removed the TLE.go file

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"`
-}