingly larger submatrices that allow extrapolation to the full-size problem. A principal submatrix of $\vec{R}_a$ is obtained by deleting a certain subset of the rows and the corresponding columns. Since $\vec{R}_a$ is symmetric and positive-definite, that is also true of all its principal submatrices (Stewart 1998).

As explained in Sect. 2.4, the attitude parameters are grouped in sub-vectors $\vec{a}_j$ corresponding to non-overlapping time segments. Deleting the rows and columns in $\vec{R}_a$ for a certain time segment is clearly equivalent to excluding all observations in that time segment. Conversely, by considering only the observations in selected time segments, we obtain a principal submatrix of $\vec{R}_a$ .

$\begin{figure} \par\includegraphics[width=9cm,clip]{13503fg1} \end{figure}$	Figure 1: The fill factor $\eta$ of the reduced normal matrix in (15), and of its Cholesky factor, as function of the number of spins (6 h intervals) included in the solution. Three sequences of increasing number of spins are considered, labelled set 1, 3 and 12, as explained in the text.
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Using the small-scale simulation software AGISLab (Holl et al. 2009), the structures of various principal submatrices of $\vec{R}_a$ were computed for a problem with one million primary sources. Each complete rotation (spin) of the satellite constitutes an attitude time segment of 6 h, which is divided into 1000 knot intervals of $\Delta\tau=21.6$ s. For each pair of knot intervals, $(\ell,\ell')$ , where $\ell$ and $\ell'$ may belong to different time segments (spins), AGISLab provides the number of sources observed in both intervals. If this number is not zero, then the $3\times 3$ block elements of the principal submatrix with $\vert\ell-\ell'\vert\le 2M$ will be non-zero, where M=4 is the order of the attitude spline (Sect. 2.5).

We consider three sequences of principal submatrices of $\vec{R}_a$ , labelled set 1, 3 and 12, each covering up to 400 spins (j):

$\begin{displaymath}\begin{array}{lllr} \textrm{set 1:} & j &=0,~1,~2,~3,~\dots,... ...36,~\dots,~4788 & \textrm{($\simeq 1200$ ~days)}. \end{array} \end{displaymath}$

The number of spins included is successively increased to study the sparsity structure of the resulting principal submatrix. Symbolic Cholesky factorization was performed after a reordering of the attitude unknowns. We used the minimum degree algorithm and the reordering software Metis (Karypis & Kumar 1998), which implements one of the most efficient reordering algorithms. We also tried the reverse Cuthill-McKee algorithm (George & Liu 1981) but it is clearly less efficient than the minimum degree algorithm in terms of the sparseness of the resulting Cholesky factor.

$\begin{figure} \par\includegraphics[width=9cm,clip]{13503fg2} \end{figure}$	Figure 2: Same as Fig. 1, but showing the complexity of reduced normal equations in terms of the number of floating-point operations (flop) needed to compute the Cholesky factors, using the minimum degree reordering algorithm and Metis software.
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Figure 1 shows the fill factors $\eta$ for the different submatrices, and for the Cholesky factors after reordering using the minimum degree algorithm, as functions of the total number of spins considered. The full problem (5 yr) corresponds to about 7300 spins. As shown by the lower set of curves in Fig. 1, the fill factor for the principal submatrices of $\vec{R}_a$ decreases with the number of spin rotations, although it appears to level out at a few times 10^-4. By contrast, for the corresponding Cholesky factors the fill factor quickly approaches 1 (the upper set of curves), implying that sparse matrix algorithms (including reordering) tend to be useless when more than a few hundred spins are included.

Figure 2 shows the complexity of the solution in terms of the number of floating-point operations needed to compute the Cholesky factors, taking into account the sparseness. Also shown (by the upper, straight line) is the complexity of the Cholesky factorization of the corresponding full matrices. It is clear that the complexity of the sparse submatrices tends towards the upper bound for the full matrices.

Roughly speaking, the connectivity between the observations increases when more and more spins are included. Even if the submatrices tend to be sparser, it is not possible to break the increasing connectivity by reordering of the unknowns, at least not with the commonly used reordering algorithms. Hence, once Gaia has covered the whole sky, the Cholesky factor of the reduced normal matrix will be almost full and as difficult to compute as for a full matrix.

Extrapolating to the full size of the problem (7300 spins), we find that a direct solution of the reduced normal equations (15) will require about $1.3\times 10^{21}$ flop, the operation count for the Cholesky decomposition of a full matrix of dimension $m\times m$ , viz. m³/6.

As explained in the introduction, we have deliberately ignored the calibration and global unknowns of the full Gaia adjustment problem. Both groups of unknowns will add more complexity and more fill-in. Similarly we have not discussed the numerical stability of a direct solution, and it is possible that a more refined numerical method, requiring an even greater computational effort than the Cholesky factorization, may be needed to compute an accurate solution. Moreover one should not forget about the complexity of storage. An upper triangular matrix with the dimension of the reduced normal matrix will require around 2 million Gigabytes. Operating efficiently on such a large matrix is certainly a very difficult problem in itself.

4 Iterative solution method

In this section we present the currently implemented iterative solution, AGIS (Lindegren et al., in prep.; O'Mullane et al., in prep.), adopting the simplifications of the present paper and comparing its complexity to that of the direct solution. The solution method outlined below belongs to a large and important class of iterative algorithms for the solution of sparse linear equations, known as Krylov subspace methods (van der Vorst 2003). The class includes well-known methods such as conjugate gradient which can be used for AGIS (Bombrun et al. in prep). The basic AGIS scheme described above is equivalent to the simplest of all Krylov subspace methods, appropriately termed ``simple iteration''.

