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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2026-10-06 18:16:51.505
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62273
↑
↻
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STARLINK-11333
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100768
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STARLINK-38450
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2.830
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-2.801, 0.223, -0.339
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12.8123
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2026-10-06 19:39:12.522
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64124
↑
↻
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STARLINK-11724
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100776
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STARLINK-38400
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3.391
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-1.510, 2.418, -1.836
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9.3063
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2026-10-06 19:48:37.621
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59711
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STARLINK-11082
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100777
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STARLINK-38409
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2.650
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2.444, -0.949, 0.389
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5.8230
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2026-10-06 20:34:32.106
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62225
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STARLINK-11471
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100765
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STARLINK-38446
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3.922
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3.594, 1.237, 0.968
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9.4670
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2026-10-06 21:17:46.237
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59768
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STARLINK-31826
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100766
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STARLINK-38438
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3.661
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3.335, 1.408, 0.548
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5.5503
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2026-10-06 22:35:15.822
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62059
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STARLINK-11454
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100778
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STARLINK-38420
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4.628
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4.435, 1.189, 0.584
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6.7717
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2026-10-07 00:13:52.485
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64124
↑
↻
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STARLINK-11724
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100776
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STARLINK-38400
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3.509
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0.682, 2.750, -2.071
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9.2620
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2026-10-07 01:36:16.065
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61693
↓
↻
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STARLINK-11366
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100771
↑
↻
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STARLINK-38339
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4.746
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3.052, -3.579, -0.634
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2.6443
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2026-10-07 01:40:34.116
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100512
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STARLINK-38362
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100773
↓
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STARLINK-38386
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3.727
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-1.469, -3.369, -0.617
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2.7796
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2026-10-07 03:42:34.013
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53665
↑
↺
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STARLINK-4334
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100761
↑
↻
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STARLINK-38402
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1.312
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1.312, -0.001, 0.003
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13.2116
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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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