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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2026-10-21 04:47:47.192
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69584
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OBJECT C
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100984
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SDA-NG-T1TL-402
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4.969
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-4.777, -1.329, -0.325
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3.5585
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2026-10-21 07:09:56.620
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13416
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COSMOS 1372 FUEL CORE
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100986
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SDA-NG-T1TL-404
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3.290
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2.762, 0.582, -1.691
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13.9428
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2026-10-21 07:32:38.156
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54270
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CZ-6A DEB
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100999
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SDA-NG-T1TL-417
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0.942
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0.797, 0.358, 0.351
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10.3758
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2026-10-21 07:36:27.324
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32461
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FENGYUN 1C DEB
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101003
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SDA-NG-T1TL-421
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3.437
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-0.072, -2.670, 2.163
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9.2799
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2026-10-21 07:42:21.790
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30393
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FENGYUN 1C DEB
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100987
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SDA-NG-T1TL-405
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4.220
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-3.419, 0.312, 2.454
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14.6019
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2026-10-21 08:01:50.649
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11080
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NIMBUS 7
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100983
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SDA-NG-T1TL-401
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3.602
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-3.418, 1.119, -0.208
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2.7041
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2026-10-21 08:41:55.331
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3583
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COSMOS 249 DEB
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100995
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SDA-NG-T1TL-413
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3.240
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-0.291, 3.074, -0.981
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3.8213
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2026-10-21 08:58:41.116
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45578
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STARLINK-1331
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101015
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STARLINK-38475
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4.370
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-1.605, 3.762, 1.540
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5.8640
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2026-10-21 09:25:23.028
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30393
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FENGYUN 1C DEB
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100989
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SDA-NG-T1TL-407
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4.037
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-3.803, -0.157, -1.345
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14.6040
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2026-10-21 09:25:39.671
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38119
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FENGYUN 1C DEB
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100990
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SDA-NG-T1TL-408
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4.583
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-3.955, -0.187, -2.307
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14.6419
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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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