Path: Orbit/OrbitManeuver
% Delta-V to change apogee.
Computes the delta-v needed to go from a transfer orbit to a final orbit
with a plane change. Assumes that the node line coincides with the line
of apsides.
If there are no arguments a figure is created.
--------------------------------------------------------------------------
Form:
[dV, theta] = ApogeeDV( eT, iT, a2, e2, i2, mu )
ApogeeDV( eT, iT, a2, e2, i2 ); % create plot
--------------------------------------------------------------------------
------
Inputs
------
eT eccentricity of the transfer orbit
iT inclination of the transfer orbit (rad)
a2 semi-major axis of the final orbit
e2 eccentricity of the final orbit
i2 inclination of the final orbit (rad)
mu gravitational parameter (default Earth, km^3/sec^2)
-------
Outputs
-------
dV total delta v
theta angle of burn with respect to the final
velocity vector
--------------------------------------------------------------------------
References: Kaplan, M., Modern Spacecraft Dynamics and Control, John
Wiley & Sons, p. 91.
--------------------------------------------------------------------------
Orbit: OrbitCoord/A2Apogee Common: Graphics/AxesCart Common: Graphics/Map
Back to the Orbit Module page