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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2026-10-04 23:43:21.592
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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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4.896
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4.621, -1.594, -0.273
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2.6380
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2026-10-05 00:10:27.362
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59949
↓
↻
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STARLINK-11138
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100771
↑
←
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STARLINK-38339
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3.874
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3.768, 0.586, -0.685
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11.6859
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2026-10-05 00:16:25.692
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60992
↑
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STARLINK-11282
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100761
↑
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STARLINK-38402
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4.228
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3.838, 1.387, -1.108
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9.5858
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2026-10-05 00:31:38.097
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59950
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STARLINK-11130
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100774
↑
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STARLINK-38447
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3.703
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3.486, 0.811, -0.949
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11.6837
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2026-10-05 00:47:33.896
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45048
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STARLINK-1134
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100769
↑
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STARLINK-38388
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3.727
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3.264, -1.171, 1.365
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11.6487
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2026-10-05 01:17:49.029
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62474
↑
↻
→
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STARLINK-11502
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100765
↑
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STARLINK-38446
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4.616
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2.166, 3.933, -1.070
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4.0229
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2026-10-05 05:15:24.998
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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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4.148
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-3.842, 1.256, -0.928
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9.1721
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2026-10-05 06:00:35.942
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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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2.256
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-0.866, -1.677, -1.236
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9.1665
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2026-10-05 06:32:57.991
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61878
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STARLINK-11314
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100773
↑
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STARLINK-38386
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4.264
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3.107, 2.871, -0.537
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2.7863
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2026-10-05 06:35:29.862
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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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4.677
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-4.215, 1.171, 1.656
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12.5548
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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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