Path: Missions/AlphaCentauri
% Simple dynamical model for a flight to Alpha-Centauri.
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Form:
xDot = RHSAlphaCentauriMission( x, t, d )
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Inputs
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x (7,:) [r;v;m] Position, velocity, and spacecraft mass
in km, km/s, kg. If no thrust: set m=0.
t (1,1) Time in seconds after jD0
d (1,1) Structure
.center (1,1) 1 = sun, 2 = alpha-centauri
.thrust (1,3) Thrust vector in N (m>0 only)
.uE (1,1) Exhaust velocity in m/s (m>0only)
.mDry (1,1) Dry mass in kg (m>0 only)
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Outputs
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xDot (7,:) [v;a;mDot], time derivative of each element of
x in km/s, km/s^2, kg/s
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See also AlphaCentauriFlight
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AC: ACData/ACTConstants Missions: AlphaCentauri/AlphaCentauriSystem SC: Ephem/SunV1 SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/xSplashSmall Common: Database/Constant Common: General/DeBlankLT Common: General/DeleteCell Common: Graphics/AssignColors Common: Graphics/NewFig Common: Graphics/PltStyle Common: Graphics/TitleS Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2000 Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit Math: Trigonometry/CosD Math: Trigonometry/SinD
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