Forecast of Conjunctions: 50 Latest Payloads vs. All (32410) 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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2026-11-10 06:31:09.834
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62756
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USA 485
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101242
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STARLINK-38250
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0.487
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-0.478, 0.053, -0.075
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12.5943
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2026-11-10 07:01:29.856
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41210
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NOAA 16 DEB
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101277
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QIANFAN-262
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1.673
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1.568, 0.549, -0.197
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5.0035
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2026-11-10 08:04:21.368
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53290
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STARLINK-4149
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101285
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OBJECT C
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4.009
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-3.189, -2.273, -0.855
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5.3483
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2026-11-10 08:36:23.521
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100117
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STARLINK-38062
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101251
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STARLINK-38341
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4.581
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3.445, 0.401, -2.993
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15.2547
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2026-11-10 08:42:48.330
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41210
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NOAA 16 DEB
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101267
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QIANFAN-252
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4.949
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1.719, -4.367, 1.570
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5.0126
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2026-11-10 09:50:38.390
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57545
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METEOR 1-17 DEB
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101281
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QIANFAN-266
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4.745
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-4.637, 0.096, 1.000
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14.7956
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2026-11-10 09:50:38.482
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57545
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METEOR 1-17 DEB
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101276
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QIANFAN-261
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4.692
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-4.618, 0.097, 0.828
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14.7956
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2026-11-10 09:50:38.707
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57545
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METEOR 1-17 DEB
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101270
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QIANFAN-255
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4.619
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-4.599, 0.051, 0.426
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14.7956
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2026-11-10 09:50:39.405
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57545
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METEOR 1-17 DEB
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101275
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QIANFAN-260
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4.648
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-4.585, -0.086, -0.758
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14.7956
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2026-11-10 10:32:15.467
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36689
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FENGYUN 1C DEB
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101266
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QIANFAN-251
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4.028
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-3.012, 0.672, 2.588
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14.4503
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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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