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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2026-10-27 13:05:40.508
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61788
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OBJECT BF
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101015
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STARLINK-38475
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2.132
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-1.589, 0.717, 1.227
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13.2743
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2026-10-27 13:32:48.880
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39452
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SWARM A
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101031
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DRAGON CRS-35
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2.841
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1.776, -2.109, 0.683
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4.7024
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2026-10-27 14:10:20.642
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47621
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STARLINK-1609
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101019
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STARLINK-38452
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2.779
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-1.524, -2.250, -0.583
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3.8566
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2026-10-27 14:51:32.718
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60306
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STARLINK-11109
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101027
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STARLINK-38455
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3.669
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3.628, 0.539, 0.118
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3.2834
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2026-10-27 14:56:13.588
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100171
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STARLINK-38197
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101030
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STARLINK-38472
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4.242
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4.196, 0.444, -0.435
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10.7464
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2026-10-27 15:08:21.031
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87737
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TBA - TO BE ASSIGNED
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101191
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HULIANWANG DIGUI 229
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4.426
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1.439, 1.193, 4.012
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14.0127
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2026-10-27 15:09:01.092
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100514
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STARLINK-38397
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101025
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STARLINK-38465
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3.999
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0.945, -3.629, -1.391
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5.5041
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2026-10-27 15:19:24.888
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29975
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FENGYUN 1C DEB
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100990
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SDA-NG-T1TL-408
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3.148
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-3.142, 0.008, -0.191
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14.6229
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2026-10-27 15:54:56.440
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100514
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STARLINK-38397
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101025
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STARLINK-38465
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4.547
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1.352, -4.053, 1.556
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5.4966
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2026-10-27 16:32:32.378
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56203
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NUSAT-37 (JOAN CLARKE)
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101006
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STARLINK-38310
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4.198
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-4.159, -0.157, -0.550
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14.7695
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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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