TLE Calculator
Parse and analyze Two-Line Element (TLE) orbital data
Load TLE from Database
Basic Information
Satellite Name:
NORAD ID:
International Designator:
Classification:
Orbital Elements
Epoch Year:
Epoch Day:
Inclination:
RAAN:
Eccentricity:
Argument of Perigee:
Mean Anomaly:
Mean Motion:
Drag and Decay Parameters
First Derivative (n-dot/2):
Second Derivative (n-dot-dot/6):
B* Drag Term:
Revolution Number:
Calculated Values
Orbital Period:
Semi-Major Axis:
Apogee Altitude:
Perigee Altitude:
Epoch Date (UTC):
Element Set Number:
Propagation
Position & Velocity at
Calculations use https://github.com/shashwatak/satellite-js
TEME Coordinates
Position X:
Position Y:
Position Z:
Velocity X:
Velocity Y:
Velocity Z:
Geographic Position
Latitude:
Longitude:
Altitude:
Ground Speed:
Orbit Ground Track (Next 90 Minutes)
Propagation Test
Go back to fetch a TLE for N/A from 30 days ago and propagate it forward, comparing positions to subsequent TLEs to see - for unpowered objects - how quickly TLEs drift from reality.
Error Growth Over Time
| Days Since TLE | Position Error (km) |
|---|
Analysis Summary
TLEs Analyzed:
Time Span:
Max Error:
Error at 7 days: