Compute the DV to change between two elliptic orbits

The computation supposes an instantenous DV applied at one apse (either perigee or apogee)

Mass of Central Body input (kg) input (Earth = 1) input (Sun = 1)

Opposite Apse of Initial Orbit input (km) input (Earth Radii) input (Astronomical Units)

Common Apse of Both Orbits input (km) input (Earth Radii) input (Astronomical Units)

Opposite Apse of Final Orbit input (km) input (Earth Radii) input (Astronomical Units)

Inclination between orbits input (degrees)

Initial Orbit Speed at m/s

Final Orbit Speed at m/s

DV m/s

Page under construction. Suggestions or requests are welcome

Created: 1998-05-04
Modified: 2001-08-22 with the collaboration of José Roberto de Castro Andrade

Links:

Change from an elliptic to a hyperbolic orbit
Other hard science fiction tools
Alberto Monteiro's home page
The constants were taken from JPL Solar System Dynamics page

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Mass of Central Body	input (kg)	input (Earth = 1)	input (Sun = 1)
Opposite Apse of Initial Orbit	input (km)	input (Earth Radii)	input (Astronomical Units)
Common Apse of Both Orbits	input (km)	input (Earth Radii)	input (Astronomical Units)
Opposite Apse of Final Orbit	input (km)	input (Earth Radii)	input (Astronomical Units)
Inclination between orbits	input (degrees)