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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2026-10-30 11:45:40.612
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33999
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COSMOS 2251 DEB
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101128
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PELICAN-12 3013
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3.355
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-2.937, 1.555, -0.461
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4.0969
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2026-10-30 11:58:14.572
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68997
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YAM-15
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101128
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PELICAN-12 3013
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4.830
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-4.714, 0.768, 0.720
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10.3868
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2026-10-30 12:27:46.358
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43773
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RANGE A
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101145
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HAWK 16B
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4.867
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-1.291, 0.730, -4.636
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15.0134
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2026-10-30 12:29:40.399
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10535
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COSMOS 970 DEB
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101190
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HULIANWANG DIGUI 228
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4.234
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-0.600, -2.701, -3.206
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11.1869
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2026-10-30 12:42:19.328
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897
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OPS 5798 (TRANSIT 5B-4)
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101187
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HULIANWANG DIGUI 225
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0.628
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0.017, 0.457, -0.430
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10.0308
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2026-10-30 13:42:13.435
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26548
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TIUNGSAT 1
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101142
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XIGUANG-4 01
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3.563
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-3.534, -0.440, -0.109
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4.2762
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2026-10-30 13:46:02.622
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60819
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CZ-6A DEB
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101128
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PELICAN-12 3013
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2.807
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0.918, -2.476, -0.950
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5.3899
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2026-10-30 14:15:03.678
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8764
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SL-8 DEB
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101149
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YAOGAN-50 03
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4.552
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-1.446, -3.550, -2.456
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8.4190
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2026-10-30 16:10:51.833
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64569
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IRIDE-MS2-HEO-2
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101132
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TOMORROW-S14
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3.207
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0.183, 1.289, 2.931
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13.8380
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2026-10-30 16:27:02.514
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46141
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STARLINK-1596
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101159
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STARLINK-38479
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4.363
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-1.579, 3.203, -2.507
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9.5249
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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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