Forecast of Conjunctions: 50 Latest Payloads vs. All (32410) Objects
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Time of Closest Approach (TCA), UTC
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NORAD ID 1
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Object Name 1
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NORAD ID 2
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Object Name 2
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Distance at TCA, km
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RIC Distance, km
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Rel.Speed
km/s
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2026-11-05 21:25:49.938
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45198
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STARLINK-1154
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101211
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STARLINK-38340
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4.257
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0.559, -3.567, 2.257
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8.2401
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2026-11-05 22:20:47.770
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67674
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COSMOS 2600
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101207
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STARLINK-38180
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3.894
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-1.787, -0.429, -3.433
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15.3187
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2026-11-05 22:47:14.750
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101164
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STARLINK-38387
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101217
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STARLINK-38146
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4.396
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0.556, 1.994, 3.878
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13.7176
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2026-11-06 00:18:17.314
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101164
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STARLINK-38387
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101217
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STARLINK-38146
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3.483
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0.572, 1.572, 3.055
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13.7176
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2026-11-06 00:41:41.294
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66176
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OBJECT B
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101241
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STARLINK-38240
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3.563
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2.104, 1.508, 2.448
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13.1666
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2026-11-06 01:49:19.875
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101164
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STARLINK-38387
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101217
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STARLINK-38146
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2.545
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0.586, 1.133, 2.202
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13.7176
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2026-11-06 03:20:22.433
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101164
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STARLINK-38387
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101217
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STARLINK-38146
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1.600
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0.601, 0.677, 1.319
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13.7176
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2026-11-06 03:31:53.018
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46141
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STARLINK-1596
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101240
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STARLINK-38458
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2.647
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2.307, 1.240, 0.384
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4.5527
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2026-11-06 04:27:49.401
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20718
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ARIANE 44L DEB (SPELDA)
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101210
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STARLINK-38125
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2.932
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2.882, 0.400, 0.357
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10.6533
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2026-11-06 04:51:24.987
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101164
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STARLINK-38387
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101217
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STARLINK-38146
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0.766
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0.616, 0.208, 0.405
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13.7176
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Our orbit propagation model is based on SGP4/SDP4 and uses data sourced from space-track.org. Object 1 and Object 2 are arranged by their NORAD ID (NORAD_CAT_ID).
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The "Within ellipsoid" option allows you to check if the predicted miss distance is within the RIC (Radial, In-track, Cross-track) ellipsoid, centered on either Object 1 or Object 2 at TCA, with specified semi-axis lengths.
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To exclude long-lasting conjunctions of ride-sharing satellites, you can use the "Relative Speed > 0.01 km/s" filter. Additionally, connected modules of ISS and CSS are not included in the forecast. Some ride-sharing satellites may also be temporarily excluded from the forecast.
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Gray background indicates a >1 km difference between the latest published position of a conjunction object and the position propagated from the TLE used for conjunction detection, indicating that the record may no longer be current.
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If comparison of the velocity vector and Keplerian orbital parameters from the latest published TLE with the corresponding values propagated from the TLE used for conjunction detection shows a deviation exceeding ±3× the background RMSE, indicating probable maneuvering, the following symbols identify the orbital parameter and direction of the probable change:
↑ ↓ - semimajor axis increase/decrease
↺ ↻ - inclination increase/decrease
→ ← - RAAN increase/decrease
↗ - probable maneuvering detected based on a propagated-versus-published velocity-vector difference exceeding 3× the background RMSE, while the semimajor axis, inclination, and RAAN deviations each remain within ±3× their respective background RMSEs.
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Please note that the "Selected Objects vs. All" option and Email Notifications are only available for registered users, with registration currently being free of charge.
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