Forecast of Conjunctions: 50 Latest Payloads vs. All (31743) 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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2026-09-30 04:20:52.919
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63010
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STARLINK-11574
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100641
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STARLINK-38436
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2.820
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2.118, 1.040, -1.544
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12.7701
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2026-09-30 04:32:01.192
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61942
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STARLINK-11320
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100639
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STARLINK-38411
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1.147
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0.886, -0.447, 0.576
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12.1364
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2026-09-30 05:18:47.895
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45700
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STARLINK-1400
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100770
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STARLINK-38301
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0.901
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-0.234, 0.850, -0.189
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3.3509
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2026-09-30 05:51:00.393
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66768
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LEMUR-2-TEODOR
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100682
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GLOBAL-36
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3.895
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-3.425, 0.812, 1.669
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13.7023
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2026-09-30 05:52:29.084
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50816
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STARLINK-3342
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100741
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TIANYI 51
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1.986
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-1.477, -1.314, 0.195
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2.2717
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2026-09-30 05:58:07.051
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4612
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THORAD AGENA D DEB
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100693
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QIANFAN-240
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1.210
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-1.156, 0.036, -0.357
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14.6403
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2026-09-30 05:59:22.849
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60013
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OBJECT B
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100682
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GLOBAL-36
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2.399
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2.399, 0.001, 0.009
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14.0029
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2026-09-30 06:29:01.767
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7209
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METEOR 1-16
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100689
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FLEX
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3.948
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2.233, 2.883, 1.513
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6.9155
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2026-09-30 06:39:46.991
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50816
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STARLINK-3342
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100741
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TIANYI 51
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1.583
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-0.302, -1.537, -0.232
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2.2661
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2026-09-30 06:56:18.218
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18513
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THORAD AGENA D DEB
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100690
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SENTINEL-3C
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4.242
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2.054, 1.220, -3.506
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14.0370
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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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