Forecast of Conjunctions: 50 Latest Payloads vs. All (31718) 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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2026-10-09 01:29:52.009
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60242
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OBJECT H
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100941
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RADUX-A
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3.655
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2.177, -0.574, -2.879
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14.9162
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2026-10-09 01:29:52.785
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60242
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OBJECT H
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100940
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RADIX-M
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4.813
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2.424, -0.811, -4.078
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14.9160
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2026-10-09 03:09:36.655
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34969
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COSMOS 2251 DEB
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100825
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YAOGAN-40 O4C
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4.927
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0.534, -2.228, 4.361
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13.2232
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2026-10-09 04:11:35.659
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61540
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STARLINK-11350
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100779
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STARLINK-38385
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4.658
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4.535, 0.585, -0.887
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12.8460
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2026-10-09 04:31:19.708
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61273
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CZ-6A DEB
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100825
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YAOGAN-40 O4C
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3.627
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3.136, -0.101, -1.819
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14.8309
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2026-10-09 05:10:46.381
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67390
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CONNECTA IOT-16
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100941
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RADUX-A
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3.164
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-0.314, 2.560, 1.833
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8.8668
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2026-10-09 05:25:12.461
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59716
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STARLINK-11099
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100778
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STARLINK-38420
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2.686
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2.480, -0.941, 0.426
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6.3294
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2026-10-09 05:51:14.298
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68827
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COSMOS 2616
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100868
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STARLINK-40092
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3.102
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-2.703, -1.140, -1.008
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10.2299
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2026-10-09 05:54:00.898
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60187
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STARLINK-11194
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100775
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STARLINK-38442
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3.269
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3.226, -0.294, -0.442
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12.8040
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2026-10-09 06:11:52.224
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100824
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YAOGAN-40 O4B
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270063
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TBA - TO BE ASSIGNED
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3.681
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-1.592, -0.260, -3.309
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14.8137
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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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