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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


SATELLITE ORBITAL CONJUNCTION REPORTS ASSESSING THREATENING ENCOUNTERS IN SPACE (SOCRATES)

T.S. Kelso1 and S. Alfano2

1 Center for Space Standards & Innovation, 7150 Campus Drive, Suite 260, Colorado Springs, CO, USA 80920-6522.
2 Center for Space Standards & Innovation, 7150 Campus Drive, Suite 260, Colorado Springs, CO, USA 80920-6522.

Abstract. As a service to the satellite operator community, the Center for Space Standards & Innovation (CSSI) offers SOCRATESSatellite Orbital Conjunction Reports Assessing Threatening Encounters in Space. CSSI runs a list of all satellite payloads on orbit against a list of all objects on orbit using the catalog of all unclassified NORAD two-line element sets (TLEs) to look for satellite conjunctions for the coming week. The runs are made using, Satellite Tool Kits Conjunction Analysis Tools (STK/CAT) and the NORAD SGP4 propagator implemented in STK. This paper will discuss how SOCRATES works and how it can help satellite operators avoid undesired close approaches through advanced mission planning.
INTRODUCTION

As of 2005 August 15, NORAD tracks 9,379 in earth orbit, of which 2,954 are designated as payloads. While not all of these payloads are still active, about a third are and they perform a variety of important tasksmany vital to the global economy. Since these payloads tend to operate in a limited orbital regime (i.e., they are not randomly distributed) and share that regime with the rocket bodies, upper stages, and associated debris which put them in orbit, the potential exists that any of these payloads might collide with another object on orbit. At relative velocities up to 15 km/s, the results of such a collision would be catastrophic. In the geostationary belt, such a collision would generate debris which would drift around the belt indefinitely, putting at risk all other payloads in that orbit.

While many satellite operators are aware of the possibility of a collision between their satellite and another object in earth orbit, most seem unaware of the frequency of near misses occurring each day. Until recently, no service existed to advise satellite operators of an impending conjunction of a satellite payload with another satellite, putting the responsibility for determining these occurrences squarely on the satellite operators shoulders. This problem has been further confounded by the lack of a timely, comprehensive data set of satellite orbital element sets and computationally efficient tools to provide predictions using industry- standard software. As a result, hundreds of conjunctions within 1 km occur each week with little or no intervention putting billions of dollars of space hardware at risk, along with their associated missions.

As a service to the satellite operator community, the Center for Space Standards & Innovation (CSSI) offers Satellite Orbital Conjunction Reports Assessing Threatening Encounters in Space (SOCRATES). Each day, CSSI runs the list of all satellite payloads against the list of all objects on orbit using the catalog of unclassified NORAD two-line element sets (TLEs) to look for conjunctions over the next seven days. The runs are made using Satellite Tool Kits Conjunction Analysis Tools (STK/CAT) with the NORAD SGP4 propagator in STK.
BACKGROUND

Beginning in May of 2004, CSSI began providing daily reports of likely conjunctions for the upcoming week to the public. Those reports are provided in a special section of the CelesTrak web site and are available to all users. There are no fees or restrictions for this service. As of this writing, no comparable service has ever been provided to the public.

The goal of this service is to provide a reliable tool for satellite users to help them assess whether their payloads might have predicted conjunctions which could require further analysis. For this tool to be considered reliable, it needs to use a comprehensive database of orbital data, along with standard orbital models, and be generated using accepted techniques. It also has to be provided on a regular basis to allow incorporation of the results into daily operational planning.

To meet this goal, SOCRATES uses the most comprehensive orbital database currently available the NORAD two-line element sets. These data are updated twice each day and made available electronically via the new Space Track web site. That database is not fully comprehensive, however, because it intentionally omits those satellites deemed vital to US national security about 185 payloads along with the associated rocket bodies and upper stages which delivered them to orbit. Even so, current orbital data is available for 8,593 of the 9,379 objects (about 91 percent) cataloged by NORAD. Not all of these missing objects are for restricted objects, though. Some are considered lost since they have not been tracked for the past 30 days. It should also be noted that this database does not include those objects too small to be detected or regularly tracked by the US Space Surveillance Network (SSN) nor does it include the roughly 4,000 objects considered to be analyst satellites.

Since TLEs are generated from SSN observations using the SGP4 (Simplified General Perturbations) orbital theory which uses mean elements, the same version of SGP4 must be used for predictions in order to minimize modeling errors. While a version of SGP4 was released to the public in 1980 in Spacetrack Report Number 3 (Hoots, 1980), subsequent modifications were made in 1990 and 1992 which were not released and are considered US export controlled. Most of these changes were to correct errors in the original code for handling special cases in the deep-space portion of the model and other researchers have independently found and corrected these errors in their implementations of SGP4. Extensive testing of the version of SGP4 implemented in STK against known hard cases has shown that it matches the official NORAD version quite well. However, without a standard released version of SGP4 along with a version control history, there will always be some additional level of modeling error in these predictions.

