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Russian Academy of Sciences
Central Astronomical Observatory at Pulkovo

SIXTH US/RUSSIAN
SPACE SURVEILLANCE WORKSHOP

August 22-26, 2005

Proceedings
Edited by P. Kenneth Seidelmann and Victor K. Abalakin

St. Petersburg, 2005


PROBLEMS OF THE CATALOGUE MAINTENANCE FOR FAINT GEO OBJECTS

V. Agapov1, V. Biryukov2, S. Kamensky3, Z. Khutorovskiy4, I. Molotov5,
V. Rumyantsev6, A. Sochilina7, V. Titenko8

1Keldysh Institute of Applied Mathematics, Miusskaya Sq., 4, Moscow, Russia, 125047 Space Informatics and Analytical Systems (KIA Systems JSC), Gzhelsky Lane, 20, Moscow, Russia, 107120
2 Crimean Astrophysical Observatory, Nauchny, Crimea, Ukraine, 98409 Crimean Laboratory of Sternberg Astronomical Institute of Moscow State University, Nauchny, Crimea, Ukraine, 98409
3 Space Informatics and Analytical Systems (KIA Systems JSC), Gzhelsky Lane, 20, Moscow, Russia, 107120
4 Vympel Corporation, 4th of March 8th Str., 3, Moscow, Russia, 125319 Space Informatics and Analytical Systems (KIA Systems JSC), Gzhelsky Lane, 20, Moscow, Russia, 107120
5 Central (Pulkovo) Astronomical Observatory, Pulkovskoe chaussee, 65/1, St. Petersburg, Russia, 196140 Keldysh Institute of Applied Mathematics, Miusskaya Sq., 4, Moscow, Russia, 125047
6 Crimean Astrophysical Observatory, Nauchny, Crimea, Ukraine, 98409
7 Central (Pulkovo) Astronomical Observatory, Pulkovskoe chaussee, 65/1, St. Petersburg, Russia, 196140
8 Keldysh Institute of Applied Mathematics, Miusskaya Sq., 4, Moscow, Russia, 125047

Abstract. Under order of the Rusian Academy of Sciences Center on collection, processing and analysis of information on space debris operated at the Keldysh Institute of Applied Mathematics (KIAM) group of researchers developed the program of search, tracking and analysis of orbital evolution of faint objects of space debris in the geostationary region (GEO), presumably from events of fragmentation of some resident GEO objects.
Search fields were calculated by use of the various approaches, each of which is briefly described in this paper. The search in the calculated fields and their vicinities was carried out on many nights in October - December, 2004 and January-August, 2005. Almost two dozen faint objects were discovered. These objects were detected repeatedly at the nearest possibility (sometimes in 2-3 weeks and more of an interruption in observations because of an unfavorable weather). All detected objects were tracked continuously during several subsequent nights. The accuracy of astrometric positions (σ=1") achieved has allowed not only to construct accurate orbits, but also to improve the estimation of the solar radiation pressure coefficient value for each object. It was revealed that at least for 3 objects the solar radiation pressure is a very essential factor, causing strong evolution of eccentricity and argument of perigee of the objects orbit. Further analysis has shown, that the eccentricity of one of objects changes 5 times during just one half-year.
The discovered objects raised serious problems for GEO catalogue maintenance. They are significantly different in evolution from other GEO population members, so making decision solutions as applied previously for objects identification, tracking etc. are not always applicable.
The detailed results of research are presented in this paper. The work is carried out at partial support of the grant INTAS 2001-0669.
1. INTRODUCTION

The center on collection, processing and analysis of information on space debris of the Russian Academy of Sciences (RAS), developed and operated on the basis of the Ballistic Center at the Keldysh Institute of Applied Mathematics (KIAM), carries out works aimed at systematic research of a population of small-sized high altitude objects and their properties. Under order of the Center, the group of the researchers from KIAM, KIA Systems, Central (Pulkovo) astronomical observatory of the RAS, and Crimean astrophysical observatory (CrAO, Nauchny, Ukraine) carry out the special program of search, tracking and analysis of orbital evolution of faint (fainter than 15m at phase angles 20-30) objects in the geostationary region (GEO). The program is aimed at reaching of the following purposes:
  • Improvement of application of the various methodical approaches of calculation of observation fields for search of objects in the GEO region
  • Detection of faint objects in GEO region
  • Tracking of the detected objects
  • Determination of trajectory parameters and analysis of evolution of orbital elements
  • Estimation of area-to-mass ratio (AMR) value for tracked objects
  • Studying catalogue maintenance problems for this class of objects

