WalkerConstellation | Compute orbital elements for a Walker constellation. |

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GravityCompare | Compare gravity models |

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HelioTrajectorySimulation | Set up and run a heliocentric trajectory simulation with two objects. |

SpiralToHohmann | Spiral to a Hohmann Transfer to Apophis. |

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ApophisTransfer | Compute a transfer from earth orbit to the asteroid Apophis. |

RelativeOrbitControl | Simulates two orbits and applies a relative controller. |

TargetDemo | Demonstrates the Lambert targeting function DVTarget. |

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TestComputeTLE | Test ComputeTLE |

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ComStarAKMDV | Plan the AKM burn by looking at the AKM thrust variations as a function of temperature. |

DragCompensationDemo | Demonstrates drag compensation maneuvers. |

GEOStationKeeping | GEO Stationkeeping Example |

GeoOrbitSim | Low thrust geo transfer |

GeoTransferSim | Low thrust geo transfer |

InsertionDeltaV | Computes the insertion delta-V for a Hohmann transfer. |

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 transfer from earth to mars orbits. |

MarsHohmannTransfer | Hohmann transfer to Mars. |

OrbMnvrDemo | Runs demonstrations of selected orbit maneuver functions. |

OrbitPlaneChange | Inclination Change |

OrbitSeparationSimulation | Orbit separation simulation with discrete delta-Vs |

OrbitSeparationTradeStudy | Orbit separation demo |

TDV | Demonstrate the various orbit change functions. |

TDVDisp | Compute delta-v dispersions given declination and velocity errors. |

TwoBurnGeoTransfer | Delta-V for a Hohmann transfer between LEO and GEO. |

TwoStageDesign | Computes a preliminary design of a two stage to orbit vehicle. |

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ComStarFBudget | Demonstrate a fuel budget for the ComStar satellite. |

LunarOrbitSim | Propagate an orbit about the moon. Show the visibility sun, earth, moon. |

SunSynchElements | Sun-Synchronous Orbit Demo |

TNORAD | Demo two of the five NORAD element propagators. |

TwoOrbSim | Generates two orbits and plots their relative positions |

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DragDemo | Demonstrate drag reentry. |

GravityModelDemo | Demonstrate using an external gravity model with PropagateOrbitPlugIn. |

IntegrationAccuracyDemo | Integration Accuracy for PropagateOrbitPlugin. |

LowThrustDemo | Demonstrate low thrust transfer using PropagateOrbitPlugIn. |

OPBatchDemo | Demonstrate using PropgateOrbitPlugin in batch |

PropagatorComparison | Integration accuracy study comparing RK4, RK45, and ode113. |

TopexDemo | Compare various orbit propagators with a Topex ephemeris. |

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EarthMoonSunSim | Simulate a spacecraft in orbit near the earth and moon. |

EarthOrbitDragDemo | Simple demo to compute drag over one orbit |

EarthOrbitSim | Simulates a spacecraft in earth orbit with spherical harmonics. |

GeoSim | Using a spherical harmonic gravity model |

InterstellarSim | Interstellar mission simulation with a sun gravity assist. |

LEOPAnalysis | Perform LEOP (Launch and Early Analysis Phase) analysis. |

LinOrbitDemo | Linear orbit simulation. This compares nonlinear with linear. |

LowThrustEscapeSim | Simulates a low thrust escape from an earth orbit. |

LowThrustHelicocentricSim | Perform a helicocentric simulation from one circular orbit to another. |

NBodySolarSystem | Simulate the solar system using an n-body model |

RelativeOrbitSim | Simulates two orbits and plots their relative positions. |

SolarSailSim | Orbit simulation of a solar sail. |

TOrbit | Investigate orbit coordinate systems. |

TVarEq | Simulate an orbit using the variational equations. |

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EarthSpiralDemo | Simulates a spiral out from LEO. |

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MarsOrb | Generates a Mars orbit plot. |

OrbViewDemo | Demonstrate the OrbView function. |

RelMotionVis | Visualize relative orbital motion in the inertial frame. |

SphericalHarmonicPlot | Demonstrate a high order gravity model. |

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CWSimAndPlot | Visualize a set of maneuvers propagated with Clohessy-Wiltshire equations. |

