Orbit Specification
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From TLE Data
Custom Orbit
NORAD ID (SATCAT)
Fetch TLE
Semi-major axis (a)
Eccentricity (e)
Inclination (i)
RAAN (Ω):
Arg. of Perigee (ω)
True Anomaly (v)
Epoch (UTC)
Set Orbit
Visibility Options
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Core Visuals
Earth
Orbit
Planes
Equat.
Eclip.
Orbital
Coordinate Axes
ECI
PQW
Orbital Angles
i
Ω
ω
Misc.
Nodes
Constellations
Simulation Controls
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Time Step
milliseconds
seconds
minutes
hours
OK
Time Between Position Updates
milliseconds
seconds
OK
Simulation Date
N/A
Pause
Forward
Reverse
Positional Data
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Latitude:
Longitude:
Altitude:
Orbital Elements
▼
Epoch:
Semi-major axis (a):
Eccentricity (e):
Inclination (i):
RAAN (Ω):
Argument of Perigee (ω):
Mean Motion (n):
Mean Anomaly (M):
True Anomaly (v):