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