About Orbital Period & Satellite Trajectory Calculator
Keplerian orbital mechanics calculator for satellites, spacecraft, and celestial bodies. Computes orbital period (seconds, minutes, hours, days, years), mean orbital velocity, periapsis and apoapsis velocities, and specific orbital energy for circular and elliptical orbits around Earth, Moon, Mars, Jupiter, or the Sun.
Key Capabilities & Features
- Kepler Third Law orbital period solver: T = 2π√(a³ / GM)
- Support for circular and eccentric elliptical orbits (eccentricity e from 0.0 to 0.9)
- Preloaded central attractors: Earth (LEO, MEO, GEO), Moon, Mars, Jupiter, and Sun
- Vis-viva periapsis and apoapsis velocity solver with specific orbital energy in MJ/kg
How to Use Orbital Period & Satellite Trajectory Calculator
Select Attractor Body
Choose Earth, Moon, Mars, Jupiter, or the Sun as your primary gravitational mass.
Set Orbital Altitude
Enter the orbital altitude above the surface in kilometers or pick a preset like ISS or GEO.
Adjust Eccentricity
Slide eccentricity from 0.0 (perfect circle) to higher values for elliptical orbits.
Review Period & Speeds
Examine the exact period duration, daily revolutions, and periapsis/apoapsis orbital speeds.
Privacy & In-Browser Execution Guarantee
Satellite trajectory models evaluate strictly in-browser with zero server telemetry.
Frequently Asked Questions
What is the orbital altitude and period of a Geostationary Satellite (GEO)?
A geostationary satellite orbits at an altitude of approximately 35,786 km (semi-major axis 42,157 km) with an orbital period of exactly one sidereal day (23 hours, 56 minutes, 4 seconds), appearing stationary relative to Earth surface.