ClohessyWiltshire | A special formulation of the Clohessy-Wiltshire equations. |

DVGlideslope | Form: |

GlideslopeCircumnav | Form: |

GlideslopeGuidance | Form: |

GlideslopePlanner | Calculate sequential glideslope maneuvers for planning purposes. |

SolveT | Form: |

SolveTD | Form: |

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EarthGravityModel.mat - Earth GEMT1 model in a mat file. | |

GEMT1.geo - GEMT1 gravity model. | |

GravityMap | Create a gravity map from a gravity model. |

JGM2.geo - JGM2 gravity model. | |

JGM3.geo - JGM3 gravity model. | |

LoadGEM | Load the GEMT1 data. |

LoadGravityModel | Load a spherical harmonic gravity model from GSFC/University of Texas at Austin. |

LoadLP150Q | Load the LP150Q Lunar gravity model. |

LoadSGM150 | Load the SGM150 Lunar gravity model. |

LunarGravityModel.mat - Gravity model based on Lunar Prospector, 75x75 | |

NormalizationMatrix | Generate a normalization matrix for spherical harmonics |

ProcessASCIIGravityModel | Process an ascii file of spherical harmonic coefficients. |

SEMGravAcc | Computes the acceleration due to the Sun and the Earth/Moon. |

UnnormalizeGravity | Remove normalization from a gravity model |

WGS84.geo - WGS84 gravity model. | |

jgl075g1.sha - Lunar spherical harmonic ASCII file |

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ApophisOrbit | Generate elements and orbit state for the asteroid Apophis. |

EarthHelioState | Compute the position and velocity of Earth in the heliocentric frame. |

EarthOrbToHelioOrb | Computes the heliocentric orbital elements after an Earth escape spiral. |

EclipticInjectionPlane | Computes the ECI parking orbit plane for a heliocentric injection. |

ForceSimple | Simple thruster force model for orbit simulations |

GravityHelio | Calculate the heliocentric gravity for the position and date. |

HelioFromPlanetInit | Initialize a heliocentric orbit from a planet centered orbit. |

HelioToBPlane | Transformation matrix from the heliocentric to B-plane frame. |

JDStartTransfer | Find the Julian Date for a straight line trajectory to the target |

LambertDoubleRendezvous | Double rendezvous problem between two planets. |

NoForce | Thruster force model producing zero force. |

PlanetAlignments | Plots planet alignments fur successive synodic periods. |

PlanetHelioPhase | Compute the phase angle in the ecliptic plane of a given planet at jD. |

PlanetOpposition | Compute Julian Dates for times when two planets are closest. |

PlanetPhasing | Compute and plot positions of planet1 and planet2 at the specified times. |

PlanetTransferLambert | Generate a Lambert transfer between two planets. |

PlotBPlane | B-plane plots using HelioToBPlane. |

RHSTrajectory | Right-Hand-Side function for solar system object trajectories |

SolarSysState | Computes planet heliocentric states for a range of dates. |

SynodicPlanets | Computes the synodic period from planets. |

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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 |

LETGuess | Compute a periodic orbit for a LET transfer. The orbit has nearest periapsis |

LETPhasing | Calculate the nominal transfer time for a low energy transfer |

LowEnergyEarthToMoonTransfer | Compute a ballistic lunar capture trajectory from a circular 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 for a 3 body problem in a Non-Rotating |

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 |

Targeting4BPB | Obtain a refined maneuver magnitude for transferring an orbit from the |

V0FromJacobiConstant | Calculate an initial velocity from the jacobi constant |

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ApogeeRaisingDeltaV | Compute two delta-v's to raise the apogee and circularize the orbit. |

DVTarget | Perform targeting using the Lambert algorithm. |

DiscreteTrajectoryToDeltaV | Compute accelerations for a point to point trajectory. |

DoDeltaV | Updates orbital elements based on an impulsive delta-V |

FLambert | Right hand side for locally optimizing the Lambert time of flight problem. |

