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 14:11:46.919
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100696
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QIANFAN-243
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100985
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SDA-NG-T1TL-403
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4.942
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4.673, -0.130, 1.603
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14.7002
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2026-10-21 14:36:02.839
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32461
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FENGYUN 1C DEB
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100995
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SDA-NG-T1TL-413
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4.562
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3.912, 1.872, -1.417
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9.2310
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2026-10-21 14:52:47.082
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16385
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COSMOS 1375 DEB
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100989
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SDA-NG-T1TL-407
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3.362
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3.246, 0.854, 0.186
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2.6985
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2026-10-21 15:15:07.659
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2121
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OV1-4
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100988
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SDA-NG-T1TL-406
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4.088
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-2.992, -1.871, 2.064
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10.9902
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2026-10-21 15:30:26.452
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15517
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SL-14 R/B
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100991
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SDA-NG-T1TL-409
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0.815
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-0.633, 0.462, -0.225
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6.4620
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2026-10-21 15:32:02.242
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100064
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PRAETORIAN SDA_506
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100987
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SDA-NG-T1TL-405
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4.746
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0.894, 4.492, -1.242
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3.9242
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2026-10-21 15:48:14.857
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13416
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COSMOS 1372 FUEL CORE
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100989
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SDA-NG-T1TL-407
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4.488
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1.839, -1.340, 3.868
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13.9315
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2026-10-21 15:55:30.869
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100696
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QIANFAN-243
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100986
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SDA-NG-T1TL-404
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4.437
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4.363, -0.065, 0.801
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14.7004
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2026-10-21 17:19:16.265
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100989
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SDA-NG-T1TL-407
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270204
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TBA - TO BE ASSIGNED
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3.888
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-2.441, -0.723, -2.939
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14.3245
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2026-10-21 17:21:40.511
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48824
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THOR ABLESTAR DEB
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101001
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SDA-NG-T1TL-419
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4.684
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1.355, -1.491, 4.229
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13.8885
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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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