Forecast of Conjunctions: 50 Latest Payloads vs. All (32410) 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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2026-11-08 22:58:01.396
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50621
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COSMOS 1408 DEB
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101239
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STARLINK-38459
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3.097
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1.414, 2.308, -1.505
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8.4196
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2026-11-08 23:24:09.393
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33065
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ORBCOMM FM 40
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101286
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CZ-2C ROCKET BODY
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4.571
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3.489, 2.026, 2.150
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10.9742
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2026-11-08 23:33:03.721
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68465
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HOTSAT-2
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101283
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OBJECT A
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1.432
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0.501, 1.111, 0.751
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8.5169
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2026-11-08 23:40:30.800
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56582
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CZ-6A DEB
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101275
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QIANFAN-260
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3.898
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-1.981, 3.341, 0.319
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1.4170
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2026-11-09 00:05:53.542
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30369
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FENGYUN 1C DEB
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101267
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QIANFAN-252
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3.630
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0.380, 3.535, -0.729
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2.9044
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2026-11-09 00:07:27.184
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55056
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VIGORIDE 5
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101252
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STARLINK-38485
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3.679
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-2.019, -1.533, -2.666
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13.3696
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2026-11-09 00:28:42.662
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63346
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YUNYAO-1 45
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101293
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OBJECT C
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4.294
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0.620, 0.577, -4.210
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15.0380
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2026-11-09 00:28:45.929
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63346
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YUNYAO-1 45
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101292
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OBJECT B
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1.143
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-1.035, -0.065, 0.479
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15.0396
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2026-11-09 00:28:48.093
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63346
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YUNYAO-1 45
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101291
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OBJECT A
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4.742
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-0.768, -0.634, 4.636
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15.0393
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2026-11-09 01:34:29.295
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66689
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AC1-003
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101283
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OBJECT A
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4.074
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3.849, 0.458, 1.253
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14.2812
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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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