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 04:02:45.935
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29996
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FENGYUN 1C DEB
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100994
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SDA-NG-T1TL-412
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4.334
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3.897, 0.284, -1.876
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14.5339
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2026-10-24 04:11:33.385
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10020
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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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1.202
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-1.027, -0.173, 0.600
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14.2056
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2026-10-24 04:26:53.826
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100696
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QIANFAN-243
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101001
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SDA-NG-T1TL-419
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4.187
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-4.001, -0.104, 1.230
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14.7042
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2026-10-24 04:50:36.339
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31160
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FENGYUN 1C DEB
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101001
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SDA-NG-T1TL-419
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4.844
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-1.116, -0.518, -4.685
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14.6310
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2026-10-24 04:52:56.354
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100075
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PRAETORIAN SDA_517
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101000
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SDA-NG-T1TL-418
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3.401
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2.110, 2.571, 0.708
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3.9235
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2026-10-24 05:09:13.487
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12728
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COSMOS 1275 DEB
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100992
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SDA-NG-T1TL-410
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1.312
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1.195, -0.143, -0.523
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14.2546
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2026-10-24 05:17:18.344
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42206
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COSMOS 1275 DEB
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100983
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SDA-NG-T1TL-401
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4.652
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-2.606, 0.782, 3.774
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14.4398
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2026-10-24 05:36:47.864
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28612
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NIMBUS 2 DEB
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100983
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SDA-NG-T1TL-401
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4.699
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-1.263, -4.457, 0.788
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2.5616
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2026-10-24 05:43:39.393
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45399
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STARLINK-1255
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101020
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STARLINK-38466
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4.079
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4.014, 0.713, 0.140
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2.8978
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2026-10-24 05:44:52.162
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29996
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FENGYUN 1C DEB
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100997
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SDA-NG-T1TL-415
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4.595
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3.576, 0.434, -2.854
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14.5367
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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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