LQOrbitController | Creates a linear quadratic relative orbit controller. |

LambertOpt | Use Lambert with Nelder-Meade simplex optimization of start and transfer time |

LowThrustControl | Low thrust control. |

RendezvousPlanner | Compute delta-Vs for rendezvous. |

TransferTimeToDV | Converts the transfer time to delta-V for a rendezvous. |

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A2Apogee | ------------------------------------------------------------------------- |

A2Perige | Computes the perigee radius from a. |

AB2RADec | Convert angles to right ascension and declination |

AE2RPRA | Converts semi-major axis and eccentricity to right perigee and apogee. |

AE2VR | Computes v and r given a, e and nu. |

AENuToVelAltFpa | Convert semi-major axis & ecc. to velocity, altitude, flight path angle |

AERToNu | Converts semi-major axis, eccentricy and r to true anomaly. |

Alfriend2El | [a,th,i,q1,q2,W] -> [a,i,W,w,e,M] |

BarycenterEarthMoon | Computes the ECI position of the Earth-Moon Barycenter. |

CEcl2SER | Transformation matrix from ecliptic to Sun-Earth rotating frame. |

CEq2C | Transformation matrix from equinoctial to cartesian coordinates. |

CRTBP2kms | Scales CRTBP Jacobi coordinates to km and sec |

CT2R | Converts tangential accelerations into radial using the true anomaly. |

CT2REl | Converts tangential accelerations into radial using the elements vector. |

CT2REq | Converts tangential accelerations into radial using equinoctial elements. |

CartOrb2Cyl | Convert a cartesian orbit state to cylindrical orbit coordinates. |

CircularOrbitState | Compute inertial position and velocity given circular orbit elements |

ComputeTLE | Compute two-line elements from osculating elements |

ConvertNORAD | Convert NORAD TLE string into a data structure. |

CylOrb2Cart | Convert a cylindrical orbit state to a cartesian orbit. |

E2RAORP | Ratio of apogee radius to perigee radius given eccentricity for an ellipsew |

ECEFToECI | Compute the transformation matrix that rotates ECEF to ECI coordinates. |

ECI2OrbitPlane | This function takes a position vector and orbit normal vector in ECI |

ECIToEarthMoonRot | Convert ECI to Earth Moon rotating coordinates about the barycenter. |

ECIToRLP | Transform from ECI to Rotating Libration Point Coordinates |

ECIToSunEarthRot | Convert ECI to Sun Earth rotating coordinates about the barycenter. |

EMBToEMBND | Scale EMB system to be non-dimensional |

ENUToECEF | Compute the transformation matrix that rotates ENU to ECEF coordinates. |

El2Alfriend | Convert the standard orbital element set into an Alfriend orbital element set |

El2Eq | Converts conventional elements to equinoctial elements. |

El2LKl | Converts orbital elements to commonly used angular quantities |

Eq2El | Converts equinoctial elements to Keplerian elements. |

Eq2RV | Converts equinoctial elements to r and v for an elliptic orbit. |

FPA | Computes the flight path angle from eccentricity and true anomaly. |

HelioToPlanet | Computes the transformation matrix from heliocentric to planet fixed frame. |

InitialOrientation | Compute the initial quaternion and body rates for a circular orbit, |

J20002RotPuls | Transform from J2000 to rotating-pulsating |

J20002RotPulsPlanetMoon | Transform a state vector from the J2000 reference frame to a rotating |

K2L | Converts eccentric longitude to true longitude |

Kms2CRTBP | Transform from km and sec to Jacobi coordinates for circular restricted |

L2K | Converts eccentric longitude to true longitude |

LatLonToRAz | Compute range and azimuth angle between two points on a sphere. |

LocusOfVisibility | Determine the locus of visibility for a satellite above a planet. |

M2NuS | Computes true anomaly from a series expansion |

ML2K | Eccentric longitude from the mean longitude by solving Kepler's equation. |

