SC Module

Directory List

Actuator Attitude BasicOrbit
DemoFuns Demos/Actuator Demos/Attitude
Demos/CAD Demos/Disturbances Demos/Dynamics
Demos/Environs Demos/Ephemeris Demos/GOESRead
Demos/GUIPlugIn Demos/MagneticControl Demos/Sensor
Demos/SystemDesign Disturbances Dynamics
Environs Ephem GOESData
GOESRead GUIPlugIn Hardware
MagneticControl SCData SCDatabase
SCMat SCModels Sensor
SystemDesign Visualization


Actuator

Designs a blowdown system.
Size a battery given an orbit and planet.
BatterySize Battery sizing for a given orbit and array power.
Generates a blowdown curve.
Simple CMG model. Assumes a tach loop controls the CMG momentum.
Computes the effective pulsewidth given the rise and fall times.
Computes friction torques based on a model with an exponential term.
Friction model. This model uses a bristle state.
Rotary friction model using differentiable functions.
Computes the thrust and fuel consumed for thrusters.
Designs an air coil by minimizing a weighted combination of power and mass.
Performs a tradeoff of magnetic torquers versus thrusters.
Computes the moment arms for a set of thrusters.
Generate a pulsewidth modulated sequence given x.
Compute the propellant mass and pressurant mass for a tank.
A RWA model using FrictionSmooth.
A RWA model using FrictionBristle to model the friction.
Size a reaction wheel using maneuver requirements.
Smart RWA model. This models an RWA using Hall sensors.
Calculates RWA parameters from spec sheet parameters.
Compute the final mass from the rocket equation.
Model a stepping motor drive.
Cold gas thruster propulsion system
Generate unit vectors for a RWA pyramid.

Back To Top

Attitude

Add mass and mass derivatives using the mass data structure.
Computes the magnitude of the angular rate of the momentum vector
Arc efficiency from spin rate and pulsewidth.
Computes the transfer matrix from gimbal rates to torques.
Compute dual spin turn rates
Computes the dual spin stability.
Computes the damping coefficient ratio for a damper wheel.
Computes the unit normal for a double pivoted assembly.
Generate a target quaternion by limiting the total angular change.
Computes the new angular rate when the inertia changes.
Integrand for pointing budgets.
Extract flex modes from a finite element modal transformation matrix.
Generate gimbal commands for a gimbal stationkeeping system.
Convert 3x3 inertia matrix to [Ixx Iyy Izz Ixy Ixz Iyz].
Computes the new inertia and body rate when appendages change discretely.
Compute the libration frequency from inertia and orbit rate.
Reads in flex data from a formatted text file.
Computes a spin precession maneuver using a rhumb line precession.
Computes a pointing budget over n categories.
Calculates the time from pulse start to the centroid.
Compute the pulse pair delay for a Spin Precession Maneuver.
Right-hand-side for attitude dynamics with a permanent magent
Creates pointing budgets using a GUI.
Computes a pointing budget over n categories.
Rhumb line precession
Simulate a rhumb line precession.
Converts random walk measured over dT to standard deviation.
Generates open loop four channel magnitude plots for roll/yaw dynamics.
Computes the skew angle for a single dipole used to control yaw and roll.
Sum a set of torques produced by summing T = rxF
Take the cross product a matrix of vectors times a flex transformation matrix.

Back To Top

BasicOrbit

Transformation matrix from the perifocal frame to the inertial frame.
Converts eccentric anomaly to mean anomaly.
Computes the true anomaly from the eccentric or hyperbolic anomaly.
Converts orbital elements to r and v for an elliptic orbit.
Computes the right-hand-side of the orbit equations about a mass point.
Computes the eccentric anomaly
Approximate root to Kepler's Equation for elliptical and hyperbolic orbits.
Eccentric anomaly for an ellipse.
Eccentric anomaly for a hyperbola.
Computes the true anomaly from the mean anomaly.
Computes the true anomaly from the mean anomaly without wrapping.
Generate the true anomaly from the mean anomaly for a parabola.
Converts true anomaly to eccentric or hyperbolic anomaly.
Converts true anomaly to mean anomaly.
Computes the mean anomaly from the true anomaly without wrapping btwn -pi / pi
Compute the orbital rate from distance and semi-major axis.
Propagate an ECI state into the future with point mass orbit.
Compute the period for an orbit.
Compute the semi major axis from the period
Computes m, nu and E from r, a and e.
Right hand side for a simple orbit.
Computes the semimajor axis given position and velocity magnitudes.
Converts Cartesian state to Keplerian orbital elements.
Generate an orbit by propagating Keplerian elements.
Computes the orbital velocity.

