Interplanetary Module

Directory List

AlphaCentauri

AlphaCentauriSystem	Model of the Alpha-Centauri system.
RHSAlphaCentauriMission	Simple dynamical model for a flight to Alpha-Centauri.

AsteroidProspector

GVEGuidance	Apply Gauss Variation Equations to determine in-plane thrust direction.
LowThrustDVToTransfer	Compute delta-v assuming full thrust applied during all transfer times.
LowThrustGVERHS	Right-hand side for low thrust GVE simulation.
LowThrustGVE_EventFcn	Stopping event function for low thrust GVE sim using ode solver.
LowThrustRendezvousSim	Simulation of low thrust maneuver to rendezvous with target orbit.
LowThrustTimeToTransfer	Compute the time to transfer each element from initial to target value.

Data

EarthMoonTraj.mat	Saved Earth/Moon trajectory.
NewHorizonsFlyby.txt	New Horizons trajectory data froomo Pluto flyby
TitanDensityData.mat	Data for Titan atmosphere density.
lnxp1600p2200.405	JPL ephemerides good through 2200

Demos/AlphaCentauri

AlphaCentauriApproach	Analysis of approach orbits to Alpha Centauri binary system
AlphaCentauriFlight	Simulate a mission to Alpha-Centauri.
AlphaCentauriGeometry	Draw the Earth-relative geometry of the Alpha-Centauri binary star system
AlphaCentauriMission	Alpha-Centauri mission
AlphaCentauriMissionDesign	Explore parameter space for straight-line interstellar mission
AlphaCentauriOpticalLink	Create an optical link budget for an Alpha-Centauri mission.
StarshipDesign	Design the starship

Demos/AsteroidProspector

AsteroidProspectorMars	Asteroid Prospector Mars mission planning.
AsteroidProspectorSim	Asteroid Prospector Simulation
AsteroidProspectorThrusterLayout	Analyze the thruster layout for the Asteroid Prospector spacecraft
AsteroidProxOpsDemo	Simulate proximity operations around an asteroid.
BuildAsteroidProspector	Build the CAD model of the Asteroid Prospector spacecraft.
DesignAsteroidProspector	Design a mission to visit an asteroid with a small satellite

Demos/Departure

TorqueDueToBField

Compute the torque due to the fusion engine magnetic dipole in Earth orbit

Demos/Enceladus

EnceladusCAD	Fusion Drive Enceladus Mission using an Orion capsule.
EnceladusMissionAnalysis	Enceladus mission

Demos/Ephemeris

EarthMarsAnimation	Animate the phasing of Earth and Mars over time.
EuropaEnvironment	Europa atmospheric density and Jupiter magnetic field near Europa.
JPLPlanetDemo	Demonstrate JPL ephemeris for the solar system.

Demos/Insertion

MarsApproach	Simulate an optimal approach and orbit insertion at Mars (fmincon)
MercuryApproach	Simulate an optimal approach and orbit insertion at Mercury (fmincon)
OptimalFmincon	Test fmincon against an analytical solution for the linear tangent law
PlutoApproach	Simulate an optimal approach and orbit insertion at Pluto (fmincon)
PlutoFlyby	Analyze hyperbolic flyby of Pluto

Demos/InterplanetaryOrbit

ApophisLambertTrajectory	Apophis 3D Lambert transfer delta-V analysis
ApophisOptimalTrajectory	Apophis 3D optimal trajectory with a linear regulator
ApophisTransfer	Compute a transfer from earth orbit to the asteroid Apophis.
EarthDeparture	Simulate a departure from the Earth
EarthMoonSunSim	Simulate a spacecraft in orbit near the earth and moon.
InterstellarSim	Interstellar mission simulation with a sun gravity assist.
LowThrustHeliocentricSim	Perform a heliocentric simulation from one circular orbit to another.
MarsOptimalTrajectory	Mars 3D optimal trajectory with a linear regulator
NBodySolarSystem	Simulate the solar system using an n-body model
SolarSailSim	Orbit simulation of a solar sail.
SpiralToHohmann	Spiral to a Hohmann Transfer to Apophis.

Demos/Landers

Lander2D	2D landing simulation using bilinear tangent thrust programming.
Lander3D	3D lander simulation using the bilinear tangent law.
LanderSizingDemo	Landing demo using bilinear tangent thrust programming.
LunarTakeoff3D	Lunar takeoff demo using bilinear tangent thrust programming.
Takeoff2D	Takeoff demo using bilinear tangent thrust programming.

