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NORAD-TLE-two-line-element-set-format

Python

NORAD TLE Parser and Structured Orbital Data Export

Python-based parser for reading, interpreting, and exporting NORAD Two-Line Element (TLE) orbital data into structured JSON format.

Overview

This project provides a structured TLE reader and parser for extracting orbital parameters from NORAD Two-Line Element sets.

TLEs are standardized orbital data formats widely used to describe the mean orbital elements of Earth-orbiting objects.

The script:

  • Detects satellite name headers (if present)
  • Parses Line 1 and Line 2 according to official NORAD field definitions
  • Extracts orbital parameters into structured dictionaries
  • Exports parsed data to output.json for integration with analytical pipelines

Example TLE Format

STARLINK-34935
1 51049U 22002AZ  23344.50972222  .00000319  00000-0  15287-4 0  9993
2 51049  53.2170 352.5403 0001660  59.5515 300.5766 15.08875454 99462

Functional Capabilities

  • Automatic satellite name detection
  • Field-level parsing based on NORAD positional specifications
  • Extraction of:
    • Inclination
    • RAAN
    • Eccentricity
    • Argument of Perigee
    • Mean Anomaly
    • Mean Motion
    • BSTAR drag term
    • Epoch
  • JSON export for downstream processing

Processing Workflow

  1. Opens a specified TLE file (default: STARLINK-34935.txt)
  2. Identifies optional satellite name header
  3. Separates Line 1 and Line 2
  4. Applies field slicing based on NORAD documentation
  5. Outputs parsed parameters to terminal
  6. Exports structured dataset to output.json

Parsed Field Structure

Line 1

Field Description
Satellite Catalog Number NORAD ID
Classification Object classification
International Designator Launch identifier
Epoch Reference epoch
1st Derivative of Mean Motion Drag-related term
2nd Derivative of Mean Motion Higher-order term
BSTAR Atmospheric drag coefficient
Element Set Number TLE version number
Checksum Data integrity validation

Line 2

Field Description
Inclination (deg) Orbital inclination
RAAN (deg) Right Ascension of Ascending Node
Eccentricity Decimal implied format
Argument of Perigee (deg) Argument of perigee
Mean Anomaly (deg) Position at epoch
Mean Motion (rev/day) Orbital frequency
Revolution Number Orbit count at epoch
Checksum Data integrity validation

Requirements

  • Python 3.x

References

Application Context

This parser supports:

  • Orbit propagation workflows
  • SGP4 integration
  • Debris tracking systems
  • Space Domain Awareness (SDA) pipelines
  • Orbital risk modeling frameworks

For collaborations, feel free to connect via LinkedIn or email.