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 16:42:29.078
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32198
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FENGYUN 1C DEB
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101269
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QIANFAN-254
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2.336
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1.444, 0.955, -1.568
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12.7214
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2026-11-11 17:07:38.299
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53839
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STARLINK-4784
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101291
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OBJECT A
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2.599
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2.267, -1.052, 0.715
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8.5258
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2026-11-11 17:09:33.686
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14409
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COSMOS 1275 DEB
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101321
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CZ-12 R/B
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4.199
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3.918, 1.250, 0.851
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8.0162
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2026-11-11 17:25:08.423
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18779
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DELTA 1 DEB
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101280
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QIANFAN-265
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2.951
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0.314, -2.903, -0.424
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2.3024
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2026-11-11 19:07:48.279
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29139
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THOR BURNER 2A DEB
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101280
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QIANFAN-265
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2.103
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-1.552, -1.391, -0.275
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2.7620
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2026-11-11 20:06:00.476
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60858
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CZ-6A DEB
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101280
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QIANFAN-265
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3.507
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3.474, -0.364, -0.311
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9.8280
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2026-11-11 20:15:38.922
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58901
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ELECTRON KICK STAGE R/B
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101247
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STARLINK-38166
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3.591
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-1.369, -3.053, 1.303
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6.0525
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2026-11-11 20:57:15.668
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19468
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CZ-4 R/B
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101277
↓
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QIANFAN-262
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3.717
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-3.701, 0.333, 0.099
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4.6898
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2026-11-11 21:00:00.411
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100107
↑
↺
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STARLINK-37864
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101247
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STARLINK-38166
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1.902
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-1.847, 0.075, -0.451
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15.1762
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2026-11-11 21:12:44.869
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7816
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OPS 6226
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101276
↓
↻
→
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QIANFAN-261
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3.573
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-3.178, -0.198, 1.621
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14.7183
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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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