General statement of the task, processing of measurements, analysis of orbital evolution, estimation of area-to-mass ratio values, calculation of ephemerides for observations, and interpretation of results were carried out by the KIAM team. The Pulkovo observatory team was responsible for the calculation of fields for search of fragments produced as a result of supposed explosions, independent analysis of measurements for increase of reliability of results, and also for identification of observed objects with the probable parent body. The CrAO team performed a search for faint objects in the calculated fields using the selected strategy of objects search, repeated detection and tracking of the rediscovered objects, and implemented the techniques of processing of CCD-frames obtained with integration time up to 20 sec. The KIA Systems team performed implementation of an improved version of GEO catalogue maintenance procedures in order to take into account peculiarities of newly discovered objects.

After obtaining the first results, the research group has addressed the request to some observatories for scheduling and realization of several sessions of follow-up observations with the purpose of confirmation of the results reliability. Observations were carried out at Mondy (Sayan observatory of the Institute of Solar-Terrestrial Physics of the Siberian Department of the RAS), Zimmerwald (Astronomical Institute of University of Bern), PIMS (Observatory Sciences Ltd.), and Xinglong (China) observatories.

On the basis of the obtained sets of astrometric positions the KIAM and KIA Systems teams carried out the precise determination of orbit parameters, researched orbital evolution, obtained the estimation of the area-to-mass ratio value, carried out studies of a series of measured values of a visual magnitude of objects.

This work is a further development of the regular IADC GEO survey campaigns and its results are an essential addition to understanding the real properties of a population of objects of space debris in the GEO region. Moreover, this work is the first attempt to include faint GEO objects in the process of regular catalogue maintenance with all appropriate tasks to be solved.

2. OBSERVATION TOOLS

The main tool for realization of the observation program is the -64 telescope (D = 64 cm, F = 90 cm), established in the CrAO. The telescope is equipped with the ST-8 (KAF-1600) CCD-matrix. The field of view with the given CCD-matrix makes 53x34 arcmin. The limiting magnitude of the instrument is 20m in integral light at the integration time of 120 sec. This mode of observation can be used to search for asteroids. For Earth-orbiting objects of space debris in the GEO region the limiting magnitude is 17,5m 18m with an integration time of 15 sec.

The

Fig. 1. The -64 telescope at CrAO

ZTSh telescope site at CrAO

Fig. 2. ZTSh telescope site at CrAO

The given telescope permits the tracking of objects having an angular rate up to 4 arcmin per sec. The exterior of a telescope is shown in Fig.1.

Since March, 2005 use of the second telescope for observations of small-sized high altitude objects ZTSh (D = 260 cm, F = 1000 cm) also established in CrAO is started. CCD-camera IMG-1001E (KAF-1001E) was specially purchased and installed at the telescope to provide support within the frame of the described observation program developed under the order of the Center at KIAM. The field of view is 8.5x8.5 arcmin. Since the telescope has not yet the capability of auto tracking of fragments of space debris (the necessary adaptations are carried out), the observations are made with a fixed telescope and periodic manual repositioning at the time of exit of an observable object from the boundary of a field of view. The exterior of the telescope site is shown in a Fig. 2.

A Zeiss-600 telescope equipped with S1C (Electron) CCD-matrix of 1024x1024 pixels in size was used for observations in Sayan observatory. The field of view is 7.5x7.5 arcmin, limiting magnitude 18m.

Observations at Zimmerwald observatory were carried out with 1m-class telescope equipped with 2048x2048 pixels CCD-matrix. The field of view is 20x20 arcmin, limiting magnitude 19m.

PIMS observatories are equipped with 40 cm aperture robotic telescopes having CCD- matrix of 1024x1024 pixels in size installed. The field of view is 40x40 arcmin, limiting magnitude - 17m.

Xinlong observatory has used a 60/90 Schmidt telescope with Ford 2048x2048 CCD-matrix. Field of view of the instrument is 58*58 arcmin.

3. OBSERVATION STRATEGIES AND CCD-IMAGES PROCESSING

3.1. Observation strategies

One of key elements of this work is the observation strategy from the point of view of two aspects: search for new objects and repeated detection of earlier observed ones.

One of the approaches used to search for new objects in the GEO area is well known. It is widely used in the coordinated IADC GEO survey campaigns. According to the IADC WG1 recommendations, the strategy in this case is to point the telescope to a given right ascension (RA) and Declination (DECL), and then take images as quickly as possible. Thus, the effective limiting detectable size is constant for each night. The sky coverage is continuous within each declination band, so there are no gaps. This search fence is solid in RA (east-west direction), but leaky in DECL (north-south direction). All of the data are then collected at the same solar phase angle. There is no time lost due to telescope motion. To provide optimal observation conditions search fields are placed close to the antisolar point (i.e. to the point with minimal phase angle that as a rule corresponds to maximal brightness of searched objects) taking into account that it should avoid the shadow of the Earth covering some part of the GEO region during the period close to spring and autumn equinoxes. Moreover, search fields sometimes are placed at areas where the apparent density of the catalogued GEO objects in the RA-DECL-space is maximal.

The second approach is developed specially for search of fragments of supposed explosions of some resident GEO objects. A list of some objects supposed to explode was given in (Agapov et al., 2003).

The developed theory of evolution of geostationary satellite orbits (Kiladze et al., 2003) allows determining RAAN (Ω) and inclination (i) for all simulated explosion fragments with high accuracy on intervals of 40-50 years. Calculating RA (α) and DECL (δ) for cross points S of orbits of fragments with the orbit of the exploded parent satellite on long time frames, it is possible to determine geocentric coordinates of the parent object orbits segment, on which cross points with orbits of all fragments are distributed with a minimum dispersion (Sochilina et al., 2003). Fig. 3 demonstrates the geometry of the discussed case.

As the planes of orbits of considered object and its fragments are intersected in two points, the coordinates on cross points S will differ on 180 in α. The value of δ will have the inverse sign.

Geometry of relative position of orbits of a parent satellite and a fragment of its explosion

Fig. 3. Geometry of relative position of orbits of a parent satellite and a fragment of its explosion.

The results of the simulation for supposed fragmentations of some Transtage-type and Ekran-type objects are presented at Fig. 4. Tiny blue dots represent trajectories of catalogued GEO objects in geocentric RA-DECL-space as of Feb 09, 2005. Green lines represent conditional boundaries of the galactic equator and solid black line represents the Earth shadow boundary. Magenta and yellow solid lines represent trajectories of supposedly exploded parent objects. Solid circles on these trajectories mark segments where cross points with orbits of all simulated fragments are distributed with a minimum dispersion.

Position of segments of cross points of orbits of fragments with orbit of some supposedly exploded parent objects

Fig. 4. Position of segments of cross points of orbits of fragments with the orbit of some supposedly exploded parent objects, where cross points distribution dispersion is minimal as of Feb 09, 2005. Transtage-type parent object orbits are shown in light gray, Ekran-type parent object orbits are shown in dark gray.

Fig. 5 represents a more detailed picture of simulation results for the case of the 1979- 078A object (an Ekran-type spacecraft). Only galactic equator boundaries, the Ekran and its simulated fragments trajectories are shown as of Feb 09, 2005. It is clearly visible that the cross points are dispersed along the Ekran trajectory, but concentrated in some limited segment. Accordingly, the field for search of the Ekran possible explosion fragments can be placed inside of this segment.

Trajectories of Ekran 1979-087A satellite and its explosion fragments as of Feb 09, 2005.

Fig. 5. Trajectories of Ekran 1979-087A satellite and its explosion fragments as of Feb 09, 2005.

