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 14:35:43.085
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100184
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STARLINK-37207
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100635
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STARLINK-38413
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4.078
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-3.635, 0.768, 1.681
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14.0271
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2026-09-20 14:59:50.209
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69998
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STARLINK-38086
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100628
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STARLINK-38348
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3.647
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-3.603, -0.229, -0.514
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14.0489
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2026-09-20 15:15:20.313
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45685
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STARLINK-1402
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100640
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STARLINK-38412
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4.148
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-2.151, -2.834, -2.133
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9.2636
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2026-09-20 16:53:02.171
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59350
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STARLINK-31593
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100562
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ELECTRON SECOND STAGE
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2.401
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-0.313, 2.167, -0.985
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6.1041
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2026-09-20 17:06:41.548
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47746
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STARLINK-2160
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100636
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STARLINK-38170
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1.929
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-1.104, -1.150, -1.088
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11.2344
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2026-09-20 17:26:08.348
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63921
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CZ-6A R/B
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100690
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FLEX
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1.180
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1.180, -0.003, -0.027
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14.7927
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2026-09-20 17:37:07.060
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100247
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STARLINK-38246
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100618
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STARLINK-38414
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3.022
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-2.995, -0.319, 0.241
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9.3087
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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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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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