
LibrationFrequency  Compute the libration frequency from inertia and orbit rate. 
CP2I  Transformation matrix from the perifocal frame to the inertial frame. 
E2M  Converts eccentric anomaly to mean anomaly. 
E2Nu  Computes the true anomaly from the eccentric or hyperbolic anomaly. 
El2RV  Converts orbital elements to r and v for an elliptic orbit. 
FOrbCart  Computes the righthandside of the orbit equations about a mass point. 
M2E  Generate the eccentric anomaly from the mean anomaly and the 
M2EApp  Approximate root to Kepler's Equation for elliptical and hyperbolic orbits. 
M2EEl  Eccentric anomaly for an ellipse. 
M2EHy  Eccentric anomaly for a hyperbola. 
M2Nu  Computes the true anomaly from the mean anomaly. 
M2NuPb  Generate the true anomaly from the mean anomaly for a parabola. 
Nu2E  Converts true anomaly to eccentric or hyperbolic anomaly. 
Nu2M  Converts true anomaly to mean anomaly. 
OrbRate  Compute the orbital rate from distance and semimajor axis. 
Period  Compute the period for any orbit. 
RV2El  Converts Cartesian state to Keplerian orbital elements. 
RVFromKepler  Generate an orbit by propagating Keplerian elements. 
VOrbit  Computes the orbital velocity. 
HysteresisOutput  Gather output from the hysteresis damping simulation 
FGravityGradientStiffness  Gravity gradient for a rigid body with small offsets from LVLH. 
GravityGradientFromR  Computes a gravity gradient torque from r and mu. 
OpticalSurfaceProperties  Returns optical surface properties for selected materials. 
SolarF  Compute the solar force on a set of elemental areas. 
FRB  Rigid body righthandside. 
RBModel  Computes the angular acceleration of a rigid body. 
RHSRigidBodyWithDamping  Rigid body dynamics with damping. 
BDipole  Computes the geocentric magnetic field based on a tilted dipole model. 
SolarFluxPrediction  Computes the solar flux prediction based on Julian date. 
CEcl2Eq  Transformation matrix from ecliptic to Earth equatorial planes. 
ECIToPlanet  Computes the matrix from mean of Aries 2000 to planet fixed frame. 
EarthRte  Computes the mean earth rate. 
Eclipse  Computes eclipses. 
GMSTime  Compute Greenwich mean sidereal time from Julian date. 
MSidDay  Computes a mean sidereal day 
MoonRot  Computes the matrix that transforms from ECI to selenographic axes. 
MoonV1  Generate the moon vector in an earth or spacecraft centered frame. 
Moons  Lists moons of a planet or planet center about which a moon orbits. 
NutDelta  The changes in longitude and obliquity due to earth nutation. 
Planets  Simplified planet ephemerides from the almanac. 
SolarSys  Computes the position vectors of the planets as a function of time. 
SunV1  Generate the sun vector in the earthcentered inertial frame. 
SunVectorECI  Finds the sun vector any place in the solar system. 
TerminatorLine  Compute the terminator line on the Earth that defines day/night. 
BFromHHysteresis  Flux density from the magnetic field due to hysteresis. 
MagneticHysteresis  Right hand side for a dynamical model of magnetic hysteresis. 
RHSHysteresisDamper  Right hand side for a dynamical model of magnetic hysteresis. 
TorqueHysteresisDamper  Torque from a hysteresis damper. 
LoadEarthMap  Creates a figure with Earth texturemap, political boundaries, and lat/lon. 
PlotPlanet  Add planet to the current axes. 
PltOrbit  Plots one orbit and the sun vector looking down on the ECI Plane. 
SVN Revision: 42425
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