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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2026-10-08 01:20:48.185
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67688
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HMU-SAT2
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100875
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STARLINK-40103
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4.332
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-3.925, 1.390, -1.197
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10.0721
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2026-10-08 02:43:35.258
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60728
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STARLINK-11249
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100777
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STARLINK-38409
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2.900
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2.464, -1.125, -1.035
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10.4081
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2026-10-08 03:31:46.581
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1521
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THOR ABLESTAR DEB
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100792
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HULIANWANG DIGUI-206
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3.731
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3.723, 0.160, 0.186
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11.5508
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2026-10-08 03:48:22.738
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61575
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STARLINK-11376
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100779
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STARLINK-38385
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3.255
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2.556, -1.641, 1.168
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8.9058
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2026-10-08 04:08:27.688
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68827
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COSMOS 2616
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100878
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STARLINK-40076
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2.981
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-2.835, -0.667, -0.637
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10.6420
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2026-10-08 05:03:09.853
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36729
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FENGYUN 1C DEB
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100824
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YAOGAN-40 O4B
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2.603
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-2.537, -0.082, -0.578
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14.7552
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2026-10-08 05:04:32.854
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100823
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YAOGAN-40 04A
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270414
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TBA - TO BE ASSIGNED
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4.743
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-4.680, -0.115, 0.762
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14.6989
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2026-10-08 06:38:11.961
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55864
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CZ-6A DEB
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100825
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YAOGAN-40 O4C
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2.208
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-2.053, -0.341, -0.739
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13.4716
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2026-10-08 07:55:02.996
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61157
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CZ-6A DEB
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100825
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YAOGAN-40 O4C
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1.229
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1.027, -0.036, -0.673
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14.8479
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2026-10-08 08:28:05.997
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31459
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FENGYUN 1C DEB
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100823
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YAOGAN-40 04A
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2.466
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-2.465, 0.025, -0.026
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12.8062
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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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