ML2KApp | Approximate eccentric longitude from the mean longitude. |

OrbElemDiff | Computes the differences between orbital element vectors. |

OrbNEl | Conmputes the orbit normal from orbital elements. |

OrbNEq | Computes the orbit normal from equinoctial elements. |

OrbitClosestPoint | Computes closest orbit point to points on the earth. |

OrbitalPlane | Display the orbital plane with the Earth. |

OverArea | Determine whether r is in a area on the surface of an Earth sphere |

Parameter | Computes the parameter for any orbit. |

PtchCnc | Computes planet centered orbital elements. |

RARP2A | Computes the semi major axis from apogee and perigee radii |

RARP2E | Computes the eccentricity from apogee and perigee radii |

RAzToLatLon | Transform (range,azimuth) to (latitude,longitude) coordinates. |

REl | Computes the orbit radius and the parameter from Keplerian elements. |

REq | Computes the orbit radius and the parameter from equinoctial elements. |

RHAzToECEF | Transform (range,azimuth) to (latitude,longitude) coordinates |

RLagrange | Computes a collinear Lagrange point. |

ROrb | Computes the orbit radius. |

RPQ | Computes the orbit position vector in the perifocal plane. |

RPRA2AE | Converts perigee and apogee to semi-major axis and eccentricity |

RPV2AE | Converts perigee and velocity at perigee to a and e |

RToNu | Computes true anomaly from semi-major axis, eccentricity and radius. |

RV2AE | Converts R and V to a, e, rP and rA. |

RV2Eq | Converts R and V to Equinoctial elements |

RV2RADec | Right ascension and declination with their rates from position and velocity vectors. |

RelativeCoord | Computes relative coordinates between two orbits. |

RelativeOrbitState | Find the relative coordinate state vector between x2 and x1. |

RotPuls2J2000 | Transform a state vector from a rotating pulsating reference frame |

SEMIToSEMR | Transform pos. and vel. from inertial heliocentric frame to |

SEMRToSEMI | Transform from Sun-Earth/Moon rotating to inertial frame |

SEMToSEMND | Scale position and velocity in SEM system (rotating or inertial) by |

SLR | Computes the semi-latus rectum. |

TEMEToPEF | Computes the matrix from TEME to the pseudo-earth fixed frame. |

TransformECIToEMBR | Transform ECI pos. and vel. to Earth Moon barycenter rotating frame. |

TransformECIToSEMR | Transform ECI pos. and vel. to Sun-Earth-Moon rotating (SEMR) frame. |

TransformEMBRToECI | Transform pos. and vel. from Earth Moon barycenter rotating frame to ECI |

TransformSEMRToECI | Transform Sun-Earth-Moon rotating (SEMR) state to ECI frame. |

TransformSEMRToHelio | Transform Sun-Earth-Moon rotating (SEMR) state to the heliocentric frame. |

TrueAnomalySpacing | Generates an array of true anomalies. |

VPQ | Computes the orbit velocity in the perifocal plane. |

VR2AE | Computes sma and eccentricity given v and r. |

VelAltFpaToAENu | Converts flight path angle, velocity and r to orbital elements. |

VelAltFpaToHAE | Compute (VF,gammaF) at hF from (V0,gamma0) at h0. |

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EarthMoonSystemConstants | Specifies Earth-Moon system constants |

LEOData.mat - Sample LEO orbit data. | |

MirNORAD.txt - Mir NORAD elements data. | |

ReadHorizons | Reads in JPL Horizons data. |

SunEarthMoonSystemConstants | Specifies Sun-Earth-Moon system constants. |

earthmap.fig - 3D Earth map in Normalized Earth-Fixed Coordinates. | |

mir.txt - Mir NORAD elements. | |

sdp.txt - SDP NORAD 2 line elements test data | |

sgp.txt - SGP NORAD 2 line elements test data |

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AccelToThrustAndQ | Convert an acceleration vector into a thrust quaternion. |

