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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2026-09-26 19:27:05.253
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43782
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SNUSAT-2
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100742
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TIANYI 52
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3.434
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2.432, -2.252, 0.900
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5.6592
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2026-09-26 19:36:33.015
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100064
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PRAETORIAN SDA_506
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100692
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QIANFAN-239
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3.410
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3.410, -0.002, 0.007
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13.2024
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2026-09-26 19:36:45.656
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37453
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FENGYUN 1C DEB
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100692
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QIANFAN-239
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2.581
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-2.580, -0.032, -0.047
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13.8904
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2026-09-26 19:49:56.498
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45915
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OBJECT E
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100611
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PLATFORM-6
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1.544
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1.461, -0.417, -0.277
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8.9949
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2026-09-26 20:03:20.268
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14463
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DELTA 1 DEB
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100696
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QIANFAN-243
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2.986
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2.963, -0.084, -0.359
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14.2815
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2026-09-26 20:29:15.626
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100522
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STARLINK-38372
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100641
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STARLINK-38436
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1.495
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0.029, -0.903, -1.191
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12.2827
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2026-09-26 20:47:54.966
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46955
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DRAGRACER 2(AUGURY)
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100624
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STARLINK-38423
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0.760
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0.472, 0.358, -0.476
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12.2894
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2026-09-26 22:12:41.618
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30160
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FENGYUN 1C DEB
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100698
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QIANFAN-245
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4.114
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-4.077, 0.092, -0.540
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14.8263
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2026-09-26 22:46:10.969
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100522
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STARLINK-38372
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100641
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STARLINK-38436
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2.108
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2.088, 0.177, -0.233
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12.2696
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2026-09-26 23:02:48.172
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66772
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IHI-SAT2
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100682
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GLOBAL-36
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1.703
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-1.261, -0.586, -0.982
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13.0592
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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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