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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2026-10-15 01:34:36.286
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24340
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PEGASUS DEB
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100962
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NEONSAT-04
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3.848
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-3.805, 0.022, -0.572
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15.4431
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2026-10-15 02:13:03.510
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41003
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FENGYUN 1C DEB
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100955
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NEONSAT-02
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4.397
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4.333, -0.302, -0.686
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13.8961
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2026-10-15 02:17:45.422
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4133
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THORAD AGENA D DEB
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100878
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STARLINK-40076
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3.068
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1.325, -1.782, -2.117
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11.7846
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2026-10-15 03:06:22.327
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34909
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COSMOS 2251 DEB
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100955
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NEONSAT-02
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4.934
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4.907, -0.058, -0.517
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15.0436
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2026-10-15 03:15:56.530
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3454
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TITAN 3C TRANSTAGE DEB
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100924
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HOTSAT-3
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2.314
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2.141, 0.737, 0.479
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8.2600
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2026-10-15 03:49:00.651
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34856
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COSMOS 2251 DEB
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100919
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ION SCV-024
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4.502
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-4.399, 0.108, -0.951
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15.0956
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2026-10-15 03:52:22.191
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57456
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YAOGAN-36 05C
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100925
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ION SCV-025
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4.319
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1.302, -3.212, 2.577
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9.5212
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2026-10-15 04:22:49.327
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49071
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TIANHUI 2-02A
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100941
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RADIX-A
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2.834
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-0.508, 2.326, -1.538
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8.3704
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2026-10-15 04:22:49.367
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49072
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TIANHUI 2-02B
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100941
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RADIX-A
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3.254
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-0.662, 2.658, -1.758
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8.3708
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2026-10-15 05:10:19.650
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49072
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TIANHUI 2-02B
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100940
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RADIX-M
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4.644
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-4.638, 0.205, 0.135
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8.3956
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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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