Forecast of Conjunctions: 50 Latest Payloads vs. All (31338) 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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2026-09-24 06:51:39.189
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57454
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YAOGAN-36 05B
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100741
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TIANYI 51
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4.656
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-2.974, 2.678, -2.379
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10.1178
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2026-09-24 07:08:25.097
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100539
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STARLINK-38211
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100626
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STARLINK-36777
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4.132
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0.432, 2.795, 3.012
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11.2969
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2026-09-24 07:17:59.136
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43181
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KANOPUS-V 4
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100682
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GLOBAL-36
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2.787
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-1.811, -1.638, -1.343
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9.6557
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2026-09-24 07:43:37.387
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12257
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DELTA 1 DEB
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100696
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QIANFAN-243
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4.203
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-0.095, -1.287, 4.001
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14.0636
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2026-09-24 08:05:27.638
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60488
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FLOCK 4BE 31
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100712
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PROGRESS MS-35
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2.055
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-1.196, -0.451, -1.609
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14.7483
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2026-09-24 08:37:38.105
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59104
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PE2_FLT2 (TYVAK-0262)
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100746
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STRIX-10
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2.838
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2.823, -0.164, 0.239
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12.3014
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2026-09-24 08:39:42.288
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100539
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STARLINK-38211
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100626
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STARLINK-36777
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1.556
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0.464, -1.010, -1.089
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11.2970
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2026-09-24 09:19:49.458
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24007
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PEGASUS DEB
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100611
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PLATFORM-6
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0.980
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-0.409, 0.010, -0.890
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15.2113
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2026-09-24 09:25:20.869
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100539
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STARLINK-38211
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100626
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STARLINK-36777
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2.132
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1.313, 1.142, -1.232
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11.2802
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2026-09-24 09:26:09.782
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12257
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DELTA 1 DEB
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100701
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QIANFAN-248
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1.816
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0.909, 0.488, -1.495
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14.0597
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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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