Forecast of Conjunctions: 50 Latest Payloads vs. All (31718) 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 17:59:12.921
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31155
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FENGYUN 1C DEB
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100699
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QIANFAN-246
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3.746
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2.174, -2.979, -0.656
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3.1921
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2026-09-30 18:05:13.423
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61253
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STARLINK-11311
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100630
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STARLINK-38376
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4.165
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3.095, 2.242, -1.656
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9.1244
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2026-09-30 18:09:55.389
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20671
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SL-14 R/B
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100694
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QIANFAN-241
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1.162
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-0.296, 0.092, 1.120
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14.7245
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2026-09-30 18:26:25.965
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100550
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STARLINK-38335
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100628
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STARLINK-38348
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4.686
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2.187, 2.817, 3.039
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11.2969
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2026-09-30 18:35:21.561
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100552
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STARLINK-38234
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100632
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STARLINK-38403
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3.542
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2.550, -1.673, -1.801
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11.2934
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2026-09-30 19:13:37.539
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61947
↑
→
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STARLINK-11390
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100621
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STARLINK-38347
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3.827
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3.694, 0.608, -0.791
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12.2076
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2026-09-30 19:20:59.783
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100552
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STARLINK-38234
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100632
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STARLINK-38403
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3.720
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3.011, 1.486, -1.601
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11.2841
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2026-09-30 19:21:09.448
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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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4.481
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2.292, -2.568, -2.870
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11.3423
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2026-09-30 19:43:14.272
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55631
↓
→
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STARLINK-5558
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100829
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STRIX-12
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2.367
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-2.028, -0.754, -0.959
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11.9337
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2026-09-30 20:04:41.395
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62617
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SCOT-1 (SCOT)
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100641
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STARLINK-38436
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0.429
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-0.420, 0.020, 0.088
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15.0058
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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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