Back To Top

DemoFuns

Returns the mass and right hand side of the dynamics equations.
Returns the mass and right hand side of the dynamics equations.
Sliding mass on a pendulum using independent coordinates
Single pendulum using independent coordinates
Dynamics of spacecraft with one reaction wheel.
Simulate a reaction wheel
RWA model
Roll/yaw simulation RHS
Roll/yaw simulation right hand sidd
Compute smooth friction RHS.
Right hand side of the two body equations.
Measurement equation for a roll/yaw controller.
Gather output from the hysteresis damping simulation
The constraint equations and Jacobians.
The constraint equations and Jacobians. The outputs are
The constraint equations and Jacobians.
Q2 transforms from A to B and Q1 transforms from B to C

Back To Top

Demos/Actuator

Demonstrate the bristle friction model with a velocity ramp.
Demonstrate the use of CMGs. Shows how to use a pseudo inverse to distribute torques.
Simulates a pivot rotation.
Test the reaction wheel model with bristle friction.
Demonstrate different RWA models.
Simulate a RWA with a PI rate controller.
Test the smart reaction wheel model.
Demonstrate the use of the smooth friction model

Back To Top

Demos/Attitude

Simple sim using a CAD model of the spacecraft to view the attitude.
Generates the surface properties needed by DSim for a simple CubeSat 3U.
Demonstrate a pointing budget using PBudget.
Tests a gimbaled thruster stationkeeping control system.
Displays different kinds of jitter.
Demonstrate LVLH angular rate for an eccentric orbit
Implements a thruster control system. Uses a CAD model of the spacecraft.
This script explores different roll/yaw controllers.
Implements a spacecraft control tutorial.
Study pulse resolution.
Space Shuttle attitude timeline

Back To Top

Demos/CAD

Build a 3U Cubesat using AddCubesatComponent
Design the Small Agile Satellite.
Create the Cassini CAD model from DXF data
Build up a model of a geosynchronous communications satellite.
Demonstrate CAD geometry (vectors and rotations) using cylinders.
Loads in dxf data for Cassini and Huygens, and saves data to mat-files.
Simple model with two thin plates.
Create a CAD model of the ISS
Generates a lunar module model.
Build a model of the Microwave Anisotropy Probe.
Make a detailed demonstration nano-spacecraft with two solar arrays.
Creates a model for the thermal demo.
A very simple spacecraft with thrusters and one sensor.
A very simple spacecraft with one sensor.
Build a solar sail model using BuildCADModel.
Load a dxf file and save it as a subassembly.
Make a detailed demonstration spacecraft with two solar arrays.
A very simple 'XYZ' spacecraft with six panels and axes.
Demonstrate CADColor
Demonstrate CADColor using the Cassini orbiter.
Draws a picture of the Cassini orbiter, Huygens probe, Saturn, and Titan.
Generates a CubeSat model that is gravity gradient stabilized.
Simulate the space shuttle model.

Back To Top

Demos/Disturbances

Surface accommodation drag demo on a flat plate
Surface accommodation drag on a cylinder
Run the disturbance model for a spacecraft with two rotating arrays.
Disturbance analysis of two thin plates.
Demonstrate disturbance modeling with shadowing.
Surface accommodation drag on a sphere

Back To Top

Demos/Dynamics

Example 4.2 and 4.3 in the reference.
Demonstrates rigid body rotation.
Demonstrates nutation and generates an STK attitude file.
Six body simulation of a spacecraft with a robot arm.
Demonstrate two body dynamics using the two body dynamics model.
Three body simulation with initialization using the CAD tools.
Three body simulation. The bodies are connected
This script demonstrates the deployment of the wire from the spacecraft.

Back To Top

Demos/Environs

Demonstrate the J70 atmosphere model over a solar cycle.
Demonstrate the J70 atmosphere model.
Compare the magnetic field models.

