Forecast of Conjunctions: 50 Latest Payloads vs. All (31338) 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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2026-09-24 16:59:49.818
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68429
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TROOP-F3
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100682
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GLOBAL-36
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2.682
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-1.348, 1.994, 1.184
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7.7775
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2026-09-24 17:46:23.845
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53547
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STARLINK-4474
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100789
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ZK-1A / RB
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4.835
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3.665, 1.800, -2.590
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12.3453
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2026-09-24 18:00:21.488
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39490
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COSMOS 2493 (SKRL 756)
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100746
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STRIX-10
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4.865
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-4.550, -1.081, -1.342
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11.8496
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2026-09-24 19:37:17.522
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12435
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COSMOS 1266 FUEL CORE
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100694
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QIANFAN-241
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3.368
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0.278, 0.971, -3.213
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14.1429
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2026-09-24 19:38:52.112
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100508
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STARLINK-38355
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100616
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STARLINK-38350
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2.973
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1.486, -1.556, 2.052
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12.2684
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2026-09-24 20:50:44.699
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66006
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STARLINK-35336
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100789
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ZK-1A / RB
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4.638
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3.916, -1.759, 1.756
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10.9074
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2026-09-24 20:59:11.305
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64878
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OBJECT C
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100682
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GLOBAL-36
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4.694
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-4.017, -2.085, 1.243
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7.8300
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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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