Time Controls
Scenario Time (UTC)
Set Time
Time Step
0.1x
0.5x
1x
2x
5x
10x
1 min/s
1 hr/s
1 day/s
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Reset to Live
Initial State
Input Type
Classical Orbital Elements
State Vector (r, v)
Two Line Element Set (TLE)
Object Name
Epoch (UTC)
Reference time for orbital elements
Semi-major Axis, a (km)
Eccentricity, e
Inclination, i (deg)
RAAN, Ω (deg)
Argument of Periapsis, ω (deg)
True Anomaly, ν (deg)
Object Name
Epoch (UTC)
Reference time for initial orbital state (r₁, v₁)
r₁x (km)
r₁y (km)
r₁z (km)
v₁x (km/s)
v₁y (km/s)
v₁z (km/s)
Object Name
Two Line Element Set
Paste two-line element set data
Propagator
SGP4 for TLEs (recommended); J2 secular or two-body otherwise
Plot Orbit
Scenario Objects
Add and manage orbital objects. Click an object name to expand options.
Load from Catalog
Ground Sites
Add observer sites for pass prediction. Sites are plotted on the ground track and used by the Access tab.
Add Ground Site
Display Options
Camera Reference
Earth (ECI)
Earth (ECEF)
Show Axes
Show Object Labels
Show Object Data
Show Sun Vector
Reset Camera
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Ground Track
Access
Conjunction
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Object Properties
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Add Object
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Dialog
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Pro feature
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