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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2026-11-07 05:49:56.577
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101163
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STARLINK-38392
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101216
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STARLINK-38483
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2.857
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1.047, 1.215, -2.365
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13.7052
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2026-11-07 05:53:03.261
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57470
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STARLINK-30186
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101242
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STARLINK-38250
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2.682
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-2.210, 0.903, -1.223
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12.4135
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2026-11-07 07:00:45.734
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57037
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OBJECT AK
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101285
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OBJECT C
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4.162
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0.059, -1.348, -3.937
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14.3924
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2026-11-07 07:20:57.930
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101163
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STARLINK-38392
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101216
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STARLINK-38483
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2.268
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1.116, -0.903, 1.756
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13.7053
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2026-11-07 09:39:55.356
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57470
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STARLINK-30186
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101242
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STARLINK-38250
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2.524
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-1.123, -1.340, -1.821
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12.4348
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2026-11-07 11:08:26.890
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101163
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STARLINK-38392
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101215
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STARLINK-38337
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2.430
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1.575, 0.845, 1.646
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13.7189
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2026-11-07 11:10:40.844
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57470
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STARLINK-30186
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101242
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STARLINK-38250
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1.689
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-0.408, -0.971, -1.320
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12.4403
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2026-11-07 12:41:27.551
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57470
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STARLINK-30186
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101242
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STARLINK-38250
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2.972
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0.168, 1.757, 2.391
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12.4458
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2026-11-07 13:24:58.784
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101163
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STARLINK-38392
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101215
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STARLINK-38337
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3.169
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1.796, 1.194, -2.322
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13.7053
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2026-11-07 13:37:24.707
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101283
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OBJECT A
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101284
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OBJECT B
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1.335
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-0.070, 0.032, -1.333
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0.0005
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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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