Forecast of Conjunctions: 50 Latest Payloads vs. All (32410) 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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2026-11-08 13:18:55.901
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101177
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STARLINK-38405
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101247
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STARLINK-38166
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3.149
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-3.039, 0.543, 0.620
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11.6366
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2026-11-08 14:43:57.318
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64536
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FOSSASAT2E21
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101286
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CZ-2C ROCKET BODY
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2.649
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-0.517, 0.929, -2.427
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14.2461
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2026-11-08 16:19:36.365
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41354
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NOAA 16 DEB
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101277
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QIANFAN-262
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2.934
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-0.901, -2.641, 0.906
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4.8192
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2026-11-08 16:37:06.707
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101065
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OBJECT F
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101285
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OBJECT C
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2.059
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-1.903, -0.549, -0.563
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10.8830
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2026-11-08 17:17:46.598
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25655
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SL-3 DEB
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101285
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OBJECT C
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1.479
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-0.997, -0.808, -0.734
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10.1978
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2026-11-08 17:52:16.915
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101177
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STARLINK-38405
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101248
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STARLINK-38344
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3.743
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-2.761, -1.657, -1.908
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11.6363
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2026-11-08 18:00:47.327
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41354
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NOAA 16 DEB
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101269
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QIANFAN-254
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3.803
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-0.780, 3.521, -1.207
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4.8283
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2026-11-08 18:00:47.939
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41354
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NOAA 16 DEB
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101268
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QIANFAN-253
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4.963
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-0.785, -4.635, 1.593
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4.8283
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2026-11-08 18:02:41.380
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41138
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NOAA 16 DEB
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101264
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QIANFAN-249
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4.655
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-3.653, 2.169, -1.904
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8.6005
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2026-11-08 18:51:42.105
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4157
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THORAD AGENA D DEB
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101285
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OBJECT C
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1.112
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-0.846, -0.545, 0.472
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9.9595
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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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