{"id":12643,"date":"2024-12-06T00:08:43","date_gmt":"2024-12-06T04:08:43","guid":{"rendered":"https:\/\/zobi.alcowep.com\/bourtagshdrevxnls658739\/space-station-trajectory-data\/"},"modified":"2024-12-06T00:08:43","modified_gmt":"2024-12-06T04:08:43","slug":"space-station-trajectory-data","status":"publish","type":"post","link":"https:\/\/zobi.alcowep.com\/bourtagshdrevxnls658739\/space-station-trajectory-data\/","title":{"rendered":"Space Station Trajectory Data"},"content":{"rendered":"

Space Station Trajectory Data<\/h2>\n

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\"The<\/a><\/figure>
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iss071e650763 (Sept. 14, 2024) \u2014 The long exposure photograph taken by NASA astronaut Matthew Dominick shows star trails, streaks of city lights, and two Roscosmos crew ships, the Soyuz MS-26 docked to the Rassvet module (foreground) and the Soyuz MS-25 (background) docked to the Prichal docking module, as the International Space Station orbited 265 miles above central China.<\/div>\n
NASA<\/div>\n<\/figcaption><\/div>\n<\/div>\n<\/div>\n

Space Station trajectory data is now available to the public!<\/h2>\n
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This data, called an ephemeris, is generated by the ISS Trajectory Operations and Planning Officer (TOPO) flight controllers in the Mission Control Center at NASA\u2019s Johnson Space Center. TOPO keeps track of where the ISS is, where it is going to be, and most importantly makes sure it isn\u2019t at risk of colliding with other objects in space. At ISS\u2019s altitude, a very thin atmosphere is still present. This thin atmosphere creates drag and over time can cause TOPO\u2019s predicted ISS trajectory to accumulate error. Because of this, TOPO updates the predicted trajectory approximately three times a week, so the ISS Flight Control Team has the best trajectory estimate possible. An accurate trajectory is essential for maintaining communications links, planning visiting vehicle rendezvous, and ensuring ISS\u2019s path is clear of any potential collisions.<\/p>\n

The links above and below are to the most current posted ephemeris. The ephemeris is in the CCSDS Orbital Ephemeris Message (OEM) standard and is available in .txt and .xml file formats. Each file contains header lines with the ISS mass in kg, drag area in m2<\/sup>, and drag coefficient used in generating the ephemeris. The header also contains lines with details for the first and last ascending nodes within the ephemeris span. Following this is a listing of upcoming ISS translation maneuvers, called \u201creboosts,\u201d and visiting vehicle launches, arrivals, and departures.<\/p>\n

After the header, ISS state vectors in the Mean of J2000 (J2K) reference frame are listed at four-minute intervals spanning a total length of 15 days. During reboosts (translation maneuvers), the state vectors are reported in two-second intervals. Each state vector lists the time in UTC; position X, Y, and Z in km; and velocity X, Y, and Z in km\/s.<\/p>\n

Orbit Ephemeris Message (OEM)<\/strong><\/h2>\n
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