4.1 The ``simple iterative'' scheme

In the present context, the iterative algorithm originally adopted for the Gaia astrometric solution (AGIS) can be described as follows. As in Eq. (11), let $\vec{N}\vec{x}=\vec{b}$ be the linear system of equations to be solved, where $\vec{N}$ is symmetric. This system has the property that the matrix-vector product $\vec{N}\vec{y}$ can be calculated rather easily, for arbitrary $\vec{y}$ , while the direct solution of $\vec{N}\vec{x}=\vec{b}$ is very difficult. Now let $\vec{K}$ be some square matrix (``preconditioner'') of the same size as $\vec{N}$ , which in some sense approximates $\vec{N}$ , but has the property that the system $\vec{K}\vec{y}=\vec{z}$ can easily be solved for arbitrary $\vec{z}$ . Writing $\vec{N}=\vec{K}-\vec{D}$ (where $\vec{D}$ is sometimes called the ``defect'' matrix) the original system becomes $\vec{K}\vec{x}-\vec{D}\vec{x}=\vec{b}$ , which naturally leads to the iteration formula

$\begin{displaymath} \vec{x}^{(k+1)}=\vec{K}^{-1}(\vec{b}+\vec{D}\vec{x}^{(k)}) ~ , \end{displaymath}$

(18)

for successive iterations $k=0,~1,~2,~\dots$ A possible starting approximation is $\vec{x}^{(0)}=\vec{0}$ . Substituting $\vec{D}=\vec{K}-\vec{N}$ in Eq. (18) leads to the alternative expression

$\begin{displaymath} \vec{x}^{(k+1)}=\vec{x}^{(k)}+\vec{K}^{-1}\vec{r}^{(k)} ~ , \end{displaymath}$

(19)

where

$\begin{displaymath} \vec{r}^{(k)}=\vec{b}-\vec{N}\vec{x}^{(k)} ~ , \end{displaymath}$

(20)

is the residual vector in the kth iteration. With $\vec{e}^{(k)}=\vec{x}^{(k)} - \vec{N}^{-1}\vec{b}$ denoting the error of the kth iteration, $\vec{r}^{(k)}=-\vec{N}\vec{e}^{(k)}$ and we find from Eqs. (18)

$\begin{displaymath} \vec{e}^{(k+1)} = \vec{e}^{(k)} + \vec{K}^{-1}\vec{r}^{(k)} ... ...D}\vec{e}^{(k)} = (\vec{K}^{-1}\vec{D})^{k+1}\vec{e}^{(0)} ~ . \end{displaymath}$

(21)

The algorithm converges to the correct solution if $\vert\vec{e}^{(k)}\vert\rightarrow 0$ as $k\rightarrow\infty$ . Equation (21) shows that this is the case if and only if the spectral radius of the so-called iteration matrix $\vec{K}^{-1}\vec{D}$ is strictly less than one. For the residual vector we similarly have

$\begin{displaymath} \vec{r}^{(k+1)} = \vec{r}^{(k)} - \vec{N}\vec{K}^{-1}\vec{r}... ...1}\vec{r}^{(k)} = (\vec{D}\vec{K}^{-1})^{k+1}\vec{r}^{(0)} ~ . \end{displaymath}$

(22)

The spectral radius of $\vec{D}\vec{K}^{-1}$ is the same as that of the iteration matrix, so the residual vector goes to zero at asymptotically the same rate as the errors.

The choice of preconditioner has a profound influence on the rate of convergence in the simple iteration scheme. In analogy with classical iteration schemes, using the diagonal (or block-diagonal) part of the $\vec{N}$ as preconditioner may be referred to as a Jacobi iteration scheme, while the lower (block-) triangular part of $\vec{N}$ is referred to as a Gauss-Seidel iteration scheme. As shown below, AGIS is close to the classical Gauss-Seidel scheme known to be a converging residual-reducing scheme (Björck 1996, Sect. 7.3.2).

4.2 Implementation in AGIS

The full normal Eqs. (12) can be written as

$\begin{displaymath} \left[\begin{array}{cc} \vec{N}_{ss} & \vec{N}_{sa} \\ [3p... ...y}{c} \vec{b}_s \\ [3pt] \vec{b}_a \\ \end{array} \right], \end{displaymath}$

(23)

where $\vec{N}_{ss}$ is the $5n\times 5n$ upper-left submatrix of $\vec{N}$ , $\vec{N}_{sa}=\vec{N}_{as}'$ is of dimension $5n\times m$ , $\vec{N}_{aa}$ is $m\times m$ , and $\vec{x}$ and $\vec{b}$ are similarly split in a source part (of length 5n) and an attitude part (of length m). It is important to note that the submatrices $\vec{N}_{ss}$ and $\vec{N}_{aa}$ , although large, have a simple block-diagonal or band-diagonal structure, which makes it simple to solve systems involving only these matrices. The complication comes from the off-diagonal blocks $\vec{N}_{sa}$ and $\vec{N}_{as}$ , which couple the source and attitude parameters.