Demos/LowEnergyManeuver

CRTBPExampleTrajectory	CRTBP Example Trajectory
EnergyMin4Body	Energy minimization in the 4 body problem.
LissajousOrbit	Compute the lissajous trajectory about a collinear libration point.
LoadFamilies	Periodic Orbit Families
LowEnergyMission	Low Energy Mission
PeriodicOrbitFamilies	Periodic Orbit Families
PlanetIDDemo	Planet id number from name.
PropagateDemos	Demonstrate propagation functions.
RefineXAxisInterceptDemo	Demonstrates RefineXAxisIntercept
Targeting	Demonstrate low-energy transfer targeting for a 3-body system
TwoDimensionalEscape	Simulate a low thrust departure from the Earth

Demos/Mars

EarthDepartureMars	Simulate a departure from the Earth
MarsFastOneWay	Fastest possible Mars one-way trip with fusion propulsion
MarsMission	Mars mission
MarsMoonSim	Spacecraft simulation around Mars with Phobos and Deimos
MarsPlanar	Mars planar orbit optimization - round-trip
MarsStraightLineSigma	Mars straight line trajectory

Demos/MissionAnalysis

JIMOMissionAnalysis	Compute the total delta-V for the JIMO mission
LowThrustMarsMission	Compute the delta-V for a low thrust mission to Mars synchronous orbit.
LowThrustMarsOptimalTransfer	Perform an optimal 2D transfer from Earth to Mars orbits.
MarsHohmannTransfer	Hohmann transfer to Mars.

Demos/OrbitOptimization

InterstellarAsteroid	Set up and run the trajectory optimization for an asteroid intercept.
MarsOptimalTransfer	Optimal 3D transfer to Mars, continuous thrust
Planet9	Optimal continous thrust transfer to Planet 9
ZermeloCostDemo	Compute the Zermelo cost function as a function of costate.
ZermeloOptimization	Demonstrate the Trajectory optimization using the Zermelo problem

Demos/PlanarOptimization

JupiterOneWayTrip	Jupiter planar optimization
LowThrustPlanar	Low-thrust Pluto trajectory
MercuryOneWay	Mercury planar optimization
Planar550AU	Planar orbit optimization to outside the solar system, 550 AU
PlutoPlanar	Pluto planar orbit optimization
TrajectoryOptimizationDemo	Demonstrate the 2D trajectory optimization function for low thrust.

Demos/Pluto

ChemicalMission	Chemical mission to Pluto
DFDPlutoMissionCAD	Generate Direct Fusion Drive (DFD) Pluto Orbiter CAD model
NewHorizonsPlutoFlyby	Load and plot the NewHorizons Pluto flyby
PlutoBeamedPower	Pluto mission beamed power
PlutoDFDMission	Pluto mission delta-Vs using DFD, Lambert solutions
PlutoGroundTrack	Generate a ground track on Pluto
PlutoLambertStudy	Lambert Delta-V to Pluto for fixed duration and variable start date
PlutoLander.mat	Saved lander configuration
PlutoLander3D	3D lander simulation at Pluto.
PlutoLanderCAD	Generate Pluto lander model
PlutoMission	Design a Pluto mission using DFD
PlutoSpacecraftData.mat	Saved fuel masses and powers.

Demos/ProMissions

DFDMarsMission	Direct Fusion Drive (DFD) Mars Mission using an Orion capsule.
DFDSpaceStation	Fusion Drive-powered space station design and CAD model.
EuropaMissionDesign	Design the Europa Clipper mission using a nuclear fusion engine.

Demos/SGLens

ConstantUEFlyby	Demo of an optimal flyby mission to the Solar Gravitational Lens
DataRateSGL	Data Rate at the Solar Gravitation Lens
DistanceStudy	Thrust and uE tradeoffs with mass flow to 550 AU SGL distance
EarthDepartureSGL	Simulate a departure from the Earth
MissionDurations	Explore mission duration parameterization to SGL distances
MissionSGL	Mission to SGL beyond 550 AU
MissionSGLCAD	Design a spacecraft for the Solar Gravitational Lens mission
SGLFlyby	Generate preliminary spacecraft design for the SGL flyby mission.
SGLOrbit	Calculate distance achieved for a 18 year mission

Demos/ThreeBody

EarthSpiralDemo

Simulates a spiral out from LEO.

