Space Debris Tracking Tools: Researcher’s Guide

For researchers needing to track space debris, the practical choice depends on your data needs: use the ESA-DISCOS database for catalogued objects, the NASA Orbital Debris Program Office models for statistical populations, and open-source tools like GMAT or Orekit for orbit propagation. This guide explains the main tools, how to select one, and common pitfalls.

Formula

The calculator above estimates the orbital speed of a debris object assuming a circular orbit. The formula is:

v = (2π × (R + d)) / (t × 60)

• v = orbital speed in km/s
• R = Earth’s radius (6371 km)
• d = altitude above Earth’s surface in km
• t = orbital period in minutes

This is a simplified version of the vis-viva equation for circular orbits. For elliptical orbits, the speed varies along the path.

Worked Example

Using the default values: altitude = 500 km, period = 90 minutes.

1. Radius = 6371 + 500 = 6871 km
2. Circumference = 2π × 6871 ≈ 43,173 km
3. Time in seconds = 90 × 60 = 5400 s
4. Speed = 43,173 / 5400 ≈ 7.99 km/s

The calculator shows 7.99 km/s, matching the typical speed for low Earth orbit debris.

Main Tracking Tools

Researchers generally use three categories of tools:

• Catalogues: ESA-DISCOS, Space-Track.org (US Space Command), and the Chinese and Russian equivalents provide positional data for tracked objects.
• Statistical models: NASA’s ORDEM and ESA’s MASTER simulate the debris environment for risk assessment and mission planning.
• Propagation software: GMAT, Orekit, and STK (commercial) compute future positions from orbital elements.

How to Choose the Right Tool

Your choice depends on your research question:

• If you need to know where a specific object is now, use a catalogue with TLEs (two-line element sets).
• If you’re studying collision risk for a satellite, use ORDEM or MASTER to get flux estimates.
• If you’re simulating a mission or avoidance maneuver, use a propagator like GMAT.

For most academic work, starting with Space-Track.org (free registration) and GMAT (open source) covers basic needs.

Common Problems and Misconceptions

A frequent mistake is treating TLEs as highly accurate. TLEs have uncertainties of kilometers, not meters. Also, the number of tracked objects (about 40,000) is far smaller than the estimated 130 million debris pieces larger than 1 mm. Models are needed for the untracked population.

Another issue: different catalogues may give different positions for the same object due to different sensors and update frequencies. Always note the epoch (time) of the data.

Costs and Accessibility

Many tools are free or low-cost for researchers:

• Space-Track.org: free with registration
• ESA-DISCOS: free for research, requires request
• NASA ORDEM: free download
• GMAT: open source
• Orekit: open source (Java)
• STK: commercial, but free educational licenses exist

Limitations and Accuracy

All models have limits. ORDEM and MASTER rely on assumptions about breakup events and solar activity. Propagation accuracy degrades with time, especially for low-altitude objects due to atmospheric drag. For high-precision work (e.g., conjunction analysis), use specialized services like ESA’s Collision Avoidance service.

Frequently Asked Questions

Is Space-Track.org really free?

Yes, for individuals and institutions that register and agree to the terms. It provides TLEs for all catalogued objects.

What is the difference between TLE and ephemeris?

A TLE is a simplified set of orbital elements used with the SGP4 propagator. An ephemeris is a table of precise positions at specific times, often more accurate for short-term predictions.

Can I use these tools for real-time tracking?

No. Catalogues update TLEs every few hours or days. For real-time tracking, you need your own radar or optical sensors, or access to a sensor network.

Which tool is best for a beginner?

Start with Space-Track.org for data and GMAT for propagation. Both have tutorials and are widely used in academic literature.

How do I cite these tools in a paper?

Check the specific tool’s documentation. Generally, cite the data source (e.g., US Space Command) and the software version (e.g., GMAT R2022a).

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in t | Observation time | min | 90 | 1 | 1440
in d | Distance to object | km | 500 | 100 | 40000
out v | Relative speed | km/s | (2 * pi * (6371 + d)) / (t * 60) | 2
out period | Orbit period | min | t | 0