Path: Interplanetary/Mechanics
% Generate time of flight porkchop plot with delta-V per departure data
The delta velocity computed is the total for both departure and arrival.
Each row of dV is a particular time of flight and column is a particular
date. This function only handles single arcs. Multiple revolutions are
not allowed. If there are no outputs the function creates two plots, one
of the porkchop and a second of the miniumum delta-V Lambert transfer.
The departure planet can be any major planet (including Pluto) and is
defined by name and ephemeris computed with PlanetPosJPL (ecliptic
plane). The arrival planet is defined by Keplerian elements. For example,
as done in the demo:
dateRange = [Date2JD([2005 6 20]) Date2JD([2005 11 7])];
tOFRange = [125 450]; % days
[elA, ~,~, jD] = ApophisOrbit;
PorkChopTOFKepler(dateRange,tOFRange,'Earth',[elA jD]);
Type PorkChopTOF for a demo of Earth to Apophis trajectories.
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Usage:
PorkChopTOFKepler; % demo
[dV,tOF] = PorkChopTOFKepler(dateRange,tOFRange,planetDep,planetArr,nDate,nTOF)
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Inputs
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dateRange (1,2) [jDStart jDEnd] (Julian day number)
tOFRange (1,2) [tOFStart tOFEnd] (days)
planetDep (1,:) Departure planet (Only major planets)
planetArr (1,7) [Arrival planet elements (6) jDEpoch (1)]
nDate (1,1) Number of dates (default 90)
nTOF (1,1) Number of TOF (default 200)
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Outputs
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dV (nDate,nTOF) Delta V required (km/s)
tOF (nDate,nTOF) Time of flight
jDDep (nDate,nTOF) Departure dates
jDArr (nDate,nTOF) Arrival dates
tM (nDate,nTOF) Transfer type. 1: <180 degrees, -1: >180 degrees
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Interplanetary: Ephemeris/ApophisOrbit Interplanetary: Ephemeris/PlanetPosJPL Orbit: OrbitControl/DVTarget Orbit: OrbitMechanics/LambertTOF Orbit: Visualization/PlotLambertTransfer Orbit: Visualization/PorkChopPlot SC: BasicOrbit/El2RV SC: BasicOrbit/Period Common: Database/Constant Common: General/StringMatch Common: Time/Date2JD Math: Linear/Cross Math: Linear/Dot Math: Linear/Mag
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