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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Notice: Current orbital data from space-track.org is unavailable. Forecast results may be incomplete or outdated.
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2026-10-25 18:09:43.671
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19324
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COSMOS 1959
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100984
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SDA-NG-T1TL-402
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2.564
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-2.196, -0.283, -1.293
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14.4185
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2026-10-25 18:11:48.134
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65584
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PRAETORIAN SDA_621
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100995
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SDA-NG-T1TL-413
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3.261
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-2.748, 1.500, -0.911
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7.6470
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2026-10-25 18:21:37.443
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59714
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STARLINK-11094
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101021
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STARLINK-38477
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3.036
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-0.314, -1.543, -2.595
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13.2302
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2026-10-25 18:23:12.787
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48957
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HAWK-3A
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101010
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STARLINK-38468
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4.797
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1.429, 3.295, 3.180
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10.6933
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2026-10-25 19:31:43.775
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30212
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FENGYUN 1C DEB
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100983
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SDA-NG-T1TL-401
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4.852
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-0.667, 4.738, -0.808
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2.5557
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2026-10-25 20:04:19.384
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6277
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SL-8 DEB
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100988
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SDA-NG-T1TL-406
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1.135
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0.752, 0.598, -0.604
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10.4957
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2026-10-25 20:15:46.843
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19325
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SL-8 R/B
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100995
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SDA-NG-T1TL-413
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3.605
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-3.028, 0.271, -1.938
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14.6258
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2026-10-25 20:35:32.368
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19367
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COSMOS 397 DEB *
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100997
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SDA-NG-T1TL-415
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4.294
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0.479, 2.295, -3.598
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12.4444
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2026-10-25 20:54:36.867
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42506
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THORAD AGENA D DEB
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100991
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SDA-NG-T1TL-409
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4.450
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-4.269, 0.096, -1.253
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14.6940
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2026-10-25 21:03:59.687
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42206
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COSMOS 1275 DEB
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100992
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SDA-NG-T1TL-410
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4.503
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-4.487, -0.068, -0.382
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14.4417
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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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