A natural choice to split the normals is therefore the following Gauss-Seidel scheme:

$\begin{displaymath} \vec{K} = \left[ \begin{array}{cc} \vec{N}_{ss} & \vec{\va... ...vec{\varnothing} & \vec{\varnothing} \\ \end{array}\right] , \end{displaymath}$

(24)

where each $\vec{\varnothing}$ stands for a zero matrix of the appropriate dimensions. With this preconditioner, the update equation (19), split into its source and attitude parts, becomes

$\displaystyle \vec{x}_s^{(k+1)}$	=	$\displaystyle \vec{x}_s^{(k)} + \vec{\delta}_s^{(k)}~ , ~\textrm{with}~~\vec{\delta}_s^{(k)} = \vec{N}_{ss}^{-1}\vec{r}_s^{(k)}~ ,$	(25)
$\displaystyle \vec{x}_a^{(k+1)}$	=	$\displaystyle \vec{x}_a^{(k)} + \vec{\delta}_a^{(k)}~ , ~\textrm{with}~~\vec{\d... ...a^{(k)}=\vec{N}_{aa}^{-1} (\vec{r}_a^{(k)}-\vec{N}_{as}\vec{\delta}_s^{(k)})~ ,$	(26)

where $\vec{r}_s^{(k)}$ and $\vec{r}_a^{(k)}$ are the source and attitude parts of the residual vector in iteration k. From Eq. (19) it can be seen that $\vec{r}_a^{(k)}-\vec{F}'\vec{\Delta x}_s^{(k)}$ is the attitude part of the residual vector computed with the updated source parameters $\vec{x}_s^{(k+1)}$ and current attitude parameters $\vec{x}_a^{(k)}$ . Each iteration can therefore be implemented by means of the following two steps: (i) Compute the source part of the residual vector, $\vec{r}_s^{(k)}$ , and update the source parameters according to Eq. (25). (ii) Using the updated source parameters, recalculate the attitude part of the residual vector, equivalent to $\vec{r}_a^{(k)}-\vec{F}'\vec{\Delta x}_s^{(k)}$ , and update the attitude parameters according to Eq. (26). Note that the coupling matrix $\vec{F}$ is not explicitly needed and that the derivatives used to set the observation Eq. (5) are indeed recomputed at each iteration.

The two steps (i) and (ii) exactly correspond to the source update and attitude update blocks of the original AGIS scheme, which therefore effectively implements the simple iteration with Gauss-Seidel preconditioner. The scheme is easily parallelizable, resulting in efficient and scalable software. The source and the attitude equations can even be accumulated in parallel, successively solved for each source, whereupon the updated source parameters are passed to the attitude equations. When all the sources have thus been processed, the attitude equations are ready to be solved.

4.3 Complexity of the iterative solution

In Sect. 3 we did not consider the complexity of computing the normal matrix and the reduced normal matrix. Indeed these computations are negligible compared with the complexity of solving the reduced normal matrix. This is not the case for the iterative method. For the present comparison, let us assume that the calculation of a single observation equation (i.e., of the observation residual and 5+3M=17partial derivatives) requires some p=10⁴ flop. Assuming, as in Sect. 2, n=10⁸ sources, $o=8\times 10^{10}$ observations, and $m=2\times 10^7$ attitude parameters, the complexity of building the source part of the normal equations (25) is around $(p+20)o\simeq 8\times10^{14}$ flop, while its solution and updating of the source parameters only requires some $20n\simeq 2\times10^{9}$ flop. For the attitude part, assuming that the residuals and partial derivatives are calculated afresh (as is the case in AGIS), building the normal equations in (26) requires around $(p+90)o\simeq 8\times10^{14}$ flop and another $(3M)^2m/6\simeq 5\times10^{8}$ flop for its solution. Thus the total complexity per iteration is of the order of $2\times 10^{15}$ , by far dominated by the setting up of the observation equations.

We have seen that the complexity of one iteration of the iterative method is much smaller than the complexity of solving the full system. An additional question that needs to be addressed then is the number of iterations needed in order to obtain a good approximation to the solution of the least squares problem. It is a drawback of any iterative method over the direct method that a convergence criterion must be set up, and there is in principle no way to know in advance how many iterations are needed to satisfy the criterion. For the present application, both the full-scale AGIS implementation (Lindegren et al., in prep.; O'Mullane et al., in prep.) and small-scale AGISLab experiments (Holl et al. 2009) indicate that of the order of 100 simple iterations are required to reach parameter updates that are negligible to the numerical precision of the 64-bit arithmetics. This can be improved by a moderate factor (2 to 4) by the use of slightly more complex iteration schemes, including conjugate gradients (Bombrun et al., in prep.). These schemes are not elaborated here since they do not so much affect the complexity of each iteration. The total complexity of the iterative solution is therefore of the order of 10¹⁷ flop, or a factor ${\sim}10^4$ smaller than the direct solution.

5 Some alternative approaches to the direct solution

The scheme described in Sect. 3 is not the only possible way to obtain a direct solution, and in this section we briefly consider some alternative approaches.

5.1 Elimination of attitude parameters

As an alternative to eliminating the source parameters, we may consider instead the elimination of the attitude parameters, one attitude segment (j) at a time. This results in a reduced matrix $\vec{R}_s$ for the source parameters, of size $5n\times 5n$ . It consists of submatrices of size $5\times 5$ , such that the (i,i')th submatrix is associated with a pair of primary sources i and i'. The minimum fill factor can easily be estimated from the geometry of the observations, submatrix (i,i') being non-zero if and only if the two sources i and i'are observed in the same attitude interval at some point of the mission. From the size of the fields of view of Gaia and the number of field transits per source (cf. Sect. 2.4) it is found that $\eta(\vec{R}_s)\sim 10^{-3}$ , which is similar to the fill factor found for the reduced attitude matrix $\vec{R}_a$ (Fig. 1). However, since for Gaia $\dim(\vec{R}_s)=5n\simeq 5\times 10^8$ , while $\dim(\vec{R}_a)=m\simeq 2\times 10^7$ , the storage of $\vec{R}_s$ requires 2-3 orders of magnitude more memory than $\vec{R}_s$ . We have not studied the complexity of the Cholesky factorization of $\vec{R}_s$ , but it seems likely that it is at least as large as that of $\vec{R}_a$ , and possibly several orders of magnitude larger. This is based on the observations that the scanning law does not admit any natural way of ordering the sources in order to reduce the bandwidth of $\vec{R}_s$ .

