SC Module |
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Directory List
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Actuator
| FrictionSmooth | Rotary friction model using differentiable functions. |
| RWA | A RWA model using FrictionSmooth. |
| SingleAxisDrive | Model a stepping motor drive. |
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Attitude
| LibrationFrequency | Compute the libration frequency from inertia and orbit rate. |
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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 | Computes the eccentric anomaly |
| 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 an orbit. |
| RV2El | Converts Cartesian state to Keplerian orbital elements. |
| RVFromKepler | Generate an orbit by propagating Keplerian elements. |
| VOrbit | Computes the orbital velocity. |
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DemoFuns
| HysteresisOutput | Gather output from the hysteresis damping simulation |
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Disturbances
| 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. |
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Dynamics
| FRB | Rigid body right-hand-side. |
| RBModel | Computes the angular acceleration of a rigid body. |
| RHSRigidBodyWithDamping | Rigid body dynamics with damping. |
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Environs
| BDipole | Computes the geocentric magnetic field based on a tilted dipole model. |
| SolarFluxPrediction | Computes the solar flux prediction based on Julian date. |
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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. |
| InterpolateState | Interpolate a planet's state for a given Julian Date. |
| MSidDay | Computes a mean sidereal day |
| MoonEl | Computes the moon orbital elements with respect to the earth inertial frame. |
| 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. |
| PlanetPosJPL | Get positions for an array of planets using the JPL ephemeris. |
| 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. |
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Hardware
| FloatToWord | Convert floating point to word. |
| WordToFloat | Convert an integer word to a floating point number. |
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MagneticControl
| BFromHHysteresis | Flux density from the magnetic field due to hysteresis. |
| MagneticHysteresis | Right hand side for a dynamical model of magnetic hysteresis. |
| MagneticTorquer | Simple MagneticTorquer model. Outputs the torque in body coordinates. |
| RHSHysteresisDamper | Right hand side for a dynamical model of magnetic hysteresis. |
| TorqueHysteresisDamper | Torque from a hysteresis damper. |
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SCData
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SCMat
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SCModels
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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. |
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