Analysis output
Interactive orbital mechanics
Plan a Hohmann transfer.
See every burn.
Explore how spacecraft move between circular orbits around Earth, the Moon, and Mars. Calculate delta-v, transfer time, orbital velocity, and every equation behind the result.
3Celestial bodies
2Impulse burns
1Transfer ellipse
Mission control
Orbital transfer simulator
Choose a central body and two circular-orbit altitudes. The lab models an ideal two-impulse Hohmann transfer.
Initial orbit
Transfer orbit
Target orbit
Burn 1—Departure impulse
Burn 2—Arrival impulse
Total delta-v—Ideal impulsive maneuver
Transfer time—Half the transfer period
Under the hood
The physics behind the mission
The simulator uses the ideal two-body approximation, circular starting and ending orbits, and instantaneous coplanar burns.
Orbital radius
r = R + h
Altitude is measured from the surface, while orbital equations require distance from the body's center.
Circular velocity
v = √(μ / r)
Orbital speed depends on the gravitational parameter μ and orbital radius r.
Vis-viva equation
v = √[μ(2/r − 1/a)]
This gives spacecraft velocity at any point along the elliptical transfer orbit.
Transfer time
t = π√(a³ / μ)
A Hohmann transfer takes half of the elliptical transfer orbit's full period.
View calculation steps using your mission
Classroom mode
Mission challenge: reach GEO
Start from a 400 km low Earth orbit and estimate the total delta-v needed to reach a 35,786 km geostationary-altitude orbit.
km/s
MISSION 01
Low Earth Orbit → GEO
Departure altitude400 km
Target altitude35,786 km
Central bodyEarth
Project information
Built to make orbital mechanics visible
Orbit Transfer Lab is an independent aerospace engineering project created by Ved Patel. It connects physics, programming, and visual design to help students understand how spacecraft change circular orbits.
The model is educational and idealized. It does not include atmospheric drag, plane changes, finite burn duration, orbital perturbations, launch windows, or real mission constraints, and should not be used for operational mission planning.
HTMLCSSJavaScriptCanvas APITwo-body mechanics
References
Equations and constants can be checked against NASA educational resources, NASA planetary fact sheets, and standard introductory orbital mechanics texts. Planetary values in this simulator are rounded for educational use.