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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2026-10-29 05:24:53.984
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100787
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OBJECT H
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101144
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HAWK 16A
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4.019
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0.017, -1.592, -3.690
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13.9477
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2026-10-29 05:37:38.484
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54431
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CZ-6A DEB
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101149
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YAOGAN-50 03
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4.163
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2.666, 1.917, 2.559
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11.9176
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2026-10-29 06:19:55.131
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43773
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RANGE A
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101146
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HAWK 16C
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2.954
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-2.935, 0.050, -0.330
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15.0141
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2026-10-29 06:41:58.669
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65270
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COSMOS 2594
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101166
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STARLINK-38401
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4.569
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-4.520, -0.154, -0.653
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15.0260
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2026-10-29 07:20:15.875
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54431
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CZ-6A DEB
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101149
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YAOGAN-50 03
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2.884
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2.628, 0.702, 0.957
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11.9282
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2026-10-29 07:27:06.636
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65270
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COSMOS 2594
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101166
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STARLINK-38401
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4.489
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4.424, -0.172, 0.744
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15.0595
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2026-10-29 07:47:15.901
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57183
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OBJECT T
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101146
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HAWK 16C
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3.302
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0.144, -0.929, 3.166
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14.5745
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2026-10-29 09:02:53.264
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54431
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CZ-6A DEB
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101149
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YAOGAN-50 03
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2.745
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2.590, -0.558, -0.718
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11.9388
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2026-10-29 09:09:20.637
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64623
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HAWK-12A
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101145
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HAWK 16B
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2.432
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0.549, -0.643, -2.280
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14.6214
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2026-10-29 09:11:39.807
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31913
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FENGYUN 1C DEB
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101191
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HULIANWANG DIGUI 229
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3.627
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2.301, 1.295, -2.487
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12.9323
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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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