Envionment

AtmDensMars2	Computes the atmospheric density of Mars.
AtmDensNeptune	Computes Neptune's atmospheric density using scale heights.
AtmDensTitan	Computes the atmospheric density of Titan using a curve fit.
AtmDensUranus	Compute the atmospheric density on Uranus.
BDipoleJupiter	Computes Jupiter's magnetic field based on a tilted dipole model.
BDipolePlanet	Computes the geocentric magnetic field based on a tilted dipole model.
NeptuneDensity	Compute the atm. density (kg/m^3) on Neptune given the altitude (km)
PlanetEnvironment	Compute the environment parameters for a selected planet.
PlanetWithTerrain	Generate vertices and faces for a planet with terrain.
PlanetaryAtmDens	Computes the atmospheric density for Earth, Mercury, Venus, Mars and Pluto.
PlanetaryDistanceToSun	Finds the distance to the sun and the solar flux.
PlanetaryRadiationAndAlbedo	Computes the albedo and radiation flux for planets.
TitanAtmosphere	Titan density model.

Ephemeris

ApophisOrbit	Generate elements and orbit state for the asteroid Apophis.
AsteroidProperties	Asteroid properties.
EarthHelioState	Compute the position and velocity of Earth in the heliocentric frame.
EclipseHelio	Determines eclipses in heliocentric coordinates.
GalileanSatelliteOrbits	Low precision orbits of the four major Galilean satellites.
InterpolateState	Interpolate a planet's state for a given Julian Date.
MarsRot	Computes the matrix that transforms from ECI to areographic axes.
PlanetHelioPhase	Compute the phase angle in the ecliptic plane of a given planet at jD.
PlanetId	Planet id number from name.
PlanetOpposition	Compute Julian Dates for times when two planets are closest.
PlanetPosJPL	Get positions for an array of planets using the JPL ephemeris.
PlanetPositionEMBarycenter	The position vectors, gravitational parameters and velocity for the planets.
PlanetWithTerrainPatch	Generate vertices and faces for a planet patch with terrain.
ReadAsteroidDatabase	Read in an asteroid database file and return elements
SolarSysJPL	Computes the JPL position vectors of the planets as a function of time.
SolarSysState	Computes planet heliocentric states for a range of dates.
astorbshort.dat	Short text file with astorb.dat asteroids

InterplanetaryOrbit

EarthOrbToHelioOrb	Computes the heliocentric orbital elements after an Earth escape spiral.
JDStartTransfer	Find the Julian Date for a straight line trajectory to the target
LambertDoubleRendezvous	Double rendezvous problem between two planets.
PlanetTransferLambert	Generate a Lambert transfer between two planets.
PropagateNBody	Propagate n-bodies in an n-body problem.
TwoDEscape	Simulate a low thrust departure from a planet

Landers

BilinearTangentAltitude	Bilinear tangent law for maximizing altitude on launch.
BilinearTangentLaw	Bilinear tangent law for orbit insertion or landing.
BilinearTangentVector	Bilinear tangent law in vector form for orbit insertion or landing.
FuelTimeOptimalAccel	Computes the optimal acceleration for a fuel/time problem.
LandingControl	Landing controller.
LandingControlBilinear	Implements a bilinear tangent landing controller.
LandingControlGravityTurn	Gravity turn landing controller.
LandingForce	Landing force in the body frame.