For repeated observation of the earlier detected objects the planar along-trajectory search strategy was realized. While using this strategy it is important to properly estimate an error of object predicted position. If the error is insignificant in comparison with the size of a field of view of the telescope, the object at once falls in a field of view and the special search is not required. Otherwise it is necessary to conduct search. As a rule, for the newly detected objects optically observed on a short time interval, an ellipse of errors of the predicted position has strongly prolate form, thus its semimajor axis is oriented approximately in parallel to trajectory of object motion. It allows to use a simple way of search -"waiting in a point ". Let predicted right ascension and declination of object in the moment t are α and δ respectively. The method of search consists in observation of a point with coordinates (α,δ) during time interval from t-ΔΤ up to t+ΔΤ, where ΔΤ - some value. Actually the object passes right ascension α in some moment t+εt, and its declination in this moment is equal to δ+εδ. Here εt is an error of the prediction in time, εδ is an error of the prediction in declination. If ΔΤ > 3σ(εt) and fδ/2 > 3σ(εδ), where fδ - size of a field of view on declination, σ(εt), σ(εδ) - RMS values of an error of the object position prediction on time and on declination accordingly, than by search the object will get in a field of view with probability not less than 0.994.

By numerical simulation the RMS values following kinds of errors of the object position prediction are determined: angular position error σ(r), error of the prediction in time σ(εt) and error of the prediction in declination σ(εδ). Angular position error here is understood as angular distance between a predicted and actual position of object. The simulation was made in the following suppositions. Geostationary object is observed on time interval Tobs, during which the angular measurements at regular intervals hm are made, the RMS error of measurements is equal am. Based on the obtained measurements, orbit is determined and then the prediction of a visible position of object for the moment, spaced from the end of an interval of observation by time Tpr is calculated.

Table 1 contains the results of calculations for the case am= 1 arcsec, hm= 1 min and various values of Tobs, Tpr. Object orbit is assumed circular with a semimajor axis of 42164 km and inclination 13. Observation facility assumed located at 40 latitude.

Table 1. Simulated prediction errors in position of newly detected object. Facility at 40 latitude.

σm,
arcsec
hm,
min
Tobs Tpr σ(r),
deg
σ(εt),
min
σ(εδ),
deg
1 1 10m 30m 0.015 0.07 0.012
1 1 10m 1h 0.07 0.32 0.04
1 1 10m 2h 0.045 1.9 0.15
1 1 10m 4h 3.2 13 0.5
1 1 10m 1d 40 160 0.5
1 1 30m 2h 0.04 0.17 0.01
1 1 30m 4h 0.25 1.0 0.04
1 1 30m 1d 6.9 28 0.22
1 1 1h 4h 0.05 0.2 0.007
1 1 1h 1d 1.2 5.0 0.05
1 1 2h 1d 0.19 0.8 0.05
1 1 2h 10d 1.9 7.7 0.05
1 1 4h 1d 0.025 0.1 0.0004
1 1 4h 10d 0.25 1.0 0.003

Depending on the selection of orbit parameters of the object and the coordinates of the observation facility, the different values of errors are obtained. In particular, the errors of the object position prediction are essentially increased, if the observation facility is located close to the orbital plane of the object. Table 2 contains the similar calculation results as table 1 for an orbit with an inclination 0 and an observation facility located exactly on the equator.

Table 2. Simulated prediction errors in position of newly detected object. Facility at 0 latitude.

σm,
arcsec
hm,
min
Tobs Tpr σ(r),
deg
σ(εt),
min
σ(εδ),
deg
1 1 10m 30m 0.13 0.5 0.01
1 1 30m 2h 0.21 0.85 0.0007
1 1 1h 4h 0.15 0.6 0.0004
1 1 1h 1d 3.6 14.5 0.0004
1 1 2h 1d 0.34 1.4 0.0002
1 1 4h 1d 0.03 0.12 0.0001

