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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2026-10-24 15:27:46.994
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64373
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STARLINK-11748
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101025
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STARLINK-38465
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2.678
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-2.420, -0.967, 0.614
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8.2809
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2026-10-24 15:30:00.068
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100073
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PRAETORIAN SDA_515
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100983
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SDA-NG-T1TL-401
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4.553
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4.135, 1.837, 0.505
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3.9265
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2026-10-24 15:30:18.557
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62099
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STARLINK-11380
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101025
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STARLINK-38465
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3.354
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-3.016, 1.389, -0.474
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4.9540
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2026-10-24 15:50:28.325
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67093
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STARLINK-35784
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101142
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XIGUANG-4 01
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4.811
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-2.724, -3.096, 2.478
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9.5027
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2026-10-24 16:11:57.774
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62554
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STARLINK-11538
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101018
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STARLINK-38257
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3.821
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-3.633, 0.772, 0.899
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11.6835
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2026-10-24 16:23:17.477
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31738
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FENGYUN 1C DEB
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100991
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SDA-NG-T1TL-409
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4.666
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4.661, -0.072, -0.196
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14.7470
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2026-10-24 16:59:21.527
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64373
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STARLINK-11748
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101025
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STARLINK-38465
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4.007
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-1.694, 3.063, -1.950
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8.2649
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2026-10-24 17:01:54.755
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62099
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STARLINK-11380
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101025
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STARLINK-38465
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2.302
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-2.282, -0.284, 0.094
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4.9394
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2026-10-24 17:04:52.778
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60184
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STARLINK-11187
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101023
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STARLINK-38463
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3.182
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0.157, -2.985, 1.090
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5.2719
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2026-10-24 17:05:36.602
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64374
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STARLINK-11739
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101028
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STARLINK-38469
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3.181
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-3.075, -0.691, 0.431
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8.1975
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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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