Path: Orbit/OrbitManeuver
% Computes the delta-v for a coplanar Hohmann transfer
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Form:
[dV, dV1, dV2, eT, aT] = DVHoh( r1, r2, v1, mu )
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Inputs
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r1 Radius 1
r2 Circular Orbit radius 2 (target)
v1 Velocity 1
mu Gravitational parameter
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Outputs
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dV Total required delta-v
dV1 Transfer ellipse injection delta-V
dV2 Final orbit injection delta-V
eT Eccentricity of the transfer orbit
aT Semimajor axis of the transfer orbit
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References: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
pp. 71-74.
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