PDF document and interactive MATLAB script called csystems.m which can be used to perform a variety of time and coordinate calculations. This script performs the following types of time calculations;
convert UTC calendar date and time to UTC Julian date, convert UTC Julian date to UTC calendar date and time, Greenwich apparent sidereal time, convert Universal Coordinated Time (UTC) to Terrestrial Time (TT), convert Universal Coordinated Time (UTC) to Barycentric Dynamical Time (TDB), convert Barycentric Dynamical Time (TDB) to Universal Coordinated Time (UTC)
The csystems script can also be used to perform the following types of coordinate calculations;
convert geodetic coordinates to eci position vector, convert eci state vector to ecf state vector, convert eci state vector to classical orbital elements, convert classical orbital elements to eci state vector, convert flight path coordinates to eci state vector, convert eci state vector to relative flight path coordinates, convert classical orbital elements to modified equinoctial elements, convert modified equinoctial elements to classical orbital elements, convert osculating orbital elements to mean elements, convert eci state vector to Two Line Elements (TLE)
In this script, by ECI frame, do you mean J2000 ECI frame or TEME frame?
Purpose: Possible issues in the function RV2TLE
It seems that the function RV2tle has issues with some quadrant checks! Some RV-pairs work and other RV-pairs don't. I am trying to point out the nature of the error. Could it be that at some places in your code, atan2 and atan3 had been mismatched unintentionally?
Greets from Luxembourg/EU
PS: any way, great lib, great work!
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