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 02:54:17.399
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57990
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YAOGAN-39 03C
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100894
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ICEYE-X87
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3.907
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-2.943, 1.802, -1.833
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10.8443
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2026-10-14 03:22:14.568
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35442
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COSMOS 2251 DEB
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100955
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NEONSAT-02
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4.802
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-3.603, -0.241, -3.165
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15.1096
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2026-10-14 03:45:33.394
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66830
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STARLINK-35881
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100955
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NEONSAT-02
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4.428
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-4.177, 0.717, -1.282
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13.2092
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2026-10-14 03:51:34.696
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100114
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STARLINK-38088
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100878
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STARLINK-40076
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3.486
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-1.264, 2.257, -2.337
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11.0854
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2026-10-14 04:37:15.137
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100114
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STARLINK-38088
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100878
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STARLINK-40076
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3.152
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-2.982, -0.707, -0.734
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11.0849
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2026-10-14 05:24:49.022
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55955
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STARLINK-5878
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100955
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NEONSAT-02
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3.865
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-3.413, -1.599, 0.854
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7.1860
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2026-10-14 06:16:45.487
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58848
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AAC-HSI-SAT3
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100919
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ION SCV-024
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3.059
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3.002, 0.587, -0.064
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1.8208
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2026-10-14 07:02:41.721
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68436
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HAWK-14B
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100941
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RADIX-A
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3.432
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2.032, -1.566, -2.280
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12.5424
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2026-10-14 07:14:02.183
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82180
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TBA - TO BE ASSIGNED
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100894
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ICEYE-X87
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4.170
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4.124, -0.228, 0.575
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14.3577
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2026-10-14 07:19:21.703
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35898
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COSMOS 2251 DEB
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100892
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CRIMSON-1
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4.110
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-4.098, -0.291, 0.135
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6.0478
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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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