The projection of the ellipsoid of errors is better understood in (Hour Angle- Declination) or (Azimuth-Elevation) space due to the specific motion of the GEO objects. So, it is very useful to calculate the appropriate values of errors and to develop telescope pointing software, which can use this representation of the search field for calculation of the search strategy. Several search fields should be covered as a rule, after the initial orbit determination based on a short arc.
3.2. CCD images processing

Since the purpose of the work was the observation of faint objects, to obtain the image of a moving object in the star background with a telescope -64 CCD-matrix, it is necessary to increase the exposure time. In this case stars look like points and the object looks like a trail. The problem of an accurate estimation of the astrometric properties of trail objects from a single observation is important for predicting its positions at the next time of observation. It is necessary to increase the probability of repeated detection of the object. To solve the problem some limited estimates based on Cramer-Rao theorem about minimum variance bound are used in the processing algorithm.

Another situation takes place when the telescope control system permits to trace the object of interest, if its predetermined trajectory is known. In that case stars smear to trails on the moving frame associated with the moving object. Then the problem is to precisely estimate the CCD-frame position relative to the star-trails, and calculate coordinates of the point-like (or slightly smeared) object on the CCD-frame. Fig. 6 shows an example of a CCD- frame, obtained in tracking mode, of one of the discovered objects. The high density of stars is clearly visible.

The Hough transform technique is used for processing such images in the case of the absence of a-priori information about star trails direction and length. But usually the telescope control system provides such information. In this case cross correlation algorithms are used for selection of star trails and their characteristics estimation. Finally, more precise estimations of star positions are obtained with the assumption that the track is a pixel detector image of a segment blurred by a 2-D Gauss point spread function (PSF). The finite size of the pixels takes into account, what the model image is calculating and the PSF is integrating inside of each pixel by analytical calculation. Parameters of the model are estimated with the maximum likelihood method. The combination of approximate, heuristic methods and algorithms on the initial stage of processing and more exact estimation on the final stage allows to achieve good outcomes.

CCD-frame  containing  the  90008 object image.

Fig. 6. CCD-frame containing the 90008 object image
3.3. Positional measurements processing

The refinement of orbit was conducted with usage of numerical motion model, which is taking into account the following essential perturbations:
  • Earth gravity field (EGM-96 model truncated down to 16x16)
  • the Moon gravity (DE-403)
  • the Sun gravity (DE-403)
  • direct solar radiation pressure (along the object-Sun direction component) in view of the Earth shadow passages
The calculation of derivatives in the model of the orbit determination depends on analytical relations, the integration of the equations of motion implements a modified Runge- Kutta method of the 8-th order (Stepaniants et al., 2000).

Already right at the beginning of activity, in November, 2004, in processing of measurements of two objects detected in the middle of October, rediscovered after a two weeks observation interruption due to weather, the following fact was obvious. For both objects the RMS value of residuals has several times exceeded that expected after refinement of the orbit parameters and the solar radiation pressure coefficient estimation. The external accuracy of single measurements was rated before, on the basis of large statistics accumulated on rather bright unknown objects in the GEO region (Agapov et al., 2005). The value of solar radiation pressure coefficient has appeared extremely large compared to the known usual GEO population representatives. Originally, even the supposition was considered that different objects on very close orbits actually were observed. However, further analysis has confirmed the obtained estimations of the solar radiation pressure coefficient. So some other explanations have to be found for the observed measurements inconsistence. There are the following possible explanations:
  • variation of the solar radiation pressure coefficient due to complex object tumbling is not taken into account in the motion model
  • two other components of direct solar radiation should be taken into account
  • Moon shadow transitions should be added into the motion model, since any time interval without solar radiation influence may result in changes in evolution of orbit for objects with high AMR values
4. RESULTS

As of Aug 20, 2005 orbits of 9 fragments were studied in detail. Object 43022 was first discovered at Zimmerwald observatory and then tracked at CrAO.
The orbital parameters are summarized in Table 3. The orbital elements are given in the J2000 reference frame at the epoch provided in the appropriate column.
Table 4 contains values of the standard visual magnitude of the objects (mean and 1 sigma RMS value), estimations of the area-to-mass (A/m) ratio value, and the most probable source of the object (parent object).
The values of the standard magnitude are reduced to distance 37000 km and a phase angle 90 according to the well known formula (McCue et al., 1970):

m= -26.58-2.5lg[AγF(φ)/R2],

where
A - area of reflected surface, sq. m
γ - reflectivity coefficient
φ - phase angle (the Sun-object-observer angle)
F(φ) - function of phase angle
R - range between observer and an object

