Forecast of Conjunctions: 50 Latest Payloads vs. All (31718) 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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2026-10-06 01:59:35.237
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63011
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STARLINK-11580
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100779
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STARLINK-38385
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3.832
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3.831, -0.082, -0.034
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6.1904
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2026-10-06 02:57:43.209
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60994
↑
↺
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STARLINK-11267
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100777
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STARLINK-38409
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4.211
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3.430, 1.885, -1.552
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9.7632
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2026-10-06 03:36:55.954
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60038
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STARLINK-11129
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100763
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STARLINK-38444
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4.348
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3.785, 1.514, -1.514
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10.8612
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2026-10-06 03:37:33.706
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64124
↑
↺
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STARLINK-11724
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100768
↓
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STARLINK-38450
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1.403
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-1.393, 0.133, 0.103
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9.4469
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2026-10-06 05:09:07.623
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64124
↑
↺
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STARLINK-11724
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100768
↓
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STARLINK-38450
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3.186
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-0.650, -2.463, -1.913
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9.4324
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2026-10-06 06:14:00.547
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62987
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STARLINK-11539
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100779
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STARLINK-38385
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2.309
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1.697, 1.081, 1.132
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11.1213
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2026-10-06 06:26:13.956
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60040
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STARLINK-11122
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100770
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STARLINK-38301
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4.268
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-1.917, 2.693, -2.701
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10.8834
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2026-10-06 07:29:12.522
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61692
↓
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STARLINK-11315
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100775
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STARLINK-38442
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4.703
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4.449, -1.500, -0.280
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2.7485
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2026-10-06 09:15:56.988
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44949
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STARLINK-1122
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100778
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STARLINK-38420
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3.902
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3.385, -1.877, -0.494
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3.8953
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2026-10-06 09:45:42.305
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63672
↑
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STARLINK-11644
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100768
↓
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STARLINK-38450
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3.106
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-0.001, -2.930, -1.032
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5.1044
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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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