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 12:19:52.460
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61126
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CZ-6A DEB
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100919
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ION SCV-024
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3.769
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0.218, 2.675, 2.646
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10.6972
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2026-10-12 12:21:02.761
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39771
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H-2A R/B
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100924
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HOTSAT-3
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3.285
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-1.255, 2.585, 1.592
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7.9786
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2026-10-12 12:30:30.305
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68827
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COSMOS 2616
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100866
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STARLINK-40091
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3.818
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-0.327, 3.072, 2.242
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9.1104
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2026-10-12 13:03:54.276
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45590
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STARLINK-1365
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100880
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STARLINK-40097
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4.009
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-3.987, 0.336, -0.253
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9.2006
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2026-10-12 13:22:55.402
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8026
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METEOR 2-1
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100825
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YAOGAN-40 O4C
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2.796
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2.134, -0.452, 1.749
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14.3647
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2026-10-12 14:40:56.442
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58848
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AAC-HSI-SAT3
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100934
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MIKROGLOB-2
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2.094
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2.093, -0.051, 0.014
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1.8180
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2026-10-12 15:14:51.927
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31519
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FENGYUN 1C DEB
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100825
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YAOGAN-40 O4C
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2.518
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-0.687, -0.763, 2.299
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14.0523
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2026-10-12 17:53:42.579
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68441
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HAWK-14C
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100901
↓
←
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ELEMENT-1
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4.570
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4.568, 0.061, -0.087
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12.5217
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2026-10-12 18:10:32.700
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10177
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DELTA 1 DEB
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100940
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RADIX-M
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4.416
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-2.308, 1.752, 3.332
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13.6168
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2026-10-12 18:19:10.784
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45369
↓
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STARLINK-1277
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100875
↑
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STARLINK-40103
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2.823
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-1.484, -2.181, -1.008
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6.4695
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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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