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 12:57:13.885
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12682
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SL-8 R/B
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100991
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SDA-NG-T1TL-409
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4.313
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-4.179, 0.281, -1.030
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14.2020
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2026-10-24 13:40:11.140
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29962
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FENGYUN 1C DEB
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100989
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SDA-NG-T1TL-407
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2.175
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1.805, 0.662, 1.015
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12.3718
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2026-10-24 13:48:13.603
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20626
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SL-16 DEB
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100992
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SDA-NG-T1TL-410
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1.887
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0.468, 0.924, 1.577
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12.7591
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2026-10-24 13:48:35.058
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31738
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FENGYUN 1C DEB
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100990
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SDA-NG-T1TL-408
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1.719
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1.179, 0.040, -1.251
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14.7418
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2026-10-24 13:48:49.564
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31738
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FENGYUN 1C DEB
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100989
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SDA-NG-T1TL-407
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4.651
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4.405, 0.041, 1.493
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14.7449
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2026-10-24 13:51:56.416
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12728
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COSMOS 1275 DEB
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100987
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SDA-NG-T1TL-405
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1.436
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0.878, -0.297, -1.098
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14.2557
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2026-10-24 13:54:37.533
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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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4.735
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-2.801, -2.483, 2.900
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11.7061
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2026-10-24 13:56:10.533
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42206
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COSMOS 1275 DEB
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100985
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SDA-NG-T1TL-403
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3.079
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-3.025, -0.109, -0.562
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14.4401
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2026-10-24 14:01:44.372
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63556
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STARLINK-11626
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101025
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STARLINK-38465
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4.689
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2.659, -2.334, 3.077
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12.2606
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2026-10-24 14:06:38.357
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61747
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POLYTECH UNIVERSE-4
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101031
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DRAGON CRS-35
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3.820
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-1.347, 1.226, 3.358
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14.3870
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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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