Forecast of Conjunctions: 50 Latest Payloads vs. All (31204) 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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2026-09-29 19:49:56.129
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55961
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STARLINK-5933
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100746
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STRIX-10
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4.280
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-0.275, -2.673, 3.331
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11.7978
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2026-09-29 20:20:31.646
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45675
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STARLINK-1458
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100628
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STARLINK-38348
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2.043
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0.309, 1.720, -1.058
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8.0671
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2026-09-29 20:32:14.936
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59354
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STARLINK-31422
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100789
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ZK-1A / RB
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3.649
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3.648, 0.009, -0.091
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14.1223
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2026-09-29 20:41:31.428
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60195
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STARLINK-11193
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100622
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STARLINK-38366
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1.766
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-1.604, 0.719, 0.170
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3.5343
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2026-09-29 20:58:08.393
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60116
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STARLINK-11210
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100634
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STARLINK-38415
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2.918
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-2.889, 0.328, 0.244
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9.1693
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2026-09-29 21:11:28.327
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66175
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OBJECT A
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100682
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GLOBAL-36
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1.655
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1.604, 0.180, -0.368
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13.7187
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2026-09-29 21:16:48.118
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60190
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STARLINK-11179
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100639
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STARLINK-38411
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1.879
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0.423, 1.782, 0.422
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3.5401
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2026-09-29 23:15:42.279
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60116
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STARLINK-11210
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100634
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STARLINK-38415
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3.117
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2.583, 1.402, -1.037
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9.1664
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2026-09-30 00:30:16.871
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60997
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STARLINK-11260
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100621
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STARLINK-38347
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3.234
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2.949, -0.845, 1.023
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11.8431
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2026-09-30 00:35:42.738
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2389
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OV3-3
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100636
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STARLINK-38170
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4.617
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-2.532, -3.637, -1.295
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3.9797
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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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