The value of standard visual magnitude should be considered as the first order estimation since it was calculated assuming function of phase angle as the one for a diffuse Lambertian sphere:

F(φ) = 2/(3π2) [(π-φ) cos φ + sin φ]

Fig. 7 shows measured values of visible magnitude of all 8 objects in integrated light.

Table 3. Orbital parameters of detected and tracked faint objects

Object Nignts/
positions
Observation
interval
Orbit
epoch
Nodal
period,
min
a, km e i, Ω, ω,
90003 7/577 18.10.04-10.01.05 2005/01/10 11:08:49 1370.55 40868.21 0.0331042 11.350 337.942 345.7792
90004 4/294 14.10.04-13.01.05 2005/01/13 15:25:41 1482.82 43075.92 0.0172312 07.464 67.385 43.7397
90005 4/158 07.11.04-10.04.05 2005/04/10 11:35:33 1428.34 42012.69 0.0605817 14.493 2.432 79.1740
90006 45/527 17.12.04-17.08.05 2005/09/05 21:12:21 1434.54 42137.74 0.0012055 14.596 356.476 21.4741
90007 3/148 18.12.04-13.01.05 2005/01/13 10:25:56 1424.14 41931.09 0.0028944 14.525 356.258 296.2724
90008 4/205 09.01.05-04.03.05 2005/09/03 18:56:01 1436.50 42175.82 0.0044647 14.340 2.169 89.6021
90009 10/166 15.03.05-01.04.05 2005/04/01 10:27:27 1441.71 42275.74 0.0030073 14.636 4.472 344.2044
90010 2/126 08.07.05-13.07.05 2005/09/06 02:08:35 1463.62 42711.46 0.0253512 13.296 12.173 263.4078
43022 4/51 09.08.05-12.08.05 2005/09/14 19:54:09 1508.38 43604.12 0.5383407 13.859 324.807 163.6123

Table 4. Some characteristics of detected and tracked faint objects

Object Standard visual magnitude A/m, m2/kg Probable origin source of object (parent object)
90003 16.910.66 2.23-2.58 03432/1968-081E, TRANSTAGE
90004 17.56 0.99 0.33-1.08  
90005 17.66 0.79 0.69-0.71 11273/1979-015A, EKRAN
90006 17.53 0.74 0.006-0.014 10365/1977-092, EKRAN
90007 18.36 0.86 0.92 10365/1977-092, EKRAN
90008 17.34 0.70 0.001-0.019 11273/1979-015A, EKRAN
90009 17.780.96 0.009-0.012  
90010 18.161.01 1.20-1.41  
43022 17.73 0.68 5.06-5.42  

Measured visible magnitude in integrated light for 8 faint GEO objects.

Fig. 7. Measured visible magnitude in integrated light for 8 faint GEO objects

It is not unexpected that 5 of the 9 objects are preliminary identified with two EKRAN and one Transtage as possible parent objects. This is due to search fields that had been chosen for modeled explosion fragments trajectory crossing areas for these objects.

The following features of the detected objects are well visible from the given data.

Two of objects, 90003 and 43022, have the AMR values 2.23-2.58 and 5.06-5.42 m /kg respectively, that is usual for materials used in manufacturing of a multi-layer thermal insulation of spacecrafts. As a result, its orbit experiences strong disturbances on the part of direct solar radiation. Fig. 8 shows evolution of an eccentricity of the object 90003. It is clearly visible, that for 7 months its value changes by 5.9 times. Thus, the maximum orbital altitude changes more than 2500 km (from 35000 up to 37550 km). The eccentricity changes due to direct solar radiation pressure influence with a period of approximately one year. During this period the object reaches a protected region of functioning GEO spacecrafts (altitude of 36600 km), and within 7.5 months intersects this region, and then for 6 months leaves the protected region.