LowEnergyManeuver

CRTBP2kms	Scales CRTBP Jacobi coordinates to km and sec
CRTBPJacobiConstant	Calculate from Jacobi constant from a scaled state vector
CheckForOptimizationToolbox	Check to see if MATLAB contains the Optimization Toolbox
EnergyWRTMoon	Keplerian Energy with respect to the Moon.
IteratePeriodicOrbit	Compute a periodic orbit for a LET transfer.
J20002RotPuls	Transform from J2000 frame to rotating-pulsating
J20002RotPulsPlanetMoon	Transform a state vector from the J2000 reference frame to a rotating
Kms2CRTBP	Transform from km and sec to Jacobi coordinates for circular restricted
LETGuess	Compute a periodic orbit for a LET transfer.
LETPhasing	Calculate the nominal transfer time for a low energy transfer
LibrationCoeff	Compute the nth coefficient for the about a collinear libration point
LibrationData	Compute libration point data for the restricted three body problem.
LibrationRHS	Computes the time derivative of a state at a collinear libration point
LibrationRHSODE45	Compute the time derivative of a state at a collinear libration point,
Lissajous	Compute the lissajous trajectory about a collinear libration point
LowEnergyEarthToMoonTransfer	Compute a ballistic lunar capture trajectory from a circular Earth orbit
LowEnergyTransferInCRTBP	Calculate a low energy transfer in a CRTBP.
MinE4BP	Minimize the keplerian energy of the final state of a transfer orbit
PeriodicOrbitFromGuess	Find a second perpendicular crossing of the x-axis
PlotLET	Plot the Low Energy Transfer
PlotLET3BP	Plot the Low Energy Transfer, 3 Body Problem
Propagate3BP	Propagate a Sun-Earth 3BP with origin at the Earth system barycenter.
Propagate4BP	Propagate a Sun-Earth-Moon 4BP with origin at the Earth-Moon barycenter.
PropagateCRTBP	Propagate an arbitrary CRTBP with origin at the secondary body.
PropagateCRTBPBackwards	Propagate an arbitrary CRTBP with origin at the secondary body
PropagateCRTBPToPeriapse	Propagate the CRTBP initial state to the next perigee.
PropagateCRTBPToXAxis	Propagate the CRTBP equations of motion for arbitrary mu
RefineXAxisIntercept	Gain a precise X axis intercept with a good initial guess
RotPuls2J2000	Transform a state vector from a rotating pulsating reference frame to J2000
Targeting3BP2	Transfer a CRTBP LET to the restricted 3 body, non-planar problem.
Targeting4BP	Transfer a LET from the restricted 3BP to the Sun/Planet/Moon 4BP
V0FromJacobiConstant	Calculate an initial velocity from the jacobi constant
f16Data.mat	Markellos f16 family orbit data
f16Ref.mat	Markellos f16 family reference data
f16pData.mat	Markellos f16' family orbit data
f16pRef.mat	Markellos f16' family reference data
f17Data.mat	Markellos f17 family orbit data
f17Ref.mat	Markellos f17 family reference data
f17pData.mat	Markellos f17' family orbit data
f17pRef.mat	Markellos f17' family reference data
f18Data.mat	Markellos f18 family orbit data
f18Ref.mat	Markellos f18 family reference data
f18pData.mat	Markellos f18' family orbit data
f18pRef.mat	Markellos f18' family reference data
f19Data.mat	Markellos f19 family orbit data
f19Ref.mat	Markellos f19 family reference data
f19pData.mat	Markellos f19' family orbit data
f19pRef.mat	Markellos f19' family reference data
f20Data.mat	Markellos f20 family orbit data
f20Ref.mat	Markellos f20 family reference data
f20pData.mat	Markellos f20' family orbit data
f20pRef.mat	Markellos f20' family reference data
f26Data.mat	Markellos f26 family orbit data
f26Ref.mat	Markellos f26 family reference data
f26pData.mat	Markellos f26' family orbit data
f26pRef.mat	Markellos f26' family reference data

LowEnergyManeuverData

f16Data.mat	Markellos f16 family orbit data
f16Ref.mat	Markellos f16 family reference data
f16pData.mat	Markellos f16' family orbit data
f16pRef.mat	Markellos f16' family reference data
f17Data.mat	Markellos f17 family orbit data
f17Ref.mat	Markellos f17 family reference data
f17pData.mat	Markellos f17' family orbit data
f17pRef.mat	Markellos f17' family reference data
f18Data.mat	Markellos f18 family orbit data
f18Ref.mat	Markellos f18 family reference data
f18pData.mat	Markellos f18' family orbit data
f18pRef.mat	Markellos f18' family reference data
f19Data.mat	Markellos f19 family orbit data
f19Ref.mat	Markellos f19 family reference data
f19pData.mat	Markellos f19' family orbit data
f19pRef.mat	Markellos f19' family reference data
f20Data.mat	Markellos f20 family orbit data
f20Ref.mat	Markellos f20 family reference data
f20pData.mat	Markellos f20' family orbit data
f20pRef.mat	Markellos f20' family reference data
f26Data.mat	Markellos f26 family orbit data
f26Ref.mat	Markellos f26 family reference data
f26pData.mat	Markellos f26' family orbit data
f26pRef.mat	Markellos f26' family reference data

Mechanics

C3ToV	Convert c3 to orbital velocity
EclipticInjectionPlane	Computes the parking orbit plane for a heliocentric injection.
FlybyHyperbola	Compute the required orbital elements for a flyby
OrbitLoweringManeuvers	Lower orbits starting from a hyperbolic orbit
PatchedConicElements	Computes patched conic elements.
PatchedConicPlanner	Helps design patched conic trajectories.
PorkChopMin	Search for multiple minima in a porkchop plot
PorkChopTOF	Generate time of flight porkchop plot with TOF vs departure data
PorkChopTOFKepler	Generate time of flight porkchop plot with delta-V per departure data
SphereOfInfluenceHelio	Computes the ratio of the sphere of influence for interplanetary
SynodicPlanets	Computes the synodic period from planets.

