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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2026-10-11 20:37:22.334
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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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4.497
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-1.764, 2.251, 3.470
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12.9359
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2026-10-11 21:22:13.899
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68466
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DB-PRECISIONFLIGHTWORKSP
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100889
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ICEYE-X83
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2.828
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2.824, 0.089, -0.132
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12.5293
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2026-10-11 22:05:21.969
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39771
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H-2A R/B
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100901
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ELEMENT-1
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4.413
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-2.296, 3.207, 1.978
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7.9854
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2026-10-11 22:15:56.999
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44753
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STARLINK-1048
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100857
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STARLINK-40094
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4.762
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-3.018, -3.417, -1.375
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5.7528
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2026-10-11 22:50:36.827
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58848
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AAC-HSI-SAT3
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100910
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ICEYE-X86
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3.316
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1.539, -2.915, 0.367
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1.8170
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2026-10-12 00:09:21.432
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45369
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STARLINK-1277
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100865
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STARLINK-40090
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2.139
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-1.943, -0.809, -0.383
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6.5712
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2026-10-12 00:26:31.279
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41599
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CARTOSAT 2C
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100901
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ELEMENT-1
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1.676
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0.733, 1.500, -0.142
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1.4503
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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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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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