Forecast of Conjunctions: 50 Latest Payloads vs. All (31718) 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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2026-10-05 00:26:55.393
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60929
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STARLINK-11240
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100775
↑
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STARLINK-38442
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4.479
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4.343, -1.054, 0.290
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4.0076
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2026-10-05 01:43:12.179
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59765
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STARLINK-11106
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100778
↑
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STARLINK-38420
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3.295
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-3.287, -0.117, 0.203
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13.4064
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2026-10-05 02:43:35.268
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62405
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OBJECT AE
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100865
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STARLINK-40090
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4.179
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1.857, -3.690, -0.635
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2.6473
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2026-10-05 02:59:53.296
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60906
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STARLINK-11264
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100778
↑
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STARLINK-38420
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3.538
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-0.260, -2.251, 2.717
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11.8523
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2026-10-05 03:41:30.293
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62402
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DJIBOUTI-1B
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100765
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STARLINK-38446
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3.496
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3.203, 1.113, 0.848
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9.2642
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2026-10-05 04:00:43.506
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59765
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STARLINK-11106
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100778
↑
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STARLINK-38420
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1.725
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-1.539, 0.384, 0.677
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13.4164
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2026-10-05 06:49:06.759
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60906
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STARLINK-11264
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100778
↑
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STARLINK-38420
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3.795
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-3.787, 0.160, 0.191
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11.8173
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2026-10-05 07:20:12.401
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48881
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STARLINK-3005
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100829
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STRIX-12
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4.428
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-2.618, 1.388, -3.291
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13.9587
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2026-10-05 07:21:32.660
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45397
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STARLINK-1307
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100763
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STARLINK-38444
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1.927
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1.534, -0.669, 0.955
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12.5670
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2026-10-05 07:31:00.677
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51775
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STARLINK-3620
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100874
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STARLINK-40078
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2.500
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-1.762, -1.427, -1.053
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9.1730
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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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