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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2026-09-28 22:59:22.454
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59755
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STARLINK-11132
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100639
↑
↺
→
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STARLINK-38411
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2.128
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0.037, 1.814, -1.111
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8.0383
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2026-09-28 23:14:40.438
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63671
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STARLINK-11603
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100634
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STARLINK-38415
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4.572
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-0.383, -3.750, 2.587
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8.7306
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2026-09-28 23:23:34.859
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13172
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OPS 6553
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100746
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STRIX-10
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1.458
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1.232, -0.492, -0.605
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11.8072
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2026-09-28 23:32:12.593
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56169
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CHECKMATE 3
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100692
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QIANFAN-239
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1.410
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1.108, 0.818, 0.302
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5.0766
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2026-09-28 23:46:48.125
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976
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SCOUT X-4 DEB
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100694
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QIANFAN-241
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4.858
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-2.804, -0.440, 3.943
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14.6451
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2026-09-28 23:51:26.585
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100124
↗
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STARLINK-37991
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100629
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STARLINK-38327
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2.587
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-1.979, 1.270, -1.079
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9.9821
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2026-09-28 23:54:53.819
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63111
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STARLINK-11630
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100631
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STARLINK-38421
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4.871
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0.716, -3.250, -3.556
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11.3648
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2026-09-29 00:11:53.496
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63134
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STARLINK-11605
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100640
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STARLINK-38412
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4.094
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-0.035, 2.963, 2.824
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10.6208
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2026-09-29 00:38:59.311
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62469
↑
↻
→
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STARLINK-11505
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100631
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STARLINK-38421
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1.987
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1.552, 0.779, -0.967
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11.9883
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2026-09-29 00:48:23.212
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52617
↓
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STARLINK-3996
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100742
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TIANYI 52
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4.396
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-0.496, 2.907, 3.260
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11.3565
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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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