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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2026-10-18 18:16:50.114
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5129
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THORAD AGENA D DEB
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100987
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SDA-NG-T1TL-405
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2.831
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-2.056, -0.060, -1.945
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14.7899
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2026-10-18 18:17:00.667
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5129
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THORAD AGENA D DEB
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100986
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SDA-NG-T1TL-404
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4.750
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-0.701, -0.112, -4.696
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14.7908
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2026-10-18 18:24:15.017
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100697
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QIANFAN-244
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101002
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SDA-NG-T1TL-420
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2.965
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2.291, -0.164, 1.875
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14.6990
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2026-10-18 18:54:48.086
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12284
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DELTA 1 DEB
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101000
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SDA-NG-T1TL-418
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3.466
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2.957, 0.037, 1.807
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14.7091
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2026-10-18 18:54:58.741
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12284
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DELTA 1 DEB
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100999
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SDA-NG-T1TL-417
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3.611
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2.878, -0.061, -2.181
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14.7086
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2026-10-18 18:59:48.635
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28521
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COSMOS 2414
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101002
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SDA-NG-T1TL-420
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3.574
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3.367, 0.645, 1.009
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12.4733
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2026-10-18 19:16:47.678
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11080
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NIMBUS 7
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100989
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SDA-NG-T1TL-407
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4.800
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-3.844, 2.813, -0.594
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3.0691
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2026-10-18 19:18:15.773
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17108
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COSMOS 1375 DEB
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100992
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SDA-NG-T1TL-410
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3.791
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-1.303, 1.202, 3.351
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13.8938
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2026-10-18 20:07:57.330
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100697
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QIANFAN-244
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101003
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SDA-NG-T1TL-421
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2.174
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1.953, 0.087, -0.952
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14.6994
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2026-10-18 20:37:30.439
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12284
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DELTA 1 DEB
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101003
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SDA-NG-T1TL-421
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1.813
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1.804, 0.001, 0.182
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14.7096
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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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