SCPro Functions

SCPro Module

Directory List

Demos/Landers Demos/ProActuators Demos/ProAttitude
Demos/ProControl Demos/ProEnvirons Demos/ProEphemeris
Demos/ProMisc Demos/ProMissions Demos/ProSensors
DynamicalModels Landers MannedVehicle
ProActuators ProAttitude ProControl
ProEnvirons ProEphemeris ProSensors
ProTools Systems


Demos/Landers

Landing demo using bilinear tangent thrust programming.
3D lander simulation.
Lunar takeoff demo using bilinear tangent thrust programming.
Takeoff demo using bilinear tangent thrust programming.

Back To Top

Demos/ProActuators

Brushless DC motor simulation.
Design and draw an air core magnetic torquer
Compare friction models
Implements and simulates a spacecraft with 3 orthogonal reaction wheels.

Back To Top

Demos/ProAttitude

Demonstrate the AttitudeProfileWithCon function.
Comparison of CubeSat and SCT Disturbance models
3-axis spacecraft with an IMU simulation

Back To Top

Demos/ProControl

Point at an earth target and spin about the pointing vector.
Implements and simulates the MAP normal mode control.
An attitude and orbit simulation with reaction wheels.
Demonstrate a spacecraft in orbit pointing at a target on the Earth
Controls the momentum in a spacecraft using solar pressure.
An attitude and orbit simulation with reaction wheels.
Simulate a momentum bias spacecraft with a telescope on a roll pivot
Implements and simulates a spacecraft with reaction wheels and thrusters.
Demonstrate vector tracking using PID3Axis.

Back To Top

Demos/ProEnvirons

Europa atmospheric density and Jupiter magnetic field near Europa.
Solar flux variation over Earth orbit.

Back To Top

Demos/ProEphemeris

Dawn-Dusk SSO eclipse calculations

Back To Top

Demos/ProMisc

Compute program costs

Back To Top

Demos/ProMissions

Direct Fusion Drive (DFD) Mars Mission using an Orion capsule.
Direct Fusion Drive-powered space station design.
Design the Europa Clipper mission using a nuclear fusion engine.

Back To Top

Demos/ProSensors

Demonstrate GPS navigation message model.
GPS time dilation.
Demonstrate camera pointing. The default 10 deg FOV camera is used.
Displays navigation observables for two NASA missions.
Compute the L3 lens position in a Cooke Triplet.

Back To Top

DynamicalModels

Computes the constraint forces and torques.
Analytical eigenvalues for gravity gradient stabilization.
Compute the eigenvalues for a gravity gradient stabilized spacecraft.
Computes the normalized linearized orbit state equations.
Right hand side for a n bodies attached to a central hub.
Computes the time derivative of n spacecraft.
Right-hand-side for a 2 dimensional planet takeoff.
Spacecraft orbit dynamics with time-varying mass.
Right-hand-side of spacecraft dynamical equations with reaction wheels.
Right-hand-side of the spacecraft dynamical equations.
Right-hand-side of the dynamical equations with three ReactionWheels.
6 DOF spacecraft dynamics with a double integrator position model.
Linearized attitude dynamics for a rigid body.
Spacecraft attitude and orbit dynamics with time-varying mass.
Right hand side of a rigid body with offset CM
Right-hand-side of spacecraft dynamical equations with a second spacecraft.
Right-hand-side for a spacecraft with an IMU
Computes the right hand side for a spacecraft with reaction wheels.
Right hand side for a three body system.
Simulate separation of multiple satellites from a carrier.
Computes disturbances for ThreeAxisControl.m

Back To Top

Landers

Bilinear tangent law for maximizing altitude on launch.
Bilinear tangent law for orbit insertion or landing.
Bilinear tangent law in vector form for orbit insertion or landing.
Computes the optimal acceleration for a fuel/time problem.
Landing controller.
Implements a bilinear tangent landing controller.
Gravity turn landing controller.
Landing force in the body frame.

Back To Top

MannedVehicle

Sizes an Environmental Control and Life Support subsystem (ECLSS).