Optimization

FindDepartureDate	Find the best departure date for TrajectoryBetweenTwoPlanets
OrbitRoundTripTransferTimes	Compute transfer start times for a round trip between orbits.
PlanarHelioOptimal	Compute coplanar optimal trajectory, direct method, with fmincon.
PlanarHelioOptimalSlidingTime	Compute optimal trajectory
RHS2DCylindricalOrbit	RHS for constant thrust in cylindrical coordinates.
SimulatePlanarHelioTrajectory	Simulate a planar heliocentric trajectory
TrajectoryBetweenTwoPlanets	Optimal 3D trajectory between two planets, fixed time (fmincon)

OrbitCoord

ECIToSunEarthRot	Convert ECI to Sun Earth rotating coordinates about the barycenter.
HelioFromPlanetInit	Initialize a heliocentric orbit from a planet centered orbit.
HelioToBPlane	Transformation matrix from the heliocentric to B-plane frame.
HelioToPlanet	Computes the transformation matrix from heliocentric to planet fixed frame.

OrbitInsertion

ApproachConst2D	Equality constraints for the 2D orbit insertion problem.
ApproachConst2DIneq	Equality constraints for the 2D orbit insertion problem.
ApproachCost2D	Cost for the landing for a 2D orbit problem.
ApproachCost2DMag	Cost for the landing for a 2D orbit problem.
RHS2DAnglePolarOrbit	RHS for 2D polar orbit, angle formulation
Simulate2DApproach	Simulate a 2D planetary approach
TrueAnomalyStartHyperbola	Starting true anomaly to reach a true anomaly in time t

RHSFunctions

FEarthMoon	Gravity acceleration in the earth moon system
FEarthMoonSun	Orbit dynamics with spherical harmonic models of the Earth and Moon gravity.
FHel	Orbit equations for InterstellarSim.
FSolarSail	Solar sail simulation right hand side.
RHSCRTBP	Compute the RHS of the CRTBP equations of motion.
RHSHelioWithPlanets	Right hand side for a heliocentric system with a thruster.
RHSMarsOrbit	Right hand side for a Mars orbit simulation.

ThreeBody

CRTBPJacobi	Compute the Jacobi constant for a state in the CRTBP system.
CRTBPLinearSystem	Compute linear system matrix for the circular restricted 3 body problem
CRTBPRHS	Right-hand-side for the circular restricted three body problem.
EarthEscape	Simulate an escape trajectory from Earth using CRTBPRHS.
FCRTBPRHS	Right-hand-side for the forced circular restricted three body problem.
HALOFamily	Compute and plot a family of stable HALO orbits in the given system
HALOInit	Compute a stable initial state for a HALO orbit
HALOState	Approximate an initial state for a HALO orbit given the orbit size
L2OrbitSim	Simulate the Earth orbit to L2 point low thrust transfer.
LEOToSunEarthL2Design	Design a low thrust transfer from Earth orbit to Sun/Earth-Moon L2 point
LowThrustCRTBP_StopFcn	Stoppping Function for the circular restricted three body problem.
LyapunovFamily	Generate a family of planar Lyapunov orbits
LyapunovInit	Compute a stable initial state for a Lyapunov orbit

VehicleDesign

NeptuneAirshipSizing	Size an airship to operate with neutral buoyancy on Neptune.
UranusAirshipSizing	Size an airship to operate with neutral buoyancy on Uranus.

Visualization

HALOPlot	Generate a plot of a HALO trajectory
HelioPlot	Plot planets and a trajectory in the heliocentric frame.
L2OrbitPlots	Simulate and plot an Earth orbit to L2 point low thrust transfer.
PlanetAlignments	Plots planet alignments fur successive synodic periods.
PlanetPhasing	Compute and plot positions of planet1 and planet2 at the specified times.
PlanetTrajectoryPlot	Plots a spacecraft between two planets
PlotBPlane	B-plane plots using HelioToBPlane.
PorkChopPlot	Create the porkchop plot from the delta-V array and dates

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