Compute the DV to escape from a body

The computation supposes an instantenous DV applied at one apse (either perigee or apogee). The final orbit is an hyperbola, with speed at infinity given as input parameter.

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)

Apse where DV is applied input (km) input (Earth Radii) input (Astronomical Units)

Final speed at infinity input (m/s)

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: 1998-12-10

Links:

Change between two elliptic orbits
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)
Apse where DV is applied	input (km)	input (Earth Radii)	input (Astronomical Units)
Final speed at infinity	input (m/s)
Inclination between orbits	input (degrees)