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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2026-10-12 02:00:40.511
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58848
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AAC-HSI-SAT3
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100914
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ICEYE-X85
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4.108
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1.862, 3.635, -0.444
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1.8168
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2026-10-12 02:31:01.056
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35156
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FENGYUN 1C DEB
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100825
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YAOGAN-40 O4C
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2.713
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0.616, 0.594, 2.574
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14.4822
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2026-10-12 02:50:35.702
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66751
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ICEYE-X58
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100919
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ION SCV-024
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2.744
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-2.459, 1.218, 0.029
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0.2213
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2026-10-12 03:05:06.303
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100370
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HONGHU 3
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100894
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ICEYE-X87
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2.489
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1.706, 1.578, -0.890
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7.5056
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2026-10-12 03:38:04.741
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66751
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ICEYE-X58
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100919
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ION SCV-024
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4.501
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4.417, 0.866, 0.026
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0.2208
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2026-10-12 04:12:32.602
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55041
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SKYKRAFT-1
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100878
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STARLINK-40076
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1.411
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0.993, -0.537, -0.847
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13.0184
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2026-10-12 04:56:05.286
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35721
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COSMOS 2251 DEB
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100825
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YAOGAN-40 O4C
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3.322
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-2.001, -1.975, 1.769
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9.9565
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2026-10-12 04:56:24.677
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53648
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STARLINK-4622
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100909
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TERRA NOVA
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4.201
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-3.334, -0.494, -2.507
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14.9042
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2026-10-12 05:03:05.435
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54316
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CZ-6A DEB
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100825
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YAOGAN-40 O4C
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3.208
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2.444, -0.720, 1.949
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13.8965
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2026-10-12 06:02:16.488
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68441
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HAWK-14C
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100913
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MIKROGLOB-4
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4.916
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4.797, 0.608, 0.885
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12.5572
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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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