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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2026-11-04 10:21:45.762
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100875
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STARLINK-40103
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101180
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STARLINK-38430
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2.830
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1.082, 2.448, 0.920
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5.4106
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2026-11-04 11:32:28.127
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67674
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COSMOS 2600
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101212
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STARLINK-37678
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0.735
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-0.725, -0.013, -0.116
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15.3327
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2026-11-04 13:03:17.217
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67674
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COSMOS 2600
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101211
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STARLINK-38340
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3.750
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1.095, -0.415, -3.562
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15.3318
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2026-11-04 14:04:28.502
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62617
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SCOT-1 (SCOT)
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101212
↑
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STARLINK-37678
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4.030
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3.990, 0.134, -0.552
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14.9842
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2026-11-04 20:17:05.963
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101166
↑
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STARLINK-38401
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101222
↑
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STARLINK-38489
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2.454
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-1.555, -0.868, 1.688
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13.7039
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2026-11-04 20:25:34.094
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4991
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THORAD AGENA D DEB
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101188
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HULIANWANG DIGUI 226
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3.695
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-3.579, 0.241, -0.887
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14.1108
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2026-11-04 20:58:58.364
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6765
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THORAD AGENA D DEB
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101188
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HULIANWANG DIGUI 226
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4.860
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-2.590, 2.612, -3.177
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11.3158
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2026-11-04 21:48:08.456
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101166
↑
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STARLINK-38401
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101222
↑
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STARLINK-38489
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4.074
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-1.088, 1.795, -3.492
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13.7036
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2026-11-04 22:01:34.630
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45764
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STARLINK-1502
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101202
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STARLINK-38336
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3.874
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-2.518, 2.258, 1.889
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9.9223
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2026-11-04 22:11:52.953
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4991
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THORAD AGENA D DEB
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101188
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HULIANWANG DIGUI 226
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4.779
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-3.692, -0.817, 2.921
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14.1138
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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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