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 03:24:12.494
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26512
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COSMOS 1249 COOLANT
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101002
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SDA-NG-T1TL-420
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4.635
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-4.631, 0.088, -0.171
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12.7254
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2026-10-21 03:30:43.650
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61776
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OBJECT AT
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101018
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STARLINK-38257
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4.051
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-0.800, -2.623, 2.982
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11.5817
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2026-10-21 04:47:47.124
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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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4.818
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-4.797, -0.439, -0.105
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3.5584
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2026-10-21 06:28:55.451
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69583
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OBJECT B
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100991
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SDA-NG-T1TL-409
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4.859
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-2.157, -4.226, -1.048
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3.5657
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2026-10-21 07:06:08.480
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45044
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STARLINK-1132
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101027
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STARLINK-38455
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1.607
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-1.578, -0.155, 0.257
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13.2932
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2026-10-21 07:09:56.613
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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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3.295
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2.769, 0.582, -1.688
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13.9428
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2026-10-21 07:32:38.128
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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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1.117
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0.787, 0.565, 0.556
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10.3758
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2026-10-21 07:36:27.267
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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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2.758
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-0.110, -2.142, 1.734
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9.2799
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2026-10-21 07:42:21.782
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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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4.247
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-3.432, 0.317, 2.481
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14.6019
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2026-10-21 08:01:50.610
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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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3.807
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-3.442, 1.599, -0.296
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2.7041
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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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