Path: LunarMissions/LunarMission
% Generate transfer orbit elements for a lunar mission.
Uses the JPL Ephemerides for the Earth and moon. The target is the
perilune altitude of the hyperbolic passage of the moon. The function
propagates the resulting trajectory using ode113. It propagates to the
target point. You can specify radius of perilune and orbit inclination.
This function uses Lambert to target a point on the Earth/Moon interface.
The point is where the hyperbolic passage of the moon starts. This
justifies the single body Lambert solution.
The spacecraft starts in any Earth orbit.
Requires fmincon in the optimization toolbox. See fmincon for the
definition of the argument opts.
Type LunarTargeting for a demo.
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Form:
[x0,eL,v,jD0] = LunarTargeting( date, a0, rP, inc, fIf, opts )
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Inputs
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date (1,:) Date [yy mm dd hh mm ss] or Julian date
of lunar encounter. "Encounter": When spacecraft reaches
earth/moon interface.
el0 (1,5) Initial keplerian orbital elements [a,i,W,w,e] in km and
radians
rP (1,1) Desired perilune distance (km)
inc (1,1) Desired Lunar orbit inclination (rad)
fIf (1,1) The Earth/Moon gravitational interface point from the
moon
simJDP (1,1) Logical. If false, jDP is computed from Keplerian lunar
elements. If true, jDP is computed more accurately via
simulation. Default: False
opts (.) Optimization tolerance data structure
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Outputs
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x0 (1,6) Initial state [r,v] in km and km/s
elL (6,1) Final lunar keplerian orbital elements [a,i,W,w,e,M] in
km and radians
v (3,2) Initial and interface velocity in km/s
jD0 (1,1) Start Julian date
jDP (1,1) Julian date of perilune
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Orbit: OrbitMechanics/APlanet Orbit: OrbitMechanics/LambertTOF Orbit: Visualization/EarthMoon SC: BasicOrbit/El2RV SC: BasicOrbit/Period SC: BasicOrbit/RV2El SC: Ephem/PlanetPosJPL Common: General/HasOptimizationToolbox Common: Graphics/Plot3D Common: Graphics/TimeLabl Common: Time/Date2JD Math: Linear/Mag
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