Back To Top

ProActuators

Design a minimum mass air core magnetic torquer.
Brushless DC Motor back emf.
Brushless DC Motor friction
Brushless DC Motor commutation using a 6 switch inverter.
Brushless DC Motor simulation
Design a minimum mass magnetic torquer.
Compute the moment for a magnetic torquer.
Create hysteresis plots.
Computes dynamics with friction for two different models.
RWA with power and heat.
RWA model. This models an RWA using Hall sensors.
Computes the friction for a reaction wheel.
Reaction wheel strength and momentum.
Simulates a two phase stepper motor.
Computes forces and torques for RWAs and thrusters using off-pulsing.
Compute the wheel speeds for a set of reaction wheels.

Back To Top

ProAttitude

Compute a trajectory to avoid stayout zones using AStar
Make time history plots of an attitude profile. See AttitudeProfileWithCon.m
Visualize an attitude profile with constraints.
Build a constrained attitude profile consisting of multiple overlapping modes.
Generate a reference quaternion for a variety of targets.
Generate a ground track error budget.
Maneuver cost on a sphere
Rotate about a body axis to align a body vector with an inertial vector
Calculate the alignment quaternion while applying constraints

Back To Top

ProControl

A PID Based 3 axis controller for rigid body.
Computes forces and torques for a set a thrusters using off-pulsing.

Back To Top

ProEnvirons

Creates an albedo map from a texture map.
Computes Neptune's atmospheric density using scale heights.
Computes the atmospheric density using Jacchia's 1970 model or scale heights.
Computes the atmospheric density using scale heights above 80 km.
Computes Jupiter's magnetic field based on a tilted dipole model.
Computes the aerodynamic disturbance using a Newtonian model.
Computes the albedo disturbance
Computes the radiation disturbance from the central body.
Computes the albedo disturbance.
Computes albedo from a texture map.
Generates a local star map. Epoch is J2000.
Compute the atm. density (kg/m^3) on Neptune given the altitude (km)
Computes the Newtonian force in ECI coordinates.
Computes the flux from a flat plate.
Create a star texture for use in other programs.
Computes the terminator circle on a planet.

Back To Top

ProEphemeris

Asteroid properties.
Compute the eclipse duration in earth orbit.
Low precision orbits of the four major Galilean satellites.

Back To Top

ProSensors

Computes the diameter of the Airy Disk.
Computes the area of intersection of a rectangle and a circle.
Compute the parameters necessary to place a camera at a target.
Get default camera properties for different camera models.
Generates the 2D coordinates in the focal plane for a camera.
Resolution of an optical sensor.
Generate a camera transformation.
Compute centroid noise terms for an optical sensor.
Position and velocity of a GPS satellite in the earth-fixed reference frame.
GPS receiver model. Models the GPS constellation.
GPS receiver model with navigation message model.
Gives the location of the GPS satellites at JD.
Gravitational time dilation.
Instantaneous field of view of an optical sensor.
Inertial measurement unit model.
Camera illumination model.
Computes the pixel map intensity.
Computes optical navigation observables.
Navigation measurement model.
Compute the MATLAB camera pointing parameters from the camera model.
Gravitational and velocity clock drift.
Computes range and range rate measurements.
Gives the spectrum for radiation using conventional names.
Computes the stellar irradiance.
= 299793.458;
Velocity time dilation.

Back To Top

ProTools

Compute a unit vector given alpha and beta angles.
Computes the altitude over a spherical harmonic terrain map.
Create a VisualCommander disturbance file from a cad model.
Draw field lines on a sphere.
Compute the glide slope angle.
Generates data for the NRL SolarCon solar array.
Size an airship to operate with neutral buoyancy on Neptune.
Generate vertices and faces for a planet with terrain.
Compute a slew to a target.
Creates a segmented unit sphere Wavefront obj and mtl files.

Back To Top

Systems

Add a multi-element arm to a CAD models.
Mass of JHU APL satellites.
Create masses for a satellite.

Back To Top

SVN Revision: 42425


Back to API main page