struct Predict::TLE

• Predict::TLE
• Struct
• Value
• Object

Overview

Represents the orbital elements contained in a two-line element set in a normalised form.

Defined in:

Constructors

• .new(name : String, catalog_number : Int32, international_designator : Predict::InternationalDesignator, epoch : Time, element_set_number : Int32, revolution_number : Int32, mean_motion : Float64, mean_motion_1st_deriv : Float64, mean_motion_2nd_deriv : Float64, radiation_pressure_coefficient : Float64, inclination : Float64, raan : Float64, eccentricity : Float64, argument_of_perigee : Float64, mean_anomaly : Float64)
• .parse_three_line(string : String, *, detect_zero_index = true) : TLE

  Parses a three line TLE (name, line1, line2).

Class Method Summary

• .checksum(string)

  Runs the checksum algorithm used by TLEs on the given string.

• .parse_three_line(io : IO, *, detect_zero_index = true) : TLE | Nil

  Reads a single three line TLE from IO.

• .parse_two_line(tle : String, name : String)

  Parses a two-line TLE given a tle string and a human-readable name.

• .parse_two_line(lines : Indexable(String), name : String)

  Parses a two-line TLE given an array of two lines and a human-readable name.

Instance Method Summary

• #argument_of_perigee : Float64

  The angle between the ascending node and the orbit's perigee in degrees.

• #catalog_number : Int32

  The NORAD catalogue number of this satellite.

• #eccentricity : Float64

  A value defining the shape of the orbit.

• #element_set_number : Int32

  Element set number of this TLE.

• #epoch : Time

  The epoch time for this TLE in UTC.

• #inclination : Float64

  Inclination between the equator and orbit in degrees.

• #international_designator : InternationalDesignator

  The InternationalDesignator of this satellite.

• #mean_anomaly : Float64

  Mean anomaly in degrees.

• #mean_motion : Float64

  Mean number of orbits per day the satellite completes.

• #mean_motion_1st_deriv : Float64

  First derivative of mean motion with respect to time (in days).

• #mean_motion_2nd_deriv : Float64

  Second derivative of mean motion with nrespect to time (in days).

• #name : String

  The human-readable name of the satellite.

• #raan : Float64

  The angle between the vernal equinox and the point where the orbit crosses the equatorial plane going north in degrees.

• #radiation_pressure_coefficient : Float64

  BSTAR coefficient, a term in the SGP4 predictor.

• #revolution_number : Int32

  The orbit number of the satellite at the epoch.

Constructor Detail

Class Method Detail

Instance Method Detail