Forecast of Conjunctions: 50 Latest Payloads vs. All (31369) 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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2026-09-20 18:04:27.138
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100504
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STARLINK-38356
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100562
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ELECTRON SECOND STAGE
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4.038
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-3.803, -0.848, 1.059
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12.4117
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2026-09-20 18:31:21.798
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19245
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P/L 153 DEB
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100690
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FLEX
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3.985
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-2.491, 0.743, -3.020
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14.4624
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2026-09-20 18:37:34.848
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66216
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STARLINK-35709
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100562
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ELECTRON SECOND STAGE
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3.299
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2.891, -1.380, -0.788
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7.7009
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2026-09-20 18:53:26.063
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64483
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STARLINK-34420
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100688
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SES MPOWER-F13
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4.881
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-0.732, -4.155, 2.455
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9.4233
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2026-09-20 19:10:01.538
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100184
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STARLINK-37207
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100618
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STARLINK-38414
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3.352
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-3.235, -0.366, -0.795
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13.9885
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2026-09-20 19:52:03.308
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58672
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STARLINK-31104
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100628
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STARLINK-38348
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0.542
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-0.538, -0.037, 0.048
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12.2211
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2026-09-20 20:02:53.100
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63295
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OBJECT E
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100614
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SPECTRUM
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3.765
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-1.730, 2.826, 1.789
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8.1255
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2026-09-20 21:22:46.408
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27769
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SL-8 DEB
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100611
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PLATFORM-6
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4.344
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-2.647, -0.722, 3.367
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14.7666
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2026-09-20 21:38:45.478
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53259
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STARLINK-4140
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100562
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ELECTRON SECOND STAGE
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3.002
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2.499, -1.476, -0.766
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7.0624
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2026-09-20 22:08:13.886
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35248
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CZ-4C DEB
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100639
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STARLINK-38411
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2.241
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-0.742, 0.768, -1.970
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14.3433
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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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