The final requirement for a reliable tool is to have a systematic way to search for all relevant conjunctions in a computationally efficient manner. With current searches comparing 2,686 payloads against 8,593 (as of 2005 August 17) total objects over a one-week period, an inefficient search strategy could be so computationally intensive that it would be impossible to produce a timely report on a daily basis. STK/CAT implements a number of standard pre- filters (out-of-date TLE, apogee/perigee, orbit path, and time) to reduce the overall computational complexity of this task. This allows current runs to be made on a 3.2 GHz, Pentium 4 with 2 GB of RAM in just 85 minutes. Efforts are currently underway to further improve the efficiency of STK/CATs filters to provide even more timely results.

Not only does STK/CAT calculate the minimum distance at the time of closest approach (TCA) for all conjunctions matching the user-specified criteria, it also provides calculations of the true probability and the maximum probability of collision. Because the minimum- distance method ignores position covariance and can lead to an exaggerated assessment of the true risk, CSSI believes the probability-based methods provide a more reasonable assessment of the true risk (Gist, 1999). For those cases where the actual covariances for the conjuncting objects are known, STK/CAT calculates the true probability of collision for that event.

For cases where no covariance data exists or data quality is insufficient, STK/CAT calculates the maximum probability of collision (Alfano, 2003). Unfortunately, the generation of TLEs does not produce covariance data and the maximum-probability method is, therefore, the only way in the absence of covariance data to generate a stochastic assessment of the probability of collision.

It is possible, however, to estimate the covariance associated with a given TLE by examining recent historical TLEs for the same object. The method currently under investigation by CSSI takes the historical TLEs for a particular object for the period of twice the prediction interval prior to the current date. A pair wise comparison of all TLEs is performed to generate predictions at the epoch of each TLE. The TLE associated with the epoch prediction time is considered the primary TLE and the relative position of the secondary TLE is calculated in the VNC (velocity-normal-conormal) coordinate system for the primary TLE. The VNC components are then plotted against the difference in epoch times to illustrate how prediction error actually, the difference between the two predictions grows over time in each dimension. The presumption here is that the actual prediction error at the TLE epoch is minimal. An example of such a plot is shown in Fig. 1.

Fig. 1. VNC Error vs. Delta Epoch Time

An estimate of the covariance value at the epoch and its growth over time can be developed by binning the VNC errors and calculating the sample mean and standard deviation for each bin. A time-varying bias can be calculated by simply interpolating between the mean bin values and then subtracted from the predicted position to produce a zero-bias mean. The resulting sample standard deviations (which are now smaller because we did not assume zero bias) then show the expected growth in prediction error.

CSSI currently plans to enhance the daily SOCRATES runs by generating pseudo- covariance data for each object, with the approach just described, and using that data within the true probability calculations in STK/CAT to provide a more realistic assessment of the probability of collision. Until then, satellite operators can selectively apply the same methodology for the specific objects in a particular conjunction to refine their estimate of the risk of collision. Future versions of STK/CAT will hopefully incorporate this capability to facilitate user analysis.
METHODOLOGY

Each SOCRATES run begins with the release of a new database from the Space Track web site. The data is first partitioned into two sets payloads only and all objects to facilitate setup for STK/CAT. Searches are currently limited to conjunctions involving payloads to give satellite operators an opportunity to plan or obtain planning services to move their satellites out of harm's way (if their satellite is maneuverable), or to take other appropriate measures. Since there currently is no way of knowing which payloads are still active, all payloads still on orbit are considered in the daily analysis. STK/CAT is set to look for all conjunctions which are within 1 km at the time of closest approach and reports minimum distance and the maximum probability for each conjunction. Maximum probability is calculated assuming an aspect ratio of 1 and using a developmental database of object sizes compiled from publicly available sources by The Aerospace Corporation. An effort is underway to provide an even more robust and extensively validated database of sizes (Isakowitz, 2004; Martin, 2000; Baker, 2002).

The actual STK/CAT runs for SOCRATES are kicked off at 0130 and 1230 UTC each day. Each run finishes in about 85 minutes and the conjunction advisory reports and associated data are uploaded to CelesTrak as soon as they are completed.

Each upload includes Top 10 lists sorted by maximum probability (see the example in Fig. 2) and minimum distance at TCA, together with a fully searchable set of all predicted conjunctions matching the input criteria. Searches can be conducted using common name or NORAD Catalog Number and sorted by maximum probability, minimum distance at TCA, or start time for the conjunction. Each report shows basic information defining which satellites are involved in the conjunction along with the specific time and circumstances of the event.