Back To Top

Demos/Ephemeris

Animate the phasing of Earth and Mars over time.
Demonstrate simple orbit and attitude ephemeris analysis
Demonstrate JPL ephemeris for the solar system.
Demonstrate earth nutation, precession and rotation.
Computes eclipses.
Demonstrate the planets model.
Animate the terminator line through a year

Back To Top

Demos/GOESRead

Demonstrates the GOES Toolbox functions.

Back To Top

Demos/GUIPlugIn

UseREA.matCommand list to use thrusters
UseREAForDV.matCommand list to use thrusters for velocity change
UserREAForDV2.matCommand list to use thrusters for velocity change
Demonstrate command lists
Launch the GUI plug in demo. See the GUIPlugIn folder for the function.

Back To Top

Demos/MagneticControl

Demonstrate the magnetic controllers.
Simulate a momentum bias spacecraft with magnetic roll/yaw control.
Demonstrates magnetic control.
Demonstrates magnetic control and power profiles.
Simulate the attitude of a rigid spacecraft with permanent magnet in LEO

Back To Top

Demos/Sensor

Test the gyro model.
Simulate various single degree of freedom gyros.

Back To Top

Demos/SystemDesign

Run the disturbance model in GEO. Uses TwoArraySC.mat
Generate the Spacecraft Fuel Budget.
Create a mass budget from a CAD file (SCwRWA.mat).

Back To Top

Disturbances

Add a surface to the data structure.
Calculate the drag force in the ECI frame assuming constant area.
Compute the aerodynamic forces on a set of elemental areas.
Compute the total force and torque on a spacecraft generated by the CAD package.
Computes the aerodynamic force using surface accommodation coefficients.
Gravity gradient for a rigid body with small offsets from LVLH.
Computes a gravity gradient torque from r and mu.
Computes gravity gradient stiffness from inertia and orbit rate.
Returns optical surface properties for selected materials.
Save surface properties to the file
Compute the solar force on a set of elemental areas.
Computes a gravity gradient torque.
Computes residual dipole torques.
Computes an RF torque for a set of antenna.
Generates solar pressure torques with shadowing.

Back To Top

Dynamics

Attitude simulation of a rigid body.
Double integrator model.
AKM Burn right-hand-side
The right hand side of equations formulated using Lagrange multipliers
Gyrostat right-hand-side.
Computes the right hand side of the spacecraft with pivot eofm.
Rigid body right-hand-side.
Rigid body right-hand-side with magnetic torque computed internally.
Two body spacecraft model right-hand-side.
Plant for a momentum bias spacecraft with flexible solar arrays.
Gyrostat dynamics model which computes acceleration or plant matrices.
Reads in flex data from a formatted text file.
Momentum bias spacecraft model
See GetFlex for formatting data into the needed structure.
Computes the angular acceleration of a rigid body.
Spacecraft attitude and orbit dynamics with a disturbance function.
Rigid body dynamics with damping.
Model for a spacecraft with a roll pivot.
Model for a spacecraft with a single pivoted momentum wheel.
Models two rigid bodies attached by a 1 to 3-dof hinge.
Right hand side of the equations of motion for a topological tree.
Add a body to the tree data structure.
Computes the momentum for the topological tree dynamics.
Create the tree data structure
Plot the output of tree.
Print out the body information for the tree model.
Computes the angular acceleration of a body with time varying inertia.
The right hand side of the wire equations formulated using Lagrange multipliers
Models the deployment mechanism
Spacecraft with multiple wires
Magnitude of the angular momentum
Initialize the wire model data structures
Plot the wires. One wire is plotted on each page.

