Forecast of Conjunctions: 50 Latest Payloads vs. All (31338) 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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2026-09-23 18:18:09.653
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23317
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OKEAN 4
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100611
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PLATFORM-6
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3.054
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-2.939, 0.005, 0.830
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15.1233
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2026-09-23 18:54:01.494
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12266
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DELTA 1 DEB
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100690
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FLEX
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4.802
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4.207, -1.791, 1.469
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9.3075
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2026-09-23 19:54:13.361
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23317
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OKEAN 4
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100611
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PLATFORM-6
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3.574
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-3.401, 0.015, -1.099
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15.1238
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2026-09-23 20:00:40.209
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30218
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FENGYUN 1C DEB
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100689
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SENTINEL-3C
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3.867
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3.123, -2.173, -0.694
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4.7368
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2026-09-23 20:20:23.595
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69996
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STARLINK-38085
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100789
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ZK-1A / RB
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4.075
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4.015, -0.357, -0.601
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13.6053
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2026-09-23 20:59:32.951
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55741
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STARLINK-5592
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100746
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STRIX-10
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1.564
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1.428, 0.376, 0.515
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12.2941
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2026-09-23 21:18:39.694
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13484
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COSMOS 1275 DEB
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100694
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QIANFAN-241
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4.912
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-4.774, 0.736, -0.890
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11.3557
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2026-09-23 21:23:36.632
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31388
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FENGYUN 1C DEB
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100692
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QIANFAN-239
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2.502
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0.857, -1.199, 2.022
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12.7050
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2026-09-23 21:43:43.506
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59911
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TIANQI 27
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100695
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QIANFAN-242
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3.313
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3.174, 0.377, 0.871
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13.5785
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2026-09-23 22:08:55.237
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64645
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CZ-6A DEB
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100692
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QIANFAN-239
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4.448
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-0.556, 0.474, 4.388
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14.6770
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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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