MyRTLE (My Refined TLE Browser) is a TLE browser application written in Go. It uses CelesTrack as the source of data.
Two-Line Element set is a data format that contains the most essential parameters describing the position and motion of a satellite in orbit around Earth. Every set consists of three lines, the first of which is a title line. The next two hold the basic orbital elements of a body at a given moment in time (epoch).
Example TLE set for the International Space Station:
ISS (ZARYA)
1 25544U 98067A 22014.20078024 -.00001581 00000+0 -20061-4 0 9991
2 25544 51.6452 19.1428 0006828 17.5887 10.3753 15.49476744321309
This information allows us to calculate the exact position and velocity of a body as well as predict changes due to various object-specific forces, such as atmospheric drag.
Orbital elements symbols and their display format is based on Orbit MFD from Orbiter Space Flight Simulator.
SMa - Semi-Major Axis
SMi - Semi-Minor Axis
PeR/A - Periapsis Radius/Altitude ASL
ApR/A - Apoapsis Radius/Altitude ASL
R/Alt - Radius/Altitude ASL
Ecc - Orbital Eccentricity
T - Orbital Period
PeT - Time to Periapsis
ApT - Time to Apoapsis
Vel - Orbital Velocity
Inc - Orbital Inclination
LAN - Longitude of Ascending Node
LPe - Longitude of Periapsis
AgP - Argument of Periapsis
TrA - True Anomaly
TrL - True Longitude
MnA - Mean Anomaly
MnL - Mean Longitude
EcA - Eccentric Anomaly
If ! appears by the eccentric anomaly's symbol it means that solution for Kepler's equation did not converge.
go install github.com/Zedran/myrtle@latest
There are 4 commands that control the behavior of application:
/b- go back to the previous page/e- exit application/f- go forward to the next page/h- display the list of commands and symbols
Search accepts the query phrase at least 3 characters in length and the following arguments:
/c- search by object's catalogue number/n- search by object's name (default)
These commands format the values of orbital elements and can be passed when making a query:
/a- display distance as altitude ASL/r- display distance as radius from the center of the dominant body (default)/p- display precise values/s- display shortened values (default)
The results page displays 20 found matches at a time. To skip to the next 20, use these commands:
/>[n]- go forward by n subpages/<[n]- go back by n subpages
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Kelso, T., S. 1985. CelesTrak. [on-line] Available at https://celestrak.com [accessed on 15.01.2022] COMSPOC Corp. Exton, PA.
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Kelso, T., S. 2019. Frequently Asked Questions: Two-Line Element Set Format. CelesTrak. [on-line] Available at http://celestrak.com/columns/v04n03 [accessed on 15.01.2022] COMSPOC Corp. Exton, PA.
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Murison, M., A. 2006. A Practical Method for Solving the Kepler Equation. [on-line] Available at http://murison.alpheratz.net/dynamics/twobody/KeplerIterations_summary.pdf [accessed on 15.01.2022] U.S. Naval Observatory, Washington, DC.
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Orbiter Space Flight Simulator by Martin Schweiger
This software is available under MIT License.