Given that $5n\gg m$ for Gaia, elimination of the attitude parameters thus appears to be much less advantageous than the scheme described in Sect. 3, although it may potentially be interesting for other missions involving a much smaller number of sources.

5.2 Orthogonal transformation of the observation equations

Forming normal equations, that are then solved by means of a Cholesky factorization, is generally speaking the most efficient direct way of solving the linear least-squares problem (10), both in terms of storage and number of floating-point operations required. Numerically, however, it is less stable and less accurate than some other methods that do not form and operate on the normal equations. The basic reason for this is that the condition number of the normal equations matrix is the square of that of the observation equations matrix, that is $\kappa(\vec{M}'\!\vec{M})=\kappa(\vec{M})^2$ . $\log_{10}\kappa$ is approximately the number of significant decimal digits lost in computing the solution with finite-precision arithmetics. Thus, a least-squares problem with a moderately high condition number, say $\kappa(\vec{M})\sim 10^8$ , could give a virtually useless solution in double-precision arithmetic ( $\simeq$ 16 significant digits) if normal equations are used, while a solution of the same observation equations using orthogonal transformation could very well be viable. For this and related reasons, orthogonal transformation methods are often strongly recommended for solving least-squares problems. Compared with the normal equations approach, the increase in the number of floating-point operations need not be very high. For example, when Householder transformations are applied to solve a non-sparse problem with many more observations than unknowns, the increase in the operation counts is typically around a factor 2 (Björck 1996, Sect. 2.4).

Fortunately, the Gaia astrometric problem is well-conditioned by design, so the superior numerical properties of orthogonal transformation methods are not necessarily a strong argument in their favour. A more important argument could be that the observation equations have a vastly simpler structure than the normal equations. If this can somehow be taken advantage of in the solution process, it could potentially lead to significant savings in terms of storage and flop. The standard approach is the QR factorization, which uses a sequence of orthogonal transformations to decompose the observation equations matrix as $\vec{M}=\vec{Q}\vec{U}$ , where $\vec{Q}$ is orthogonal and $\vec{U}$ is upper triangular. The application of the QR factorization to a block angular matrix as in Eq. (7) is described for example in Sect. 6.3 of Björck (1996). Briefly, for each source (i) the observation Eqs. (6), here summarized by $\left[\vec{S}_i~\vec{A}_i~\vec{h}_{si}\right]$ , are first reduced to upper triangular form by the orthogonal transformation

$\begin{displaymath} \vec{Q}_i' \left[\begin{array}{ccc} \vec{S}_i & \vec{A}_i &... ...ec{\varnothing} & \vec{T}_i & \vec{d}_{i} \end{array}\right] , \end{displaymath}$

(27)

where $\vec{U}_i$ and $\vec{T}_i$ are upper triangular. In parallel with this, the equations $\vec{T}_i \vec{x}_a = \vec{d}_i$ , here summarized by $\left[\vec{T}_i~\vec{d}_i\right]$ , are successively brought into upper triangular form by a sequence of orthogonal transformations, finally yielding the system

$\begin{displaymath} \vec{Q}_a' \left[\begin{array}{cc} \vec{T}_1 & \vec{d}_1 \\ ... ..._a\\ [3mm] \vec{\varnothing} & \vec{d}_a \end{array} \right] . \end{displaymath}$

(28)

The original least-squares problem is then equivalent to solving the system for the attitude unknowns, $\vec{U}_a \vec{x}_a=\vec{c}_a$ , and obtaining the source unknowns by back-substitution. It is easy to see that the triangular matrix $\vec{U}_a$ obtained at the end of this process is mathematically identical to the Cholesky factor of the reduced matrix $\vec{R}_a$ in Eq. (15), i.e., $\vec{U}_a'\vec{U}_a=\vec{R}_a$ . From the analysis in Sect. 3.2 we therefore conclude that $\vec{U}_a$ is essentially full and that the number of operations needed to compute it must be at least as large as for the Cholesky factorization of $\vec{R}_a$ . Thus, in terms of storage and complexity, the approach using QR factorization of the observation equations is not an improvement over the normal equations approach.

5.3 Hipparcos-type decomposition

For completeness we mention here also the astrometric solution method adopted for the original reduction of the Hipparcos data by the two data analysis consortia, FAST (Kovalevsky et al. 1992) and NDAC (Lindegren et al. 1992). The astrometric solution for Hipparcos involved about $o\simeq 10^8$ observations of $n\simeq 10^5$ sources (stars), and $m\simeq 10^7$ attitude parameters. Already in the very early mission studies (in the 1970's) it was realized that the complexity of the astrometric solution would be daunting; for example, a comparison with the then recently developed photographic plate overlap reduction technique (Jefferys 1979; Eichhorn 1960; Jefferys 1963) gave estimates of ${\sim}10^{16}$ floating-point operations (flop). This basically assumed a solution based on the approach in Sect. 5.1, viz., that the attitude unknowns were first eliminated, leading to a nearly full, reduced normal equations matrix $\vec{R}_s$ of dimension $5n\times 5n$ . Its Cholesky decomposition would require $(5n)^3/6\simeq 2\times 10^{16}$ flop.

