Forecast of Conjunctions: 50 Latest Payloads vs. All (32067) 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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2026-10-18 04:20:12.363
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13917
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SL-8 R/B
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100986
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SDA-NG-T1TL-404
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3.926
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-2.570, 2.798, -0.992
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4.9103
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2026-10-18 05:09:20.353
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28521
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COSMOS 2414
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100999
↗
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SDA-NG-T1TL-417
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3.340
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3.165, -0.565, -0.907
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12.4664
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2026-10-18 07:39:50.449
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18639
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COSMOS 1275 DEB
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100992
↗
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SDA-NG-T1TL-410
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0.644
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0.439, 0.164, 0.442
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13.8906
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2026-10-18 07:40:31.979
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40434
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DMSP 5D-2 F13 DEB
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100995
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SDA-NG-T1TL-413
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0.834
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0.535, -0.447, 0.457
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10.4837
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2026-10-18 07:42:29.891
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30918
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FENGYUN 1C DEB
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100997
↗
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SDA-NG-T1TL-415
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4.613
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4.569, -0.084, -0.630
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14.6836
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2026-10-18 08:01:48.563
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100697
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QIANFAN-244
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100997
↗
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SDA-NG-T1TL-415
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4.351
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3.710, -0.199, 2.265
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14.6968
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2026-10-18 09:22:23.972
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40434
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DMSP 5D-2 F13 DEB
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101001
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SDA-NG-T1TL-419
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0.859
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0.630, -0.407, 0.418
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10.4964
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2026-10-18 09:25:02.487
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18639
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COSMOS 1275 DEB
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100988
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SDA-NG-T1TL-406
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4.749
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0.844, 1.600, 4.392
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13.8905
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2026-10-18 09:45:30.429
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100697
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QIANFAN-244
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100998
↗
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SDA-NG-T1TL-416
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3.976
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3.428, 0.184, -2.006
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14.6972
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2026-10-18 10:34:51.906
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10142
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SL-8 R/B
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101001
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SDA-NG-T1TL-419
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2.509
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-0.310, -0.379, -2.460
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14.5967
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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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