ApogeeDV | Delta-V to change apogee. |

ChangePerigee | Compute the delta V required to change perigee |

CircularManeuver | Compute maneuver profile for a circular maneuver. |

DVAKM | Computes the temperature required to achieve the desired delta-V. |

DVDisp | Computes the velocity and inclination errors for a delta V burn |

DVGeoTrx | Delta-V needed to control the longitudinal acceleration in geo. |

DVHoh | Computes the delta-v for a coplanar Hohmann transfer |

DVHohE | Computes two impulses needed to transfer between two elliptical coplanar orbits. |

DVIDrift | Computes inclination drift for geosynchronous orbits. |

DVLowThrust | Delta-V from a circular to noncoplanar circular orbit. |

DVOCCapt | Computes the optimal circular capture radius and delta-v. |

DVOHohmn | Delta-v for injection into an interplanetary orbit using Olberth's method. |

DVReentry | Computes the delta-V for reentry from a near-circular orbit. |

HohmannTransferRendezvous | Compute delta-Vs for rendezvous using Hohmann transfers. |

LTSpiral | Low thrust delta v between two circular orbits. |

LTVCon | Solve the Linear Terminal Velocity Constraint problem. |

LowThrustEscape | Compute the delta-V required for a low thrust escape. |

ManeuverDuration | Compute maneuver duration given constant thrust. |

ManeuverEnvelope | Compute the maneuver envelope for a spacecraft rotating around another. |

OrbMnvrBielliptic | Delta-V for a bielliptic orbit maneuver between circular orbits. |

OrbMnvrCircularize | Computes the delta-V for a 2-burn transfer to a circular orbit at rF. |

OrbMnvrHohmann | Computes the delta-V for a Hohmann transfer between circular orbits. |

OrbMnvrInclAndHohm | Delta-V for a Hohmann transfer between circular non coplanar orbits. |

OrbMnvrInclination | Computes the delta-V for an inclination correction. |

OrbMnvrInsertion | Computes the delta-V to insert into a planetary or lunar orbit. |

OrbMnvrLongAndIncl | Delta-V for an longitude and inclination change maneuver for a circular orbit. |

OrbMnvrLongitude | Computes the delta-V for a longitude only maneuver for a circular orbit. |

OrbMnvrLowerApogee | Computes the delta-V to lower apogee. |

OrbMnvrOneTangent | Computes the delta-V for a one-tangent transfer between coplanar orbits. |

OrbMnvrPerigee | Compute the delta V required to change perigee. |

OrbMnvrPhaseChange | Computes the delta-V for a phase change. |

OrbMnvrSemimajor | Computes the delta-V for a change in semi-major axis. |

PatchedConicPlanner | Helps design patched conic trajectories. |

SemimajorAxisRevisit | Computes semi-major axis from revisit and swath angle. |

TransferAndPhaseAngle | Computes the transfer and phase angle given transfer time. |

TriangularManeuver | Compute maneuver profile for a triangular maneuver. |

TrxCntrl | Plans delta-v maneuvers to correct triaxial motion. |

VDA | Computes the heliocentric departure vector for a spacecraft. |

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AFLTSpiral | Low thrust delta v between two circular orbits. |

AGravity | Compute the gravitational acceleration in spherical coordinates. |

AGravityC | Compute the gravitational acceleration in cartesian coordinates. |

APlanet | Perturbing acceleration due to a planet on a spacecraft. |

AZLaunch | Launch azimuth to achieve a desired orbit inclination. |

BallisticCoefficient | Compute the ballistic coefficient from a CAD model. |

C3ToV | Convert c3 to heliocentric velocity |

CylOrb | Right-hand-side of the cylindrical orbit equations about a mass point. |

DVOrbitDrag | Compute the drag loss over an orbit arc in planetary orbit. |

EclipticInjectionPlane | Computes the parking orbit plane for a heliocentric injection. |

Energy | Compute the energy for any orbit |

FBudget | Computes a fuel budget from a list of events. |

FlightPathAngle | Compute the flight path angle for a Cartesian state. |

FlightPathAngleFromCartEl | Compute the flight path angle from elements |

Flyby | Calculates orbital elements and perigee radius for a planetary flyby. |

FlybyHyperbola | Compute the required orbital elements for a flyby |

GVEDynamics | Compute continuous-time relative dynamics for Gauss' variational equations |

