Glideslope, GravityModels, OrbitCoord, OrbitData, OrbitManeuver, OrbitMechanics, OrbitPropagator, Vehicle, Visualization, Demos/OrbitManeuver, Demos/OrbitMechanics, Demos/OrbitPropagator, Demos/Visualization,
CWSimAndPlot - Visualize a set of maneuvers propagated with Clohessy-Wiltshire equations.
ClohessyWiltshire - A special formulation of the Clohessy-Wiltshire equations.
DVGlideslope - Calculate delta-Vs for glideslope rendezvous.
Glideslope - Guidance trajectory where range rate is proportional to range.
GlideslopeCircumnav - Calculate delta-Vs for a pulsed circumnavigation.
GlideslopePlanner - Calculate sequential glideslope maneuvers for planning purposes.
SolveT - Function to pass to NewtRaph for solving for the period of a glideslope
SolveTD - Derivative function to pass to NewtRaph for solving the period of a glideslope
EarthGravityModel.mat - Earth gravity model in a mat file.
GEMT1.geo - GEMT1 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.
LunarGravityModel.mat - Gravity model based on Lunar Prospector
ProcessLunarGravityModel - Process the lunar gravity model.
WGS84.geo - WGS84 gravity model.
A2Apogee - Computes the apogee radius from a and e.
A2Perige - Computes the perigee radius from a.
AB2RADec - Converts angles in the orbit plane 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.
Alfriend2El - Convert an Alfriend orbital element set into the standard orbital element set
CEq2C - Transformation matrix from equinoctial to cartesian coordinates.
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
CylOrb2Cart - Convert a cylindrical orbit state to a cartesian orbit.
E2RAORP - Ratio of apogee radius to perigee radius given eccentricity for an ellipse
ECEFToECI - Compute the transformation matrix that rotates ECEF to ECI coordinates.
ECEFToLLA - Compute latitude, longitude, altitude from ECEF position.
ECI2OrbitPlane - This function takes a position vector and orbit normal vector in ECI
ECIToRLP - Generates the transformation matrix from ECI to Rotating Libration Point
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.
InitialOrientation - Compute the initial quaternion and body rates for a circular orbit,
K2L - Converts eccentric longitude to true longitude
L2K - Converts eccentric longitude to true longitude
LLAToECEF - Compute latitude, longitude, altitude from ECEF position.
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.
OrbNEl - Conmputes the orbit normal from orbital elements.
OrbNEq - Computes the orbit normal from equinoctial elements.
OrbitalPlane - Display the orbital plane with the Earth.
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
REl - Computes the orbit radius and the parameter from Keplerian elements.
REq - Computes the orbit radius and the parameter from equinoctial elements.
RLagrange - Computes a collinear Lagrange point. Default is for the earth/moon
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
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.
SLR - Computes the semi-latus rectum.
VPQ - Computes the orbit velocity in the perifocal plane.
VR2AE - Computes sma and eccentricity given v and r.
LEOData.mat - Sample LEO orbit data.
MirNORAD - Comment.
mir.txt - Mir NORAD elements.
sdp.txt - SDP NORAD 2 line elements test data
sgp.txt - SGP NORAD 2 line elements test data
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 per year 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.
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
FOrbLTE - Orbit model for low thrust escapes.
FSolarSail - Solar sail simulation right hand side.
HohmannTransferRendezvous - Compute delta-Vs for rendezvous using Hohmann transfers.
LQOrbitController - Creates a linear quadratic relative orbit controller. Assumes full state
LTSpiral - Low thrust delta v between two circular orbits.
LTVCon - Solve the Linear Terminal Velocity Constraint problem.
LowThrustControl - Low thrust control.
LowThrustEscape - Compute the delta-V required for a low thrust escape.
LowThrustSim - Simulate low thrust spacecraft.
ManeuverEnvelope - Compute the maneuver envelope for a spacecraft rotating around another.
NORADToEl - Convert NORAD to Keplerian elements.
OrbMnvrBielliptic - Delta-V for a bielliptic orbit maneuver between circular orbits.
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.
OrbMnvrLongAndIncl - Delta-V for an longitude and inclination change maneuver for a circular orbit.
OrbMnvrLongitude - Computes the delta-V for an longitude only maneuver for a circular orbit.
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.
OrbitManeuverPlanner - Plan a maneuver using the Maneuver Planner GUI.
RendezvousPlanner - Compute delta-Vs for rendezvous. The inputs are
TransferAndPhaseAngle - Computes the transfer and phase angle given transfer time.
TransferTimeToDV - Converts the transfer time to delta-V for a rendezvous.
TriangularManeuver - Compute maneuver profile for a triangular maneuver.
VDA - Computes the heliocentric departure vector for a spacecraft.
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.
CylOrb - Right-hand-side of the cylindrical orbit equations about a mass point.
DriftRate - Drift rate in orbit elements from Earth oblateness.
Energy - Compute the energy for any orbit
FBudget - Computes a fuel budget. You need only fill in the data structure with
FEarthMoon - Gravity acceleration in the earth moon system
FEarthMoonSun - Orbit dynamics with spherical harmonic models of the Earth and Moon gravity.
