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| author | emile <hanemile@protonmail.com> | 2019-08-30 15:51:01 +0000 |
|---|---|---|
| committer | Emile <hanemile@protonmail.com> | 2019-08-30 17:55:03 +0200 |
| commit | 66f68d8a5b7c6168aa447b1cf7fd5e6476699150 (patch) | |
| tree | cf0176390cb536ef8a9de933d27a465aaf39c0aa | |
| parent | 27e835206952d91000bc36b64928c60b097569bc (diff) | |
| parent | b6af1ce4e4b847c3ba83f25787c52dccdf0b58e1 (diff) | |
Merge branch 'format' of Satellite/TLE into master
| -rw-r--r-- | README.md | 49 |
1 files changed, 46 insertions, 3 deletions
diff --git a/README.md b/README.md index 0c95ee8..58871ab 100644 --- a/README.md +++ b/README.md @@ -1,7 +1,50 @@ [](https://godoc.org/git.darknebu.la/Satellite/TLE) [](https://goreportcard.com/report/git.darknebu.la/Satellite/TLE) [](https://drone.nbg1.emile.space/Satellite/TLE) # TLE -Implementing the "Two-line element set (TLE)", a data format encoding orbital elements of Earth-orbiting objects. https://en.wikipedia.org/wiki/Two-line_element_set +Implementing the "Two-line element set (TLE)", a data format encoding orbital elements of Earth-orbiting objects. https://en.wikipedia.org/wiki/Two-line_element_set -[nasa documentation of the -format](https://spaceflight.nasa.gov/realdata/sightings/SSapplications/Post/JavaSSOP/SSOP_Help/tle_def.html) +[nasa documentation of the format](https://spaceflight.nasa.gov/realdata/sightings/SSapplications/Post/JavaSSOP/SSOP_Help/tle_def.html) + +## Format + +(the below tables are copied 1:1 from wikipedia ([from here](https://en.wikipedia.org/wiki/Two-line_element_set))) + +### Title line + +| Field | Columns | Content | Example | +| ----- | ------- | ------- | ------- | +| 1 | 01-24 | Satellite name | ISS (ZARYA) | + +### Line one + +| Field | Columns | Content | Example | +| ----- | ------- | ------- | ------- | +| 1 | 01-01 | Line number | 1 | +| 2 | 03–07 | Satellite number | 25544 | +| 3 | 08–08 | Classification (U=Unclassified) | U | +| 4 | 10–11 | International Designator (Last two digits of launch year) | 98 | +| 5 | 12–14 | International Designator (Launch number of the year) | 067 | +| 6 | 15–17 | International Designator (piece of the launch) | A | +| 7 | 19–20 | Epoch Year (last two digits of year) | 08 | +| 8 | 21–32 | Epoch (day of the year and fractional portion of the day) | 264.51782528 | +| 9 | 34–43 | First Time Derivative of the Mean Motion divided by two [11] | −.00002182 | +| 10 | 45–52 | Second Time Derivative of Mean Motion divided by six (decimal point assumed) | 00000-0 | +| 11 | 54–61 | BSTAR drag term (decimal point assumed) [11] | -11606-4 | +| 12 | 63–63 | The number 0 (originally this should have been "Ephemeris type") | 0 | +| 13 | 65–68 | Element set number. Incremented when a new TLE is generated for this object.[11] | 292 | +| 14 | 69–69 | Checksum (modulo 10) | 7 | + +### Line two + +| Field | Columns | Content | Example | +| ----- | ------- | ------- | ------- | +| 1 | 01–01 | Line number | 2 | +| 2 | 03–07 | Satellite number | 25544 | +| 3 | 09–16 | Inclination (degrees) | 51.6416 | +| 4 | 18–25 | Right ascension of the ascending node (degrees) | 247.4627 | +| 5 | 27–33 | Eccentricity (decimal point assumed) | 0006703 | +| 6 | 35–42 | Argument of perigee (degrees) | 130.5360 | +| 7 | 44–51 | Mean Anomaly (degrees) | 325.0288 | +| 8 | 53–63 | Mean Motion (revolutions per day) | 15.72125391 | +| 9 | 64–68 | Revolution number at epoch (revolutions) | 56353 | +| 10 | 69–69 | Checksum (modulo 10) | 7 | |
