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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2026-10-22 01:34:12.933
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66841
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STARLINK-35715
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100968
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NEONSAT-06
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4.473
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3.183, -2.119, -2.320
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11.1689
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2026-10-22 02:10:11.162
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13416
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COSMOS 1372 FUEL CORE
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100993
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SDA-NG-T1TL-411
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4.142
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0.803, -1.342, 3.835
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13.9174
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2026-10-22 03:13:08.144
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64989
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COSMOS 970 DEB
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100992
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SDA-NG-T1TL-410
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3.680
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3.676, 0.061, 0.160
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14.1671
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2026-10-22 03:44:24.139
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28983
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PEGASUS R/B
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101026
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STARLINK-38484
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3.600
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-0.895, -3.150, 1.496
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5.2004
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2026-10-22 04:01:50.592
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100696
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QIANFAN-243
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100991
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SDA-NG-T1TL-409
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4.988
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2.674, -0.348, 4.196
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14.7017
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2026-10-22 05:00:48.536
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47736
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STARLINK-2147
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101028
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STARLINK-38469
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3.387
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2.751, 1.343, 1.450
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11.2919
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2026-10-22 05:26:42.655
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28355
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SL-16 DEB
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100992
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SDA-NG-T1TL-410
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4.068
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2.225, 2.339, -2.474
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10.8203
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2026-10-22 05:45:29.686
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100696
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QIANFAN-243
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100992
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SDA-NG-T1TL-410
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4.109
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2.307, 0.285, -3.389
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14.7019
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2026-10-22 05:51:23.632
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22398
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SL-16 DEB
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100999
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SDA-NG-T1TL-417
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1.640
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-0.872, 0.417, -1.325
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14.0337
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2026-10-22 06:01:48.358
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37236
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COSMOS 951 DEB
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100999
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SDA-NG-T1TL-417
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3.073
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-1.489, -1.167, 2.421
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13.2900
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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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