Forecast of Conjunctions: 50 Latest Payloads vs. All (31204) 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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2026-09-27 02:26:12.625
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100508
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STARLINK-38355
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100616
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STARLINK-38350
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0.670
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0.669, 0.018, -0.024
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12.2674
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2026-09-27 02:28:50.864
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100519
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STARLINK-38370
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100617
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STARLINK-38357
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4.468
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2.157, -2.362, 3.119
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12.2696
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2026-09-27 02:33:11.775
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66507
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STARLINK-34767
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100789
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ZK-1A / RB
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1.359
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1.267, 0.390, -0.299
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8.7656
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2026-09-27 03:04:34.253
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45389
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STARLINK-1283
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100765
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STARLINK-38446
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4.995
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-4.918, -0.615, 0.619
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11.0759
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2026-09-27 03:05:19.289
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42398
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NOAA 16 DEB
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100690
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SENTINEL-3C
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1.797
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-1.360, -1.004, 0.609
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7.7182
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2026-09-27 03:17:39.732
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22422
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SL-16 DEB
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100689
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FLEX
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4.566
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-4.560, 0.061, -0.224
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14.4417
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2026-09-27 03:48:31.936
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17635
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COSMOS 1275 DEB
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100690
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SENTINEL-3C
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2.754
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-2.586, -0.880, -0.348
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5.3258
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2026-09-27 04:21:56.522
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31017
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FENGYUN 1C DEB
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100692
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QIANFAN-239
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4.746
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1.364, 2.274, 3.936
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12.7593
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2026-09-27 04:59:49.281
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57886
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YAOGAN-39 02A
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100742
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TIANYI 52
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4.514
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1.570, -4.099, -1.052
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3.7879
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2026-09-27 05:07:02.949
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37695
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FENGYUN 1C DEB
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100689
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FLEX
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3.219
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-0.974, 2.654, -1.538
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7.5252
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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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