GetFuelBudgetDataFromCAD | Compute the power balance in a spacecraft. |

GroundCoverage | Compute ground coverage for an orbit. |

HEl | Computes orbit angular momentum from the elements vector. |

HEq | Calculates the orbit angular momentum given the input in equinoctial elements |

IDrift | Computes the inclination rate of an earth orbit due to the sun. |

InclinationRate | Finds the inclination rate and orbit normal vector. |

J2OrbitEffects | Compute J2 effects on the orbital elements. |

J2Prop | Propagate an ECI state into the future with the J2 perturbation. |

LTAN | Compute the local time of the ascending node. |

LambertTOF | Solves the Lambert time of flight problem using Battin's method. |

LoadNORAD | Load a set of historical NORAD elements and convert to Cartesian states. |

LonMot | Computes the longitudinal motion due to an acceleration a |

MeanAnom | Computes the mean anomaly from change in time |

MeanMotn | Computes the mean orbit rate for an elliptic orbit |

N2A | Computes the semi-major axis given the mean orbit rate. |

NORAD | Propagates the NORAD two line elements, ex. SGP, SGP4, SGP8. |

NORADToEl | Convert NORAD to Keplerian elements. |

NonDimensionalOrbit | Dimensionalize or non-dimensionalize an orbit. |

NuInf | Computes the asymptote angle for a hyperbola. If e is < 1 it substitutes 1. |

OptDIH | Optimal inclination corrections for a Hohmann transfer with a plane change. |

OrbDecay | Approximate time for an orbit to decay based on an exponential atmosphere. |

OrbitDrag | Approximate the acceleration due to drag over an orbit arc, h0 to hF. |

OrbitFromSynodic | Computes the elements of an orbit with the desired synodic period. |

OrbitInsertion | Compute orbit insertion velocity and flight path angle. |

OrbitJacobian | Computes the Jacobian for a spherical planet gravity model. |

OrbitVel2D | Compute (VF,gammaF) at hF from (v0,gamma0) at h0. |

PAHohmn | Computes the phase angles for a Hohmann intercept |

PDrag | Dynamic pressure on a satellite based on an exponential atmospheric model. |

PToSMA | Compute the semi-major axis from an orbit period or mean motion. |

PatchedConicElements | Computes patched conic elements. |

PlanetaryAccelerations | Compute perturbations due to other planets aside from the center. |

PropEph | Propagates the ephemeris one step. |

PropagateTLE | Propagates the NORAD two line elements, ex. SGP, SGP4, SGP8. |

PropagateTLECommonTime | Propagates a set of NORAD two line elements with a common time frame. |

RVOrbGen | Generate an orbit by propagating Keplerian elements. |

RVSet2El | Batch form of RV2El. |

RandomOrbit | Monte-Carlo orbit simulation. |

SphOI | Computes the sphere of influence ratio |

SphOrb | Point mass orbit equations in equatorial spherical coordinates. |

SphereOfInfluenceHelio | Computes the ratio of the sphere of influence for interplanetary |

SunSyncInclination | Compute the sun-synchronous inclination for an orbit. |

SunSyncNode | Compute the ascending node for the desired local time. |

SynPer | Computes the synodic period between two orbits. |

SynodicFromSemimajorAxes | Computes the synodic period from semi-major axis. |

TARes | Resolves the transfer angle ambiguity. |

THohmn | Computes all times for a Hohmann Transfer. |

TTrnsHoh | Computes the Hohman transfer time between two orbits |

TWaitHoh | Computes the wait time at the target. |

Tfr2Imp | Two impulse optimal orbit transfer. |

Tfr3Imp | Three impulse orbit transfer. |

TimeOfFlightHyperbola | Time of flight in a hyperbola |

UGravity | Compute the earth's gravitational potential. |

VAtm | Atmospheric velocity from position and planetary rate. |

VEscape | Computes the escape velocity. |

VInf | Computes the asymptotic velocity for a hyperbola |

VarEqP | Computes the right hand side of the equinoctial variational equations. |

