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 13:43:59.408
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30464
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FENGYUN 1C DEB
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101001
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SDA-NG-T1TL-419
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0.292
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-0.009, 0.079, 0.281
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14.1340
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2026-10-18 13:58:46.073
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39939
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COSMOS 1275 DEB
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101000
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SDA-NG-T1TL-418
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2.112
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0.216, 0.389, 2.065
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14.5114
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2026-10-18 14:03:47.692
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10142
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SL-8 R/B
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100998
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SDA-NG-T1TL-416
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1.886
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0.138, 0.288, 1.859
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14.5968
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2026-10-18 14:48:28.376
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60630
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CZ-6A DEB
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101031
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DRAGON CRS-35
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4.995
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-3.832, 1.695, -2.719
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13.0126
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2026-10-18 16:04:46.315
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69584
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OBJECT C
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100983
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SDA-NG-T1TL-401
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3.842
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1.792, 3.307, 0.781
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3.3887
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2026-10-18 16:28:01.082
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87159
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TBA - TO BE ASSIGNED
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100983
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SDA-NG-T1TL-401
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3.484
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-2.821, -1.128, -1.705
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12.2683
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2026-10-18 16:34:57.627
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19162
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COSMOS 1932 FUEL CORE
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100986
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SDA-NG-T1TL-404
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4.087
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-3.780, 1.168, -1.024
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9.6647
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2026-10-18 16:40:32.124
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100697
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QIANFAN-244
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101001
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SDA-NG-T1TL-419
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4.706
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2.617, -0.344, 3.896
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14.6986
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2026-10-18 17:12:18.390
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12284
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DELTA 1 DEB
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100996
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SDA-NG-T1TL-414
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4.271
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4.119, -0.040, -1.129
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14.7079
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2026-10-18 17:27:44.322
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39939
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COSMOS 1275 DEB
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100997
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SDA-NG-T1TL-415
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4.320
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0.480, 0.791, 4.220
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14.5114
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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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