The so-called three-step method was proposed by Lindegren in 1976 (unpublished) as a practical way to achieve a solution with only marginal degradation compared with a theoretically optimum solution (ESA 1997, Vol. 3, Sect. 4.1). The three steps are:

1.: The ``great-circle reduction'' uses observations in a few consecutive spins to solve the one-dimensional positions (``abscissae'') of the sources along a reference great circle, together with the relevant attitude and calibration parameters. The origin (zero point) of the abscissae along the reference great circle is arbitrary in each such solution.
2.: The ``sphere solution'' uses all the abscissae from Step 1 as ``observations'' for a least-squares solution of the abscissa zero points. The observation equations also involve the five astrometric parameters per source, but they can be eliminated successively (analogous to the calculation of $\vec{R}_a$ in Sect. 3.1). The resulting system for the abscissa zero points is nearly full, and can be solved by standard methods.
3.: The ``astrometric parameter determination'' is a back-substitution of the abscissa zero points from Step 2 into the observation equations for the individual sources. The resulting least-squares systems, analogous to Eq. (17), were solved one source at a time to give the source parameters.

Different variants of this scheme were adopted by both FAST and NDAC for their astrometric solutions.

The three-step method appears simple and logical in view of the scanning law and basic one-dimensionality of the measurements (both for Hipparcos and Gaia). Moreover, it has been shown to work in practice for Hipparcos. It may therefore be of some interest to examine the approximations involved in it, and why it has not been adopted for Gaia.

The use of one-dimensional abscissae as an intermediate step is clearly an approximation in the sense that the information contained in the perpendicular coordinate (``ordinate'') is ignored. Moreover, since the instantaneous scanning circle can be inclined with respect to the reference great circle by up to a few degrees, initial errors in the source ordinates, and the corresponding attitude errors, effectively add some (much smaller) along-scan observation errors, due to their projection onto the instantaneous scanning circle. This makes it necessary to iterate the three-step procedure at least a few times, as was actually done for the Hipparcos reductions.

However, the restriction of the intermediate data to one-dimensional abscissae is not a fundamental one. Indeed, it is possible to use two-dimensional positions (albeit with a highly anisotropic precision), as in the so-called Ring Solution, also called the one day astronomical solution, of the Gaia First-Look Processing (Bombrun 2008a; Jordan et al. 2009; Bernstein et al. 2005), or even five-dimensional data, using the full parametrization of the primary sources, by a slight generalization of the method.

The abscissae in the Hipparcos great-circle solution, and the two-dimensional positions in the Ring Solution, are somewhat akin to the ``normal places'' (Normalorte in German) often encountered especially in older astronomical literature, e.g., for least-squares determination of the orbits of asteroids, comets and visual binaries. The basic idea is that multiple observations, usually obtained in a limited time interval, can be grouped together, and subsequently treated as a single observation with the combined weight of the individual observations. When considering a single coordinate (e.g., declination, $\delta$ ) the method amounts to computing a weighted mean of a group of residuals $(O{-}C)_\delta$ with respect to some reference orbit, and then treating this mean residual as an observation referring to the weighted mean time of observation within the group (von Oppolzer 1880, p. 371). This can greatly reduce the amount of computation needed to process long series of observations, and the method of normal places was understandably popular before the advent of electronic computers. In the present context, a generalization of the method might be relevant for reducing the amount of computation needed to obtain the Gaia astrometric solution. The method is conveniently discussed in terms of Ring Solutions (roughly corresponding to Step 1 above) producing multiple two- or higher-dimensional normal places for each source, and a single Ring-to-Sphere solution putting all the normal places on a common reference system (roughly corresponding to a combination of Step 2 and 3 above).

A closer examination of the procedure reveals several weaknesses. They are all related to the circumstance that each Ring Solution must use only observations in a limited time interval (hours to days). One weakness concerns the availability of positional information for the across-scan attitude determination. Normally this information would come primarily from scans making a large angle to the present scan, i.e., from other time intervals. Restricting the processing to data within a limited time interval will always entail a loss of positional information for the attitude determination. Another weakness is that instrument parameters that are constant on time scales longer than a Ring Solution cannot easily be correctly treated in the Ring Solutions. Further weaknesses are the arbitrariness of the division of the time line into Ring Solutions, and the absence of continuity at the times of division. Obviously, all these weaknesses can be eliminated by extending the Ring Solution to encompass the whole mission; this is however equivalent to the previously studied direct solution. Thus it appears that decomposition methods of this kind are always sub-optimal, to some extent arbitrary, and in any case requires iteration to propagate information back from the Ring-to-Sphere solution to the Ring Solutions. Although a viable solution along these lines could no doubt be found, it is difficult to see any real advantages over an iterative solution of the rigorous normal equations, as discussed in Sect. 4.

6 Conclusions

We have analyzed the structure of the least-squares problem to simultaneously determine the astrometric parameters (position, parallax, proper motion) of a large number of sources and the three-axis attitude of a scanning satellite, with application to the Gaia mission. Although the resulting normal matrix is very sparse, its structure is complex and related to the specific design of Gaia's instrument and scanning law. For simplicity only two kinds of unknowns were considered, viz., the source parameters ( ${\sim}5\times 10^8$ ) and the attitude parameters ( ${\sim}2\times 10^7$ ). Eliminating either kind results in a reduced normal matrix, and we have studied the smaller of them (for the attitude parameters) in detail using numerical simulations and symbolic computation. Although the reduced attitude matrix is still sparse, Cholesky decomposition gives a high degree of fill-in even after re-ordering the unknowns. In particular, we have seen that the minimum-degree re-ordering algorithm is not efficient to solve this problem. Some alternative approaches to the direct solution (eliminating the attitude unknowns, and orthogonal transformation of the observation equations) have also been briefly considered, but appear to be at least as complex. These findings make it unlikely that any direct method can be found to solve the overall Gaia astrometric adjustment problem with current practical limitations in terms of storage and floating-point operations. By comparison, a simple iteration scheme requires negligible storage and a factor ${\sim}10^{-4}$ less computations, and is clearly feasible. Alternative solution methods, along the lines of the Hipparcos three-step procedure, involve undesirable approximations without offering any clear advantages.

