Forecast of Conjunctions: 50 Latest Payloads vs. All (31718) 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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2026-10-01 22:50:19.475
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66768
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LEMUR-2-TEODOR
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100682
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GLOBAL-36
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3.105
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-2.416, -0.793, -1.781
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13.8971
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2026-10-02 00:12:25.750
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8544
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DELTA 1 DEB
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100701
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QIANFAN-248
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2.517
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1.087, 1.536, -1.672
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10.6606
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2026-10-02 01:27:36.270
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405
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THOR ABLESTAR DEB
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100696
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QIANFAN-243
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0.398
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0.191, 0.231, 0.261
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11.0610
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2026-10-02 02:30:09.150
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87405
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TBA - TO BE ASSIGNED
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100692
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QIANFAN-239
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2.157
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-1.637, -0.107, 1.401
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14.6976
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2026-10-02 02:36:26.830
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41272
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NOAA 16 DEB
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100690
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SENTINEL-3C
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4.360
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2.949, -3.210, 0.070
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0.3256
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2026-10-02 03:15:53.477
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65585
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PRAETORIAN SDA_601
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100696
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QIANFAN-243
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2.474
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-2.455, 0.202, 0.233
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11.1881
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2026-10-02 03:16:07.689
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35520
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SL-14 DEB
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100698
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QIANFAN-245
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4.416
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3.781, -0.207, 2.273
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14.7097
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2026-10-02 03:29:17.400
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14464
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DELTA 1 DEB
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100694
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QIANFAN-241
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3.945
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-0.893, 1.567, -3.509
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13.4557
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2026-10-02 04:01:05.616
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36551
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COSMOS 2251 DEB
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100741
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TIANYI 51
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1.819
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-1.817, 0.040, -0.085
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13.6046
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2026-10-02 04:18:29.175
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69648
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HOKUSHIN1
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100638
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STARLINK-38416
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2.749
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-1.307, -2.010, 1.344
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8.5165
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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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