Forecast of Conjunctions: 50 Latest Payloads vs. All (32628) 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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2026-11-14 12:57:58.645
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64074
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STARLINK-11730
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101254
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STARLINK-37806
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3.902
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3.580, -1.156, 1.035
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10.2492
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2026-11-14 13:11:50.169
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21330
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DELTA 1 DEB
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101328
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HULIANWANG DIGUI 240
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4.542
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-1.938, -3.011, 2.795
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10.0900
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2026-11-14 13:32:28.091
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24236
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PEGASUS DEB
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101280
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QIANFAN-265
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4.730
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1.147, -0.616, -4.548
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14.7104
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2026-11-14 13:36:48.602
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61205
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STARLINK-11277
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101250
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STARLINK-38407
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4.500
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-2.583, -2.530, -2.679
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11.1878
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2026-11-14 13:39:15.420
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60114
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STARLINK-11198
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101250
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STARLINK-38407
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4.725
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-2.779, 3.337, 1.861
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7.5104
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2026-11-14 13:48:33.678
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17618
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COSMOS 1275 DEB
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101273
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QIANFAN-258
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3.120
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-2.950, -0.909, 0.453
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6.6571
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2026-11-14 14:05:25.311
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60399
↓
→
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STARLINK-11182
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101250
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STARLINK-38407
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4.466
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-3.789, -1.186, 2.045
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13.3333
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2026-11-14 14:12:01.605
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42398
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NOAA 16 DEB
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101264
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QIANFAN-249
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3.002
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2.070, -2.161, -0.244
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1.5082
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2026-11-14 14:30:40.923
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31725
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FENGYUN 1C DEB
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101270
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QIANFAN-255
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4.299
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0.021, -0.996, -4.182
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14.6848
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2026-11-14 14:49:04.644
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101069
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OBJECT K
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101294
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OBJECT D
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1.174
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0.858, -0.104, -0.794
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15.0491
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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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