FLambert - Right hand side for locally optimizing the Lambert time of flight problem.
FOrb - Computes the right-hand-side of the orbit equations about a mass point
FOrbHF - High fidelity orbit model right-hand-side.
FOrbHF2 - High fidelity orbit model designed to work with ode113.
FOrbLowThrust - Right hand side of the planar orbit equations assuming constant thrust
FVarEq - Computes the right hand side of the variational equations.
FlightPathAngle - Compute the flight path angle for a Cartesian state.
Flyby - Calculates orbital elements and perigee radius for a planetary flyby
FlybyHyperbola - Compute the required orbital elements for a flyby
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.
J2OrbitEffects - Compute J2 effects on the orbital elements.
J2Prop - Propagate an ECI state into the future with the J2 perturbation.
LambertOpt - Use Lambert with Nelder-Meade simplex optimization of start and transfer time
LambertTOF - Solves the Lambert time of flight problem using Battin's method.
LinOrb - Computes the linearized orbit equations.
LonMot - Computes the longitudinal motion due to an acceleration a
MeanAnom - Computes the mean anomaly
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.
NuInf - Computes the asymptote angle for a hyperbola. If e is < 1 it substitutes 1.
OblEff - Ascending node and perigee rates due to oblateness effects
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.
OrbRate - Compute the orbital rate from distance and semi-major axis.
OrbitJacobian - Computes the Jacobian for a spherical planet gravity model.
PAHohmn - Computes the phase angles for a Hohmann intercept
PDrag - Dynamic pressure on a satellite based on an exponential atmospheric model.
PlanetaryAccelerations - Compute perturbations due to other planets aside from the center.
PropEph - Propagates the ephemeris one step.
PropagateLowThrust - Propagate a low thrust trajectory assuming that the thrust is constant
RVOrbGen - Generate an orbit by propagating Keplerian elements. If t is not
RVOrbHF - High fidelity orbit simulation with drag and planetary perturbations.
SphOI - Computes the ratio of the sphere of influence to the distance
SphOrb - Point mass orbit equations in equatorial spherical coordinates.
SphereOfInfluenceHelio - Computes the ratio of the sphere of influence for interplanetary
SynPer - Computes the synodic period between two orbits.
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.
TrxCntrl - Plans delta-v maneuvers to correct triaxial motion.
UGravity - Compute the earth's gravitational potential. r must be a scalar
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.
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 - Propagate an orbit.
ReadTopexPOE - Reads a Topex Precision Orbit Ephemerides file.
StoppingConditions - Stopping conditions for an orbit.
StoppingPlugIn - Create a stopping conditions plug in for OrbitPropagator.
DXDM - Change in position for a rocket with time varying mass.
EarthMoon - Plot an orbit track in the Earth/Moon System.
OrbTrack - Plot an orbit track.
OrbView - View orbit related parameters on a quad chart.
ComStarAKMDV - Plan the AKM burn by looking at the AKM thrust variations as a function
DragCompensationDemo - Demonstrates drag compensation maneuvers.
GEOStationKeeping - GEO Stationkeeping Example
InsertionDeltaV - Computes the insertion delta-V for a Hohmann transfer.
LowThrustEscapeSim - Simulates a low thrust escape from an earth orbit.
LowThrustHelicocentricSim - Perform a helicocentric simulation from one circular orbit to another.
LowThrustMarsMission - Compute the delta-V for a low thrust mission to Mars synchronous orbit.
LowThrustMarsOptimalTransfer - Perform an optimal transfer from earth to mars orbits.
MarsOptimalTransfer - Perform an optimal transfer from earth to mars orbits.
OrbMnvrDemo - Runs demonstrations of selected orbit maneuver functions.
SolarSailSim - Orbit simulation of a solar sail.
TargetDemo - Demonstrates the Lambert targeting function DVTarget.
TwoStageDesign - Computes a preliminary design of a two stage to orbit vehicle.
ComStarFBudget - Demonstrate a fuel budget for the ComStar satellite.
EarthMoonSunSim - Simulate a spacecraft in orbit near the earth and moon.
InterstellarSim - Interstellar mission simulation with a sun gravity assist.
LinOrbitDemo - Linear orbit simulation. This compares nonlinear with linear.
LunarOrbitSim - Simulate an orbit about the moon. Show the visibility sun, earth, moon.
RelativeOrbitControl - Simulates two orbits and applies a relative controller.
RelativeOrbitSim - Simulates two orbits and plots their relative positions.
TDV - Demonstrate the various orbit change functions.
TDVDisp - Compute delta-v dispersions given declination and velocity errors.
TNORAD - Demo two of the five NORAD element propagators.
TOrbit - Investigate orbit coordinate systems.
TVarEq - Simulate an orbit using the variational equations.
TwoOrbSim - Simulates two orbits and plots their relative positions
DragDemo - Demonstrate drag reentry.
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.
MarsOrb - Comment.
OrbViewDemo - Comment.
RelMotionVis - Comment.
SVN Revision: 10554
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