It should be stressed that the present results do not prove that a direct method is unfeasible. Indeed, even if it appears unlikely, it cannot be excluded that a good permutation of the unknowns can be found that dramatically reduces the fill-in of the Cholesky factor. Nonetheless, our conclusions support the current plans to implement relatively straightforward iteration schemes for the core astrometric solution of Gaia (Lindegren et al., in prep.). Their optimization is the subject of a separate paper (Bombrun et al., in prep.).

Acknowledgements

This work was supported by the European Marie-Curie research training network ELSA (contract MRTN-CT-2006-033481) and by the Swedish National Space Board. The first author thanks Ulrich Bastian and Hans Bernstein for their useful comments on earlier versions of this paper (Bombrun 2008b).

Appendix A: Sparseness structure of the reduced normal matrix

In this appendix we give some more details concerning the structure of the reduced normal matrix $\vec{R}_a$ (Eq. (16)) computed by the process described in Sect. 3.

$\begin{figure} \par\mbox{\includegraphics[width=8cm,clip]{13503fg3a.eps}\hspace{5mm} \includegraphics[width=7.8cm,clip]{13503fg3b.eps} } \end{figure}$

Figure A.1:

Left: Structure of the reduced normal matrix $\vec{R}_a$ (Eq. (16)) for 10 successive spins (2.5 days). Non-zero elements are filled. The row and column indices refer to groups of three attitude parameters (representing the three orientation angles). Thus the actual number of attitude parameters in this time segment is 30 000, and each element represents a $3\times 3$ submatrix. Right: A detail from the left diagram (the square in the upper-right corner), showing how the attitude parameters over a single 6 h period (one spin) are connected to the attitude parameters two days previously. See Fig. B.1 for an explanation of the geometry.

Open with DEXTER

Figure A.1 (left) shows the sparseness structure of the reduced normal matrix calculated from simulated Gaia observations covering a period of 2.5 days (10 successive spins). Non-zero values are filled and the zeroes left blank. This figure is similar to Fig. 3 in Bernstein et al. (2005) and some figures in Bombrun (2008b). We can observe the effects of the Gaia design. The two fields of view and the scanning law introduce a banded, almost periodic, pattern. The first and second bands parallel to the diagonal are due to connections introduced by sources successively seen in the two fields of view, whereas the third band is due to connections over a full spin period (6 h). The distance between the diagonal and the third band corresponds to a full rotation ( $360^\circ$ ) of Gaia around its spin axis, whereas the distance between the diagonal and the first band corresponds to the basic angle between the two fields of view ( $106.5^\circ$ ). Moreover, we observe that the farther away from the diagonal a band is, the sparser is becomes. This is due to the spin axis slowly changing its direction, by about $1^\circ$ per spin period. Some points on the celestial sphere are repeatedly observed during more than a day, whereas others are only observed in a single passage of one of the fields of view.

In the right diagram of Fig. A.1 we plot an isolated pattern that appears in the reduced normal matrix some distance away from the diagonal. This pattern is composed of eight blocks of points. In order to understand this pattern, we should look at it as composed of two squares, one following the other in time, i.e., in the diagonal direction. On the time scale of a spin period (6 h), Gaia will scan the celestial sphere roughly along a great circle. Considering any two points in time during the mission, there are two such great circles (A and B in Fig. B.1) which usually intersect at a significant angle. This means that they only have common sources in two small areas (N1, N2) symmetrically with respect to the center of the celestial sphere. The sources at N1 link the attitude parameters around times A1, A2, B1 and B2. In Fig. B.1, the pointings A1, A2, B1 and B2 show the positions of the instrument x axis (half-way between the two fields of view) at these times. In Fig. A.1 (right) the corresponding connections are seen as the four groups of non-zero elements forming the corners of a square. Similarly, the sources around N2 link the attitude parameters around times A3, A4, B3 and B4 forming a second square in the diagram.

Although the approximate size and repetition period of the pattern shown in the right part of Fig. A.1 are determined by the angle between the two fields of view and the spin period, the pattern is not repeated with strict periodicity, due to the precessional motion of the spin axis around the Sun-Earth axis, which itself is rotating. Over the time, the spinning axis is again pointing toward one of its previous directions. Hence, far away from the diagonal, the pattern can become similar to the structure observed close to the diagonal. It may also happen that the non-zero bands are orthogonal, rather than parallel to the diagonal, viz., when the spin axis is pointing in the opposite direction. The complexity of the Cholesky decomposition (see Appendix B) of the reduced normal matrix is due to this particular structure that strongly connects all the attitude parameters over the whole mission.

