Forecast of Conjunctions: 50 Latest Payloads vs. All (32679) 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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2026-11-11 13:19:53.912
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30505
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FENGYUN 1C DEB
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101280
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QIANFAN-265
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3.854
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-3.697, -0.834, 0.698
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9.3786
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2026-11-11 13:55:35.574
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42298
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DMSP 5D-2 F13 DEB
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101323
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HULIANWANG DIGUI 234
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0.730
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-0.622, -0.346, -0.162
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6.7610
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2026-11-11 14:03:54.260
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54443
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CZ-6A DEB
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101264
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QIANFAN-249
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4.040
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-0.500, 3.976, 0.514
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1.8755
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2026-11-11 14:12:54.329
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26265
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CZ-4 DEB
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101264
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QIANFAN-249
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3.733
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-1.486, -3.000, -1.652
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7.1893
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2026-11-11 14:15:33.079
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33741
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FENGYUN 1C DEB
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101278
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QIANFAN-263
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3.978
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1.434, 2.170, -3.009
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12.0618
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2026-11-11 14:35:59.661
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63345
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YUNYAO-1 44
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101291
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OBJECT A
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3.082
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3.073, 0.026, -0.225
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15.0345
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2026-11-11 15:26:24.030
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62733
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OBJECT E
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101294
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OBJECT D
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2.281
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1.527, 0.311, 1.666
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14.9166
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2026-11-11 15:49:32.319
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82524
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TBA - TO BE ASSIGNED
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101269
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QIANFAN-254
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4.639
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4.406, -1.177, 0.846
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8.2936
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2026-11-11 15:57:36.521
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33741
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FENGYUN 1C DEB
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101266
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QIANFAN-251
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2.704
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2.500, -0.667, 0.785
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12.0553
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2026-11-11 16:03:29.303
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54285
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CZ-6A DEB
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101266
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QIANFAN-251
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4.601
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-3.840, -2.495, 0.447
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2.6174
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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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