diff options
| -rw-r--r-- | TLE.go | 133 |
1 files changed, 0 insertions, 133 deletions
diff --git a/TLE.go b/TLE.go deleted file mode 100644 index 95b0a55..0000000 --- a/TLE.go +++ /dev/null @@ -1,133 +0,0 @@ -/* -Package tle implementing the "Two-line element set (TLE)", a data format encoding orbital elements of Earth-orbiting objects. - -More information can be found in the wikipedia article: (https://en.wikipedia.org/wiki/Two-line_element_set) and in the official NASA documentation: (https://spaceflight.nasa.gov/realdata/sightings/SSapplications/Post/JavaSSOP/SSOP_Help/tle_def.html) - -*/ -package tle - -// TLE defines the lines contained in a Two-Line-Element -type TLE struct { - TitleLine TitleLine `json:"titleline"` - LineOne LineOne `json:"lineone"` - LineTwo LineTwo `json:"linetwo"` -} - -// TitleLine defines the first line in the the TLE -// It contains the name of the satellite -type TitleLine struct { - Satname string `json:"satname"` -} - -// LineOne defines the first line in the TLE -type LineOne struct { - Linenumber int `json:"linenumber"` - - // Catalog number defined by USSPACECOM - // A "U" indicates an unclassified object - SatelliteNumber int `json:"satellitenumber"` - Classification string `json:"classification"` - - // International Designator containing information about the launch - InternationalDesignator InternationalDesignator `json:"internationaldesignator"` - - // Epoch defining from when the TLE is - Epoch Epoch `json:"epoch"` - - // First Time Derivative of the Mean Motion divided by two - // Unit: revs / day - // "catch all" drag term used in SGP4 USSPACECOM predictor - Firstderiv float64 `json:"firstderiv"` - - // Second Time Derivative of Mean Motion divided by six (decimal point assumed) - // second order drag term in the SGP4 - // Unit: revs / day^3 - // A leading decimal must be applied to this value - // The last two characters define an applicable power of 10 (12345-5 = 0.0000012345) - Secondderiv float64 `json:"secondderiv"` - - // Drag Term - // (67960-4 = 0.000067960) - // Unit: earth radii^-1 - // The last two characters define an applicable power of 10 - BSTAR float64 `json:"BSTAR"` - - // The number 0 (originally this should have been "Ephemeris type") - Numberzero int `json:"numberzero"` - - // Element set number. Incremented when a new TLE is generated for this object. - ElementSetNumber int `json:"elementesetnumber"` - - // Checksum (modulo 10) - Checksum int `json:"checksum"` -} - -// InternationalDesignator stores information about the satellite such as when it launched -type InternationalDesignator struct { - - // Last two digits of launch year - Launchyear int `json:"launchyear"` - - // Launch number of the year - Launchnumber int `json:"launchnumber"` - - // Piece of the launch - Launchpiece string `json:"launchpiece"` -} - -// Epoch defines a moment in time -type Epoch struct { - - // Last two digits of the year - Year int `json:"year"` - - // day of the year and fractional portion of the day - Dayfraction float64 `json:"dayfraction"` -} - -// LineTwo of the TLE -type LineTwo struct { - Linenumber int `json:"linenumber"` - - // Catalog number defined by USSPACECOM - SatelliteNumber int `json:"satellitenumber"` - - // Inclination - // Unit: degrees - // Angle between the equator and the orbit plane - Inclination float64 `json:"inclination"` - - // Right Ascension of the Ascending Node - // Unit: degrees - // Angle between vernal equinox and the point where the orbit crosses the equatorial plane (going north). - RightAscensionOfTheAscendingNode float64 `json:"rightascensionoftheascendingnode"` - - // Eccentricity - // Constant defining the shape of the orbit (0=circular, Less than 1=elliptical). - // The value provided is the mean eccentricity. - // A leading decimal must be applied to this value - Eccentricity float64 `json:"eccentricity"` - - // Argument of perigee - // Unit: degrees - // The angle between the ascending node and the orbit's point of closest approach of the earth (perigee) - ArgumentOfPerigee float64 `json:"argumentofperigee"` - - // Mean Anomaly - // Unit: degrees - // The angle, measured from perigee, of the satellite location in the orbit referenced to a circular orbit - // with radius equal to the semi-major axis. - MeanAnomaly float64 `json:"meananomaly"` - - // Mean Motion - // The value is the mean number of orbits per day the object completes. There are 8 digits after the decimal, - // leaving no trailing space(s) when the following element exceeds 9999. - MeanMotion float64 `json:"meanmotion"` - - // The orbit number at Epoch Time. This time is chosen very near the time of true ascending node passage as - // a matter of routine. The last digit is the check sum for line 2. - RevolutionNumberAtEpoch int `json:"revolutionnumberatepoch"` - - // Checksum (modulo 10) - Checksum int `json:"checksum"` -} |