Appendix B: Cholesky factorization and the Minimum Degree algorithm

$\begin{figure} \par\includegraphics[width=6cm,clip]{13503fg4.eps} \end{figure}$

Figure B.1:

Illustration of the two great-circle scans (A, B) that may produce a connectivity diagram similar to the right graph in Fig. A.1. The two circles intersect at the nodes N1 and N2. The points marked A1, A2, A3, A4 are successive pointings of the instrument x axis (bisecting the two viewing directions) along scan A when either N1 or N2 is observed in one of the fields of view. The angle from N1 to A1 or A2 is half the basic angle, $53.25^\circ$ , as is the angle from N2 to A3 or A4. Similarly B1, B2, B3, B4 are successive pointings of the x axis along scan B when either N1 or N2 is observed in one of the fields of view. The times corresponding to the pointings A1, $\dots$ , B4 indicated in the left diagram of Fig. A.1.

Open with DEXTER

Any real symmetric positive semidefinite matrix $\vec{N}$ (i.e., $\vec{N}=\vec{N}'$ is such that $\vec{x}'\vec{N}\vec{x}\geq 0$ for all vectors $\vec{x}$ ) can be factored into $\vec{N}=\vec{U}'\vec{U}$ , where $\vec{U}$ is a real, upper triangular matrix. The factorization is achieved by means of the Cholesky algorithm (e.g., Björck 1996; Golub & van Loan 1996; Stewart 1998). Cholesky factorization is particularly useful for least-squares problems, where the normal matrix $\vec{N}$ is always symmetric positive semidefinite. After factorization, the normal equations $\vec{N}\vec{x}=\vec{b}$ are solved as the two triangular system $\vec{U}'\vec{y}=\vec{b}$ and $\vec{U}\vec{x}=\vec{y}$ . The factorization can be made ``in place'', which means that the elements in (the upper triangular part of) $\vec{N}$ are successively replaced by the elements of $\vec{U}$ . During this process elements in $\vec{N}$ that are strictly zero may be replaced by non-zero elements in $\vec{U}$ . This is known as ``fill-in''. Thus, factorization of a sparse matrix $\vec{N}$ usually results in a less sparse triangular factor $\vec{U}$ . However, certain sparseness structures of $\vec{N}$ (e.g., a band-diagonal structure) do not produce fill-in when computing the Cholesky factor.

It is important to note that the fill-in of the Cholesky factor $\vec{U}$ depends on the order of the unknowns. Any reordering of the unknowns can be formally represented by an orthogonal permutation matrix $\vec{P}$ such that $\vec{P}\vec{x}$ is the vector of the reordered unknowns. The permuted normal equations are $\vec{P}\vec{N}\vec{P}'\vec{P}\vec{x}=\vec{P}\vec{b}$ . The permuted normal matrix, $\vec{P}\vec{N}\vec{P}'$ , is obtained by reordering both the rows and columns of $\vec{N}$ , and is also symmetric positive semidefinite, and can be factorized by the Cholesky algorithm.

The fill-in of the Cholesky factor thus depends on $\vec{P}$ . In particular, there is a permutation that minimizes the number of non-zero elements in $\vec{U}$ . The computation of the best permutation matrix $\vec{P}$ is an NP-complete problem (Cook 1971; Pothen 1988), i.e., a problem with a complexity that grows faster than any polynomial in the size of the matrix $\vec{N}$ . Since no ``fast'' algorithm is known for this problem, essentially all permutations have to be tested in order to find the one that minimizes the fill-in of the Cholesky factor. This is not very meaningful, however, since it will take less resources to solve the normal equations without reordering than to find the best permutation.

The Minimum Degree algorithm (Markowitz 1957) is a classical heuristic process that computes a reordering of $\vec{N}$ that decreases the fill-in of the Cholesky factor. This reordering is not the best, but is usually a good one. The idea of the minimum degree reordering is to consider the graph of the sparseness structure and to perform at each step the Gauss pivoting on the node with the minimum number of direct connections with other nodes. For more information about the minimum degree reordering, see for example Sect. 6.5.2 of Björck (1996) and the description of the Matlab command symamd in Davis (2006).

References

Bastian, U., & Biermann, M. 2005, A&A, 438, 745 [NASA ADS] [CrossRef] [EDP Sciences] [Google Scholar]
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Footnotes

... solution: Standard errors and correlations can nevertheless be estimated through statistical techniques, see Holl et al. (2009) for a first study of spatial correlations in the global astrometric solution for Gaia.
... matrix: Also called Helmert blocking in reference to the German geodesist F. R. Helmert who described this structure in 1880.
...: A floating-point is a standard that defines the representation of rational numbers in a computer. The term flop is used as a unit for the number of floating-point operations needed to solve a problem.
... unfeasible: For comparison, it is estimated that the entire Gaia DPAC processing will require of the order of 10²¹ flop (Mignard et al. 2008), comparable to several other large computational projects. On a 10 TFLOPS machine, the corresponding computing time is three years.
... formula: In this and subsequent formulae, an expression like $\vec{y}=\vec{K}^{-1}\vec{z}$ is shorthand notation for the solution of $\vec{K}\vec{y}=\vec{z}$ . Naturally, the inverse matrix is never computed unless explicitly needed.
... number: The condition number of the arbitrary (square or rectangular) matrix $\vec{X}$ is defined in terms of the Euclidean matrix norm as $\kappa(\vec{X})=\vert\vert\vec{X}\vert\vert~\vert\vert\vec{X}^\dagger\vert\vert$ , where $\vec{X}^\dagger$ is the pseudo-inverse of $\vec{X}$ (e.g., Stewart 1998).
... triangular: The standard notation uses $\vec{R}$ for the upper-triangular matrix; hence the name QR factorization. For consistency with Appendix B and to avoid confusion with the reduced matrix, we use $\vec{U}$ instead.