Back To Top

Environs

Computes the atmospheric density of Mars.
Computes the geocentric magnetic field based on a tilted dipole model.
Magnetic field based on the Mead-Fairfield Model.
Computes the heat absorbed per unit area due to albedo.
Compute the environment parameters for the Earth.
Computes the heat absorbed due to earth radiation.
Computes parameters for a geosynchronous orbit.
Computes the normalized sun intensity for an earth geosynchronous orbit.
Computes the Earth magnetic field using the DGRF/IGRF model.
Data for planet magnetic fields.
Computes the magnetic field using Schmidt normalized coefficients.
Computes the magnetic field of a dipole along the z axis.
Computes the magnetic field of a dipole along m.
Computes R given the molecular weight.
Compute the environment parameters for a selected planet.
Computes the atmospheric density for Earth, Mercury, Venus, Mars and Pluto.
Computes the albedo and radiation flux for planets.
Read in the magnetic field from a file.
Solar flux from the sun as a function of distance including sunspots
Computes the solar flux prediction based on Julian date.
Solar flux from the sun as a function of distance in AU.
Compute the sun beta angle from the sun vector and orbit.
Solar flux and direction from the sun with seasonal variation.
Titan density model.
Atmospheric velocity from position and planetary rate.
Properties of water.

Back To Top

Ephem

Transformation matrix from ecliptic to Earth equatorial planes.
Creates an SPK file from two text files.
Compute total change in longitude between two orbits.
Computes the transformation form ECI to ECIR.
Computes the matrix from mean of Aries 2000 to planet fixed frame.
Computes the equation of the equinoxes
The matrix that rotates from the Earth mean axes to the true axes.
Computes the earth precession matrix
Computes the Earth greenwich matrix that transforms from ECI to EF.
Determine jD for when the earth-fixed frame is aligned with the ECI frame.
Computes the mean earth rate.
Computes eclipses.
Computes eclipse orbit fraction.
Determines eclipses in heliocentric coordinates.
Returns the equatorial to Galactic transformation matrix.
RHS for computing solstice.
Compute Greenwich apparent sidereal time.
Compute Greenwich mean sidereal time from Julian date.
Calculate a ground track on an ellipsoid.
Converts hours, minutes and seconds into seconds
Interpolate a planet's state for a given Julian Date.
Computes the position of Lagrange points in normalized rotating
Reads in the FK5 catalog in MICA format.
Reads in the Clementine data.
Computes the angle needed to see over lunar terrain.
Draw a lunar profile given lambda and theta.
Computes a mean sidereal day
Computes a mean solar day.
Computes the matrix that transforms from ECI to areographic axes.
Computes the moon orbital elements with respect to the earth inertial frame.
Computes the matrix that transforms from ECI to selenographic axes.
Generate the moon vector in an earth or spacecraft centered frame.
Generate the moon vector in an earth or spacecraft centered frame.
Lists moons of a planet or planet center about which a moon orbits.
The changes in longitude and obliquity due to earth nutation.
Computes the mean obliquity of the ecliptic of date.
Calculate the parallax
Get positions for an array of planets using the JPL ephemeris.
The position vectors, gravitational parameters and velocity for the planets.
The position vectors, gravitational parameters and velocity for the planets.
Computes the mean planet rotation rates from their rotation periods.
Length of year of planets in terms of Earth years.
Finds the distance to the sun and the solar flux.
Simplified planet ephemerides from the almanac.
Creates a series of quaternions with its x axis spinning about u.
Compute the sun-nadir quaternion and other quantities.
Creates a sun reference frame with +x pointing at the sun.
Generate the moon position in the earth-centered inertial frame.
Generates a topographic map of the moon using spherical harmonics.
Generate the sun position in the earth-centered inertial frame.
Read a bsp file.
Converts seconds into hours, minutes and seconds
Computes the position vectors of the planets as a function of time.
Computes the position vectors of the planets as a function of time.
Computes the solar system elements on a given Julian Date.
Look up a moon or planet and return its properties.
Compute the solar intensity experienced by a spacecraft.
Sort FK5 by distance in light years and save in a new file
Draws a star map.
Compute the sun-nadir angles and yaw rate.
Generate the sun vector in the earth-centered inertial frame.
Moderate precision sun model.
Finds the sun vector any place in the solar system.
Compute the terminator line on the Earth that defines day/night.
Computes the position and velocity of stable Lagrange points.
Computes the matrix from mean of Aries 2000 to earth fixed frame.
Apparent sun vector from quantities tabulated in the astronomical almanac.
Create a bsp file

Back To Top

GOESData

G0758910.BIN;1Example GOES data.
SATPOS.TXT;1Satellite positions.

