SC Functions

SC Module

Directory List

Attitude BasicOrbit DemoFuns
Disturbances Dynamics Environs
Ephem MagneticControl SCData
SCMat Visualization

Attitude

LibrationFrequency Compute the libration frequency from inertia and orbit rate.

Back To Top

BasicOrbit

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 right-hand-side 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 semi-major 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.

Back To Top

DemoFuns

HysteresisOutput Gather output from the hysteresis damping simulation

Back To Top

Disturbances

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.

Back To Top

Dynamics

FRB Rigid body right-hand-side.
RBModel Computes the angular acceleration of a rigid body.
RHSRigidBodyWithDamping Rigid body dynamics with damping.

Back To Top

Environs

BDipole Computes the geocentric magnetic field based on a tilted dipole model.
SolarFluxPrediction Computes the solar flux prediction based on Julian date.

Back To Top

Ephem

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 earth-centered 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.

Back To Top

MagneticControl

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.

Back To Top

SCData


Back To Top

SCMat


Back To Top

Visualization

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.

Back To Top

SVN Revision: 42425

Back to API main page