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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2026-09-26 15:30:18.258
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43782
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SNUSAT-2
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100742
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TIANYI 52
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1.619
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-1.460, -0.652, -0.257
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5.6310
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2026-09-26 15:54:36.183
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18232
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DELTA 1 DEB
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100700
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QIANFAN-247
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4.779
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-4.324, 0.165, 2.027
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14.7055
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2026-09-26 16:14:02.834
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53661
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STARLINK-4472
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100746
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STRIX-10
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3.641
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3.129, -0.923, -1.615
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13.1685
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2026-09-26 16:49:40.097
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49135
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STARLINK-3073
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100746
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STRIX-10
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2.910
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-1.746, 1.382, -1.874
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12.1900
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2026-09-26 16:57:54.053
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100539
↑
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STARLINK-38211
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100627
↑
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STARLINK-36778
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4.464
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-0.954, 2.967, 3.196
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11.2966
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2026-09-26 16:58:49.223
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30178
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FENGYUN 1C DEB
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100692
↑
↻
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QIANFAN-239
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0.616
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0.147, -0.154, 0.578
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14.3030
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2026-09-26 17:37:26.042
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18232
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DELTA 1 DEB
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100701
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QIANFAN-248
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2.294
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-2.254, -0.069, -0.419
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14.7076
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2026-09-26 17:46:24.542
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57542
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METEOR 1-17 DEB
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100690
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SENTINEL-3C
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0.617
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0.536, -0.074, -0.295
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14.4448
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2026-09-26 18:05:53.182
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67212
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STARLINK-36213
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100746
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STRIX-10
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3.780
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-0.144, 2.721, -2.620
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10.4951
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2026-09-26 18:27:51.932
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41054
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NOAA 16 DEB
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100689
↗
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FLEX
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3.739
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-0.841, -0.583, -3.597
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14.6670
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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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