VarEqT | Computes the right hand side of the variational equations |

VarGausP | Computes the right hand side of the Gauss variational equations. |

VarGausT | Variational Keplerian equations with the acceleration in tangential coordinates. |

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FAero | The aero force model. This is a pure drag model. |

FAtmDensity | Atmospheric density model function that calls the Jacchia J70 model. |

FEngine | Computes the engine force vector in the ECI frame. |

FOrbHFOP | High fidelity orbit model designed to work with ode113. |

FPlantNoise | The plant noise model. |

FSolar | The solar force model for OrbitPropagator. |

PropagateOrbitPlugIn | Main GUI for propagating an orbit using ode113 and user-selected models. |

ReadTopexPOE | Reads a Topex Precision Orbit Ephemerides file. |

StoppingConditions | Stopping conditions for an orbit. |

StoppingPlugIn | Create a stopping conditions plug in for OrbitPropagator. |

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LowThrustSim | Simulate low thrust spacecraft. |

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 |

PropagateLowThrust | Propagate a low thrust trajectory assuming that the thrust is constant |

PropagateNBody | Propagate n-bodies in an n-body problem. |

RVOrbHF | High fidelity orbit simulation with drag and planetary perturbations. |

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DLinOrb | Computes the linearized orbit equations for a discrete system. |

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. |

FOrb | Computes the right-hand-side of the orbit equations about a mass point |

FOrbCartH | Computes the right-hand-side of a spherical harmonic orbit (Cartesian). |

FOrbHF | High fidelity orbit model right-hand-side. |

FOrbHF2 | High fidelity orbit model designed to work with ode113. |

FOrbLEOP | Orbit model for Launch and Early Orbit Operations. |

FOrbLEOPStopping | Its companion function is FOrbLEOP |

FOrbLTE | Orbit model for low thrust escapes. |

FOrbLowThrust | Right hand side of the planar orbit equations assuming constant thrust |

FSolarSail | Solar sail simulation right hand side. |

FVarEq | Computes the right hand side of the variational equations. |

LinOrb | Computes the linearized orbit equations. |

RHSGeoHarm | Computes the right hand side for a gravity model. |

RHSGeoJ2 | Computes the right hand side for Earth gravity with J2. |

RHSHelioWithPlanets | Right hand side for a heliocentric system with a thruster. |

RHSOrbit2D | Two dimensional orbit dynamics. |

RHSOrbitPlanetFixed | Cartesian orbital equations in a planet fixed (rotating) frame. |

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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 |

PropagateCRTBP | Propagate an arbitrary CRTBP with origin at the secondary body. |

PropagateCRTBPToPeriapse | Propagate the CRTBP initial state to the next perigee |

RHSCRTBP | Compute the RHS of the CRTBP equations of motion. |

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AttitudeFrames | Draw attitude frames. You can add these to any 3D picture. |

DrawOrbitPlane | Draw an orbit plane. You can add this to any 3D plot. |

EarthMoon | Plot an orbit track in the Earth/Moon System. |

EarthMoonRotFrame | Plot an orbit track in the Earth/Moon Rotating System. |

HALOPlot | Generate a plot of a HALO trajectory |

L2OrbitPlots | Simulate and plot an Earth orbit to L2 point low thrust transfer. |

OrbTrack | Plot a planet-fixed orbit track in 2D or 3D. |

OrbTrackECI3D | Plot an orbit track in the ECI frame. |

OrbView | View orbit related parameters on a quad chart. |

PlotEMTraj | Plot a trajectory in the Earth-Moon system |

PlotOrbitPage | Create a plot page with 2D and 3D views of an orbit. |

PlotOrbitTransfer | Plot the two initial orbits and the transfer orbit. |

PlotSEMTraj | Plot an orbit track in the Sun/Earth-Moon Rotating System. |

SeeTLE | View a set of satellite TLEs in Earth orbit, using TLEs from celestrak. |

SelectTLEGroup | A GUI to view / select from a list of TLE groups at www.celestrak.com. |

TrajectoryPlot | Draws a 2D or 3D trajectory plot. |

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SVN Revision: 42425

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