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Path: Orbit/OrbitManeuver
% Computes the heliocentric departure vector for a spacecraft.
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Form:
b = VDA( d )
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Inputs
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d (:) Input data structure
d.rInjection (1,:) Injection radius
d.planet (1,:) Planet name
d.jD (1,1) Julian date
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Outputs
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b (:) Data structure
.v (3,1) Departure velocity
.dV (1,1) Delta V
.el (1,6) Elements
.
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Common: Time/Date2JD Common: Time/JD2T SC: Ephem/Planets SC: Ephem/SolarSys
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