Back To Top

GOESRead

Computes a sine/cosine harmonic series for the magnetic field.
Transforms the GOES data into popular earth pointing frames.
Ordering information for the GOES CD-ROM.
Draws the GOES Legend.
Computes the west longitude of a GOES spacecraft.
Removes glitches from data.
Loads GOES binary data. Will edit out magnetometer glitches.
Loads GOES magnetometer data. This can take a lot of data.
Loads in GOES Satellite Positions
Loads GOES data from multiple files.
Converts two's complement of length 2b to a floating point number.
Draws the Weather Legends.
Loads GOES binary data. Will edit out magnetometer glitches.

Back To Top

GUIPlugIn

Generate attitude profiles.
Create a command interface for a simulation.
Draw spacecraft in orbit about a planet. Includes a separate controls window.
Create an orbit elements GUI plug in.
This gui displays a counter.
Create an orbit display.
Parse a command string
Demonstrate using the GUI plug ins with an orbit simulation.
Create an spacecraft state GUI plug in.

Back To Top

Hardware

Convert floating point to word.
Computes the magnetic field for a filament or loop magnetic element.
Models a pivot mechanism and converts stepping motor steps to pivot angle.
Convert an integer word to a floating point number.

Back To Top

MagneticControl

Flux density from the magnetic field due to hysteresis.
Compute the magnetic field of a dipole
Computes the dipole for a solid magnet.
Dipole vector needed to produce a torque given the magnetic field over time.
Two axis magnetic control dipole
Models a magnetic torquer.
Right hand side for a dynamical model of magnetic hysteresis.
Simple MagneticTorquer model. Outputs the torque in body coordinates.
Right hand side for a dynamical model of magnetic hysteresis.
Torque from a hysteresis damper.
Torque rod model using tanh

Back To Top

SCData

030201AP_SK_SM546_T45.bspJPL Ephemerides binary support file
Apophis.objOBJ file of the Apophis asteroid.
AtmData.txtStandard atmosphere data field
AutoCADColors.txtGenerate colors for AUTOCAD.
BRIGHT.CATBright star catalog.
CLIPPER.dxfPan Am space clipper.
Clipper.cadCAD data that goes with CLIPPER
ComSat.txtText file with ComStar CAD data
Commands.txtCommands
ComstarSA.txtComstar solar array
EarthMoonTraj.matSaved Earth/Moon trajectory.
FK5.100FK5 catalog.
HUBBLE.dxfHubble space telescope.
NeptuneMagField.txtMagnetic field coefficients for Neptune.
PolylineTest.dxfPolyline file.
SolarFluxPredictions.txtASCII solar flux data for SolarFluxPredictions.txt
TFIGHTER.dxfTie like fighter.
USS_LA.dxfUS submarine.
X1.bspBSP file.
ascp2000.405.zipZip file with binary support package
bin2000.405JPL 405 ephemeris data for the planets, 2000 to 2040
cassini.dxfCassini CAD Model
gltm2b.topoTopographic data
lnxp1600p2200.405JPL ephemerides good through 2200
orion.obj.
probe.dxfHuygens CAD model.
sCTConstants.matConstant database.
sts.txtShuttle NORAD 2 line elements.
visual.txtVisible satellite NORAD 2 line elements
zvezda1.dxfZvezda module.
GUI to output the value of a constant for a spacecraft.

Back To Top

SCDatabase

GUI to output the value of a constant for a spacecraft.

