Forecast of Conjunctions: 50 Latest Payloads vs. All (32067) 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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2026-10-14 10:41:45.227
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63258
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ICEYE-X46
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100962
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NEONSAT-04
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4.021
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-0.726, -1.044, -3.814
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14.5726
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2026-10-14 11:07:03.740
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55766
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STARLINK-5599
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100963
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NEONSAT-05
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0.975
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-0.518, 0.799, 0.206
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3.8127
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2026-10-14 11:10:57.657
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60878
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CZ-6A DEB
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100899
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JACK-006
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3.616
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-0.026, -2.332, 2.763
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11.5956
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2026-10-14 12:46:01.085
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63356
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LEMUR 2 TILLINFINITY
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100892
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CRIMSON-1
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1.031
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0.783, -0.464, 0.485
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10.9892
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2026-10-14 13:16:49.819
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35996
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COSMOS 2251 DEB
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100897
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ALTAIR-1
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3.248
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3.247, 0.003, -0.047
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15.0972
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2026-10-14 13:21:11.297
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66690
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OBJECT AA
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100914
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ICEYE-X85
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3.389
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2.374, 2.417, -0.077
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0.2476
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2026-10-14 13:45:49.990
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54766
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STARLINK-5471
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100899
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JACK-006
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4.774
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0.290, 1.792, -4.415
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14.0969
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2026-10-14 14:19:18.736
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68366
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RASSVET-3 7
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100899
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JACK-006
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4.734
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4.311, -1.186, 1.555
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12.0691
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2026-10-14 14:31:12.357
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47391
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STARLINK-2112
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100899
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JACK-006
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1.347
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1.139, 0.355, 0.626
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13.2166
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2026-10-14 14:33:20.924
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54766
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STARLINK-5471
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100899
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JACK-006
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2.612
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-2.016, -0.625, -1.539
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14.0705
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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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