Eccentricity (as well as argument of perigee and inclination) of 43022 has evolved even more dramatically. Its clearly visible that at present this object has orbital energy corresponding to the usual GEO objects drifting above the operational GEO altitude. But the eccentricity is equal to 0.538! This fact can be explained by strong solar radiation pressure perturbations due to the high AMR ratio value of the object.

Eccentricity evolution for object 90003.

Fig. 8. Eccentricity evolution for object 90003

The second interesting feature of object 90003, as well as objects 90006 and 90008, is the absence of the obviously expressed relation of brightness from the value of a phase angle in the range of phase angles 12 80. This result is rather unexpected and requires close detailed learning. Taking into account the initial supposition on the phase angle function, one can conclude that 90003, 90006 and 90008 are closer in shape to spheres. But this will not explain variations of the AMR ratio for 90003.

For objects 90004 and 95024 the variability of brightness is visible at different phase angles, as well as a strong dependence of brightness on a phase angle value. Such behavior is characteristic for objects such as a plate, flat cover, etc.
5. CONCLUSIONS

The results of the research of faint objects in the GEO area have allowed to reveal a number of features of such objects. In particular, the objects with large area-to-mass ratio values are discovered. It confirms a stated earlier hypothesis about an incorrectness of the supposition of a zero eccentricity at statistical processing of measurements obtained within the framework of the IADC GEO survey campaigns. Direct solar radiation pressure has an essential influence on orbit evolution for these objects. In view of fast changes of eccentricity and argument of perigee of such objects, the statistical samplings of measurements obtained on various nights, even with a difference of a few months, can contain measurements of the same object, where the eccentricity of the orbit has undergone significant change. The result of calculation of a quantity of objects in such a sampling can appear uncertain, if the changes of eccentricity are not taken into account.

Some of the objects do not have the obviously expressed relation of the value of a brightness to a phase angle in the range of phase angles 12 80.

The obtained results can be used for refinement of models of a density function of objects in the GEO region, and also can serve as a starting point for organization of constant monitoring of the GEO region with the purpose of obtaining the maximum reliable information about a true population of objects in it.

The authors would like to acknowledge James Dick, Phil Herridge, Thomas Schildknecht, Zhou Xu, Pavel Papushev, and Oksana Yurysheva for the rendered support in realization of additional observations of the detected objects. The work is carried out at partial support of the grant INTAS 2001-0669.
6. REFERENCES

  • Agapov V., Khutorovsky Z., Boykov V., Sbytov N., Samotokhin A., Experience Of Formation Of The GEO Orbital Information Archive Based On Different Data Sources, Proceedings of the 5th US-Russian Space Surveillance Workshop, 24-27.09.2003, Pulkovo, St. Petersburg, Russia
  • Agapov V., Dick J., Guseva I., Herridge P., Khutorovskiy Z., Molotov I., Ploner M., Rumyantsev V., Schildknecht T., Stepanyants V., Sukhov P., Titenko V., Joint RAS/PIMS/AIUB GEO survey results. 4th European Conference on Space Debris, ESOC, Darmstadt, 18-20 April, 2005.
  • Kiladze, R.L, Sochilina, A.S.. On the new theory of Geostationary satellite motion. Astronomical and Astrophysical Transactions, Vol. 22, Nos. 4-5, August-October 2003, pp. 525-528.
  • McCue, Gary A., Williams, James G., Morford, Joan M. Optical characteristics of artificial satellites. SD 70-55. 1 July 1970, Space Division, North American Rockwell
  • Schildknecht T., Musci R., Ploner M., Preisig S., Cruz J. de Leon, Krag H., Optical Observations of Space Debris in the Geostationary Ring, Proceedings of the 3rd European Conference on Space Debris, ESOC, Darmstadt, 19-21 March 2001, SP-473, Vol.1, October 2001
  • Sochilina A., Kiladze R., On orbital evolution of fragments of exploded objects. Izvestiya GAO at Pulkovo, 216, 2003, pp.437-438 (rus.)

29 2006.

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