Back To Top

SCMat

Ariel.matTexture map.
AttitudeProfileExampleData.matExample data for attitude profile
Callisto.matTexture map.
CassiniColor.matCassini model colored.
Charon.matTexture map.
DefaultSpacecraftDataFile.matSaved spacecraft component data.
Deimos.matTexture map.
Dione.matTexture map.
Earth.matLow-res Earth texture map with clouds.
EarthHR.matHigh resolution Earth texture map.
EarthMR.matMedium res Earth texture map without clouds.
ElementSet.matOrbital element set
Enceladus.matTexture map.
Europa.matTexture map.
FlexM00.matFlex model, array at 0 deg.
FlexM90.matFlex model, array at 90 deg.
GEMT1.matGEM-T1 gravity model.
Ganymede.matTexture map.
Huygens.matSpacecraft CAD model.
IGRF11.matIGRF magnetic field data, 2010.
IGRF95.matIGRF magnetic field data, 1995.
Iapetus.matTexture map.
Jupiter.matTexture map.
Kp_ap_Ap_SN_F107_since_1932.matSolar and magnetic index history
Mars.matTexture map.
Mercury.matTexture map.
Mimas.matTexture map.
Miranda.matTexture map.
Moon.matTexture map.
Neptune.matTexture map.
Oberon.matTexture map.
Phobos.matTexture map.
Pluto.matTexture map.
Proteus.matTexture map.
RCS.matThruster unit vectors and positions
RYC.matRoll/yaw control data.
Rhea.matTexture map.
SCHelp.matHelp file data
Saturn.matCreates the rings of Saturn.
SolarFluxPredictions.matSolar flux data for 2000-2040
SolarFluxPredictions2020.matSolar flux data for 2000-2020
Sun.matTexture map.
TelemetryData.matA telemetry page data sete
Tethys.matTexture map.
Titan.matTexture map.
TitanDensityData.matData for Titan atmosphere density.
Titania.matTexture map.
Triton.matTexture map.
Umbriel.matTexture map.
Uranus.matTexture map.
Venus.matTexture map.
planet.matPlanet file

Back To Top

SCModels

COMETS_Data.matComets spacecraft CAD data.
Cassini.matSpacecraft CAD components.
FlatPlate.matFlat plate CAD model.
FlatPlates.matTwo flat plates CAD model.
ISS.matInternational Space Station CAD model.
ISS2.objInternational Space Station Wavefront obj file.
NanoSatModel.matNanosat CAD model.
SCForImaging.matStored CAD model for thermal imaging demos.
SCwRWA.matCAD model with reaction wheels.
SatWThrusters.matModel for a simple satellite with thrusters.
ShuttleModel.matShuttle CAD model with rotating doors and arm.
SimpleSat.matSatellite CAD model of a simple cube.
TwoArraySC.matSpacecraft with two rotating arrays for system studies.
XYZSat.matSimple spacecraft with axes.

Back To Top

Sensor

Converts attitude increments to rate.
Converts the output from a conical scanning sensor to roll.
Simulate a counter.
Simulates an ideal earth sensor measuring roll and pitch.
Models a conical scanning earth sensor.
Compute the delta earth chord for a scanning earth sensor.
Energy per ring for a diffraction limited circular aperture
Converts focal plane coordinates into right ascension/declination of the targets.
Computes the output of focal plane sensors.
Gyro right-hand-side.
Models a gyro.
Typical gyro noise data.
Model a hemispherical resonating gyro. Includes all noise sources
Computes the hsa (horizon) sensor data for a spinning spacecraft.
Plots the HSA sensor data.
Normalized stellar-light detector integral given a star type and detector
Models accelerometers. This model includes quantization, noise and a bias.
Returns roll and pitch for a generic earth sensor.
Returns magnetic field measurement in Earth orbit.
Returns body rate information.
Model of a rate integrating gyro measurement.
Returns relative position information.
Returns the output of a star tracker.
Returns elements of a state vector as a measurement.
Returns analog sun sensor measurements.
Returns digital sun sensor measurements.
Computes nadir angle from a cant angle, earth angle and chordwidth
Models a generic 2 dimensional optical sensor.
Point spread function for a circular aperture
Propagates a quaternion based on updated angular increment measurements.
Converts right ascension and declination into focal plane coordinates.
Computes the output of a rate integrating gyro package.
RIG output.
Converts RWA tachometer count to rate.
Model a rate gyro. Includes all noise sources
Models a spacecraft clock.
Single degree of freedom mechanical gyros.
Simulates a single axis suns sensor
Power series model for the output of an analog sun sensor.
Computes the location in the focal plane of unit vectors.
Converts a unit vector into a pixel location.

Back To Top

SystemDesign

Sizes the battery and solar array
Create masses for a satellite.
Analyze the structure of a small agile satellite.

Back To Top

Visualization

Plot planets and a trajectory in the heliocentric frame.
Creates a figure with Earth texturemap, political boundaries, and lat/lon.
Add planet to the current axes.
Plot a 3D orbit around a planet in the ECI or planet fixed frame.
Plots one orbit and the sun vector looking down on the ECI Plane.

Back To Top

Back to API main page