Forecast of Conjunctions: 50 Latest Payloads vs. All (32067) 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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2026-10-10 22:08:03.720
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45746
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STARLINK-1504
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100777
↑
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STARLINK-38409
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2.627
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-0.150, 1.570, 2.101
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12.3102
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2026-10-10 22:37:10.983
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30879
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FENGYUN 1C DEB
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100892
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CRIMSON-1
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2.356
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1.752, 0.348, 1.536
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14.9053
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2026-10-10 23:18:54.709
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61462
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CZ-6A DEB
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100823
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YAOGAN-40 04A
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4.515
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-2.462, -0.910, 3.673
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14.4634
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2026-10-10 23:51:25.559
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67091
↓
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STARLINK-36097
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100775
↑
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STARLINK-38442
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3.404
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-1.187, -2.024, 2.466
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11.8948
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2026-10-11 01:57:33.174
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45746
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STARLINK-1504
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100777
↑
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STARLINK-38409
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3.707
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3.471, 0.785, -1.038
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12.3079
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2026-10-11 02:25:38.957
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35625
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IRIDIUM 33 DEB
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100825
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YAOGAN-40 O4C
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3.083
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-2.936, -0.083, -0.937
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14.7653
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2026-10-11 02:25:39.657
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43822
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OBJECT BS
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100899
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JACK-006
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1.281
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0.085, 1.255, -0.242
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2.8657
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2026-10-11 03:48:34.556
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60069
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STARLINK-11171
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100778
↑
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STARLINK-38420
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3.489
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3.093, -0.784, -1.413
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13.4638
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2026-10-11 03:50:13.451
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58848
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AAC-HSI-SAT3
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100941
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RADIX-A
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3.885
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1.698, -3.467, 0.437
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1.8146
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2026-10-11 04:37:50.514
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23407
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SL-16 DEB
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100796
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HULIANWANG DIGUI-210
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4.788
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1.735, 3.607, 2.628
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8.5828
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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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