A typical report shows on the order of 250 predicted conjunctions within the 1-km computation threshold over the 7-day forecast period. Since the typical error at the end of the forecast period is more on the order of 10 km, CSSI plans to eventually open the computation threshold to 10 km, but preliminary tests show on the order 25,000 conjunctions within 10 km over a 7-day forecast period. Refinements in processing and associated benchmarking are being conducted prior to implementation.

Fig. 2. SOCRATES Top 10 Conjunctions by Maximum Probability

Perhaps the most powerful aspect of SOCRATES is the ability to immediately build a complete conjunction scenario for enhanced analysis at the push of a button. Each conjunction entry has an Analysis button which brings up a window like the one in Fig. 3. The window contains the basic information used to generate the report (currently only the TLEs) to allow the user to use the data within their preferred analysis software. If the user has STK, however, they can launch STK directly from their web browser and build the complete STK/CAT scenario on the fly, complete with stored viewpoints for threshold start, closest approach, and threshold end.

Fig. 3. SOCRATES Conjunction Analysis Screen

The ability to build a standard conjunction scenario at the push of a button enables the user to quickly conduct analysis rather than spending time collecting and formatting the data and then independently constructing what can often be a fairly complex scenario. For a typical satellite operator, they can now focus on inputting more refined data that might be available for their constellation (e.g., more precise ephemeris and covariance data), thus pro- viding a much better assessment of the risk than available solely from the TLEs. It also allows them to readily conduct maneuver planning, using tools such as STK/Astrogator or MATLAB, for maneuvers to further minimize the risk, should they determine such action is necessary.

The data for each conjunction is made as realistic as possible, using true-scale models of spacecraft and debris, along with attitude information, if available. CSSI is developing a database which will map each NORAD Catalog Number to a model and attitude profile for use in scenario generation. When attitude information is unknown, an attitude uncertainty sphere is put around the model with a diameter equal to the largest dimension of the object. Covariance data is notional, although current research efforts should provide pseudo- covariance data in the near future.

Soon, even non-STK users will be able to interactively view conjunctions reported in SOCRATES using the new AGI Viewer software, which is now available free of charge via AGIs web site (http://www.agi.com). Viewer Definition Format (VDF) files will be produced for the top conjunctions and then linked to that SOCRATES report. A screen shot from a sample VDF scenario is shown below in Fig. 4. SOCRATES users may then download the file and interactively manipulate the scenario (zoom, pan, and control animation time) to get a better visual impression of that conjunction. It is hoped that these VDF scenarios will help a wider audience develop a better appreciation of just how close a near miss can be.

Fig. 4. SOCRATES-Generated STK/CAT Scenario
CONCLUSIONS

This paper has shown how SOCRATES was developed to combine standard data products (NORAD TLEs), along with their associated orbital models (SGP4), in existing commercial- off-the shelf software (STK) to provide a regular situational report which can help satellite operators avoid undesired close approaches through advanced mission planning. It has also demonstrated how these products can be combined on the fly into a three-dimensional analysis framework to fully explore the circumstances of a particular conjunction and possible mitigation approaches.

Several advantages to the SOCRATES methodology should be readily apparent. The standardized systematic approach to collecting and processing the data ensures data validation, scenario development, and report generation are applied in a consistent manner. Centralized report generation and distributed advanced analysis maximizes computational efficiency by eliminating the need for each user to obtain full catalog data and run it against all of their satellites of interest. Plus, the simple web interface makes the somewhat complex and tedious task of collecting and formatting data to build the conjunction scenario(s) transparent and helps to eliminate the possibility of errors in that portion of the task, thus allowing the user to focus immediately on more detailed analysis. In addition to the obvious benefits SOCRATES provides to satellite operations, it is also hoped that these reports will help educate the public as to the circumstances and numbers of conjunctions occurring each day and demonstrate the feasibility of a regular process.
REFERENCES

  1. Hoots F.R. and Roehrich R.L., Spacetrack Report Number 3: Models for Propagation of NORAD Element Sets, 1980 December.
  2. Gist R.G. and Oltrogge D.L., Collision Vision: Covariance Modeling and Intersection Detection for Spacecraft Situational Awareness (AAS 99-351), AIAA/AAS Astrodynamics Specialist Conference, Girdwood, AK, 1999 August 1619.
  3. Alfano S., Relating Position Uncertainty to Maximum Conjunction Probability (AAS 03-548), AIAA/ AAS Astrodynamics Specialist Conference, Big Sky, MT, 2003 August 37.
  4. Isakowitz S.J., Hopkins J.B., and Hopkins J.P., Jr., International Reference Guide to Space Launch Systems, AIAA, Reston, Virginia, Fourth Edition, 2004.
  5. Martin D.H., Communication Satellites, The Aerospace Press, El Segundo, California, Fourth Edition, 2000.
  6. Baker D., ed., Janes Space Directory: 20022003, Janes Information Group Limited, Surrey, United Kingdom, Eighteenth Edition, 2002.

29 2006.

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