All Figures

$\begin{figure} \par\includegraphics[width=9cm,clip]{13503fg1} \end{figure}$	Figure 1: The fill factor $\eta$ of the reduced normal matrix in (15), and of its Cholesky factor, as function of the number of spins (6 h intervals) included in the solution. Three sequences of increasing number of spins are considered, labelled set 1, 3 and 12, as explained in the text.
Open with DEXTER
In the text

$\begin{figure} \par\includegraphics[width=9cm,clip]{13503fg2} \end{figure}$	Figure 2: Same as Fig. 1, but showing the complexity of reduced normal equations in terms of the number of floating-point operations (flop) needed to compute the Cholesky factors, using the minimum degree reordering algorithm and Metis software.
Open with DEXTER
In the text

$\begin{figure} \par\mbox{\includegraphics[width=8cm,clip]{13503fg3a.eps}\hspace{5mm} \includegraphics[width=7.8cm,clip]{13503fg3b.eps} } \end{figure}$	Figure A.1: Left: Structure of the reduced normal matrix $\vec{R}_a$ (Eq. (16)) for 10 successive spins (2.5 days). Non-zero elements are filled. The row and column indices refer to groups of three attitude parameters (representing the three orientation angles). Thus the actual number of attitude parameters in this time segment is 30 000, and each element represents a $3\times 3$ submatrix. Right: A detail from the left diagram (the square in the upper-right corner), showing how the attitude parameters over a single 6 h period (one spin) are connected to the attitude parameters two days previously. See Fig. B.1 for an explanation of the geometry.
Open with DEXTER
In the text

$\begin{figure} \par\includegraphics[width=6cm,clip]{13503fg4.eps} \end{figure}$	Figure B.1: Illustration of the two great-circle scans (A, B) that may produce a connectivity diagram similar to the right graph in Fig. A.1. The two circles intersect at the nodes N1 and N2. The points marked A1, A2, A3, A4 are successive pointings of the instrument x axis (bisecting the two viewing directions) along scan A when either N1 or N2 is observed in one of the fields of view. The angle from N1 to A1 or A2 is half the basic angle, $53.25^\circ$ , as is the angle from N2 to A3 or A4. Similarly B1, B2, B3, B4 are successive pointings of the x axis along scan B when either N1 or N2 is observed in one of the fields of view. The times corresponding to the pointings A1, $\dots$ , B4 indicated in the left diagram of Fig. A.1.
Open with DEXTER
In the text

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[1] Bastian, U., & Biermann, M. 2005, A&A, 438, 745 [NASA ADS] [CrossRef] [EDP Sciences] [Google Scholar]

[2] Bernstein, H., Bastian, U., & Hirte, S. 2005, Gaia Technical Notes, GAIA-ARI-BST-001-5 [Google Scholar]

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[9] Eichhorn, H. 1960, Astron. Nachr., 285, 233 [Google Scholar]

[10] ESA. 1997, The Hipparcos and Tycho Catalogues, SP-1200 (ESA) [Google Scholar]

[11] George, A., & Liu, J. W.-H. 1981, Computer Solution of Large Sparse Positive Definite Systems (New Jersey: Prentice-Hall) [Google Scholar]

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[17] Jordan, S. 2008, Astron. Nachr., 329, 875 [Google Scholar]

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[20] Kovalevsky, J., Falin, J. L., Pieplu, J. L., et al. 1992, A&A, 258, 7 [NASA ADS] [Google Scholar]

[21] Lacroute, P. 1967, Transactions of the IAU, XIIIB, 63 [Google Scholar]

[22] Lacroute, P. 1975, in Space Astrometry, ESRO SP-108, ed. T. D. Nguyen, & B. T. Battrick, 5 [Google Scholar]

[23] Lammers, U., Lindegren, L., O'Mullane, W., & Hobbs, D. 2009, in Astronomical Society of the Pacific Conference Series, ed. D. A. Bohlender, D. Durand, & P. Dowler, ASP Conf. Ser., 411, 55 [Google Scholar]

[24] Lindegren, L., Babusiaux, C., Bailer-Jones, C., et al. 2008, in IAU Symp. 248, ed. W. J. Jin, I. Platais, & M. A. C. Perryman, 217 [Google Scholar]

[25] Lindegren, L., Høg, E., van Leeuwen, F., et al. 1992, A&A, 258, 18 [NASA ADS] [Google Scholar]

[26] Markowitz, H. M. 1957, Management Sci., 3, 255 [CrossRef] [Google Scholar]

[27] Mignard, F., Bailer-Jones, C., Bastian, U., et al. 2008, in IAU Symp. 248, ed. W. J. Jin, I. Platais, & M. A. C. Perryman, 224 [Google Scholar]

[28] Perryman, M. A. C., de Boer, K. S., Gilmore, G., et al. 2001, A&A, 369, 339 [NASA ADS] [CrossRef] [EDP Sciences] [Google Scholar]

[29] Pothen, A. 1988, Technical report CS-88-16 [Google Scholar]

[30] Stewart, G. 1998, Matrix Algorithms: Basic decompositions (SIAM) [Google Scholar]

[31] van der Vorst, H. 2003, Iterative Krylov Methods for Large Linear Systems (Cambridge University Press) [Google Scholar]

[32] van Leeuwen, F. 2007, Hipparcos, the New Reduction of the Raw Data (Astrophysics and Space Science Library), 350 [Google Scholar]

[33] von Oppolzer, T. 1880, Lehrbuch zur Bahnbestimmung der Kometen und Planeten. Zweiter Band (Leipzig: Wilhelm Engelmann) [Google Scholar]

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