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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2026-09-27 17:58:37.884
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55041
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SKYKRAFT-1
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100619
↑
↺
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STARLINK-36683
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1.050
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-1.050, -0.001, -0.004
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14.2457
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2026-09-27 18:17:55.949
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54091
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STARLINK-5221
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100742
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TIANYI 52
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4.438
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-4.232, 0.800, -1.070
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12.1664
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2026-09-27 18:23:32.298
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58918
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OBJECT B
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100742
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TIANYI 52
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2.338
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1.904, -1.232, -0.568
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6.3830
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2026-09-27 18:27:48.061
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17638
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COSMOS 1275 DEB
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100696
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QIANFAN-243
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4.406
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4.151, -0.288, 1.449
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14.5036
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2026-09-27 19:32:47.559
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64374
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STARLINK-11739
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100639
↑
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STARLINK-38411
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3.381
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-3.351, -0.358, 0.268
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9.3427
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2026-09-27 19:41:48.699
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100550
↑
↺
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STARLINK-38335
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100630
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STARLINK-38376
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2.608
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-0.855, -1.676, 1.806
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11.2821
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2026-09-27 19:56:17.493
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30903
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FENGYUN 1C DEB
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100701
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QIANFAN-248
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3.479
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2.836, 0.469, 1.959
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14.3791
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2026-09-27 20:48:22.746
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42214
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COSMOS 1275 DEB
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100692
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QIANFAN-239
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3.189
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-0.294, -2.894, -1.305
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6.0344
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2026-09-27 21:23:23.334
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57300
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STARLINK-30236
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100616
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STARLINK-38350
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3.236
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-3.232, 0.152, 0.084
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7.7107
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2026-09-27 21:27:27.279
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61368
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CZ-6A DEB
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100693
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QIANFAN-240
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4.037
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0.840, 1.935, 3.442
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12.8371
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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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