Missions Functions

Missions Module

Directory List

AlphaCentauri AsteroidProspector Comsat
Demos/AlphaCentauri Demos/AsteroidProspector Demos/Comsat
Demos/FastReorientation Demos/LunarLanding Demos/LunarMission
Demos/MarsOrbiter Demos/Pluto Demos/SunNadir
FastReorientation LunarLanding LunarMission
MarsOrbiter SunNadir


AlphaCentauri

Model of the Alpha-Centauri system.
Simple dynamical model for a flight to Alpha-Centauri.

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AsteroidProspector

Apply Gauss Variation Equations to determine in-plane thrust direction.
Compute delta-v assuming full thrust applied during all transfer times.
Right-hand side for low thrust GVE simulation.
Stopping event function for low thrust GVE sim using ode solver.
Simulation of low thrust maneuver to rendezvous with target orbit.
Compute the time to transfer each element from initial to target value.

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Comsat

Generates the data needed to compute the AKM firing.
Generates the data needed for a attitude data collection in TrnsfOrb.m
The ComStar satellite properties database GUI.
Simulate a dual-spin-turn.
Generates the data needed for a dual spin turn in TrnsfOrb.m
Generates the data needed for a delta Vs in TrnsfOrb.m
Updates the fuel mass.
Gets HSA attitude data
Computes the half system moment arms
Generates the data needed for an injection in TrnsfOrb.m
Generates the data needed for initialization in TrnsfOrb.m
Count the number of odd and even numbered thrusters in use.
Updates orbital elements based on an impulsive delta-V
Kalman Filter for pitch
Design the Pitch Loop including a tach loop for the wheel.
Computes the REA and tank pressure
Computes the thrust and fuel consumed for thrusters.
Designs the dual-spin-turn roll estimator
Generates the data needed to compute stationkeeping maneuvers
Computes spin precession maneuver data for fuel budgets
Generates the data needed for an SPM maneuver in TrnsfOrb.m
Performs a spin precession maneuver.
Find the surfaces that are in shadow.
Simulates a spin change.
Computes spin precession maneuver data for fuel budgets
Generates the data needed for a spin change in TrnsfOrb.m
Estimates rate from measurements of period
Computes the thrust level of a set of thrusters.
Computes the thruster torques based on an exponential rise
Simulates transfer orbit

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Demos/AlphaCentauri

Analysis of approach orbits to Alpha Centauri binary system
Simulate a mission to Alpha-Centauri.
Draw the Earth-relative geometry of the Alpha-Centauri binary star system
Alpha-Centauri mission
Create an optical link budget for an Alpha-Centauri mission.

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Demos/AsteroidProspector

Asteroid Prospector Mars mission planning.
Asteroid Prospector Simulation
Analyze the thruster layout for the Asteroid Prospector spacecraft
Simulate proximity operations around an asteroid.
Build the CAD model of the Asteroid Prospector spacecraft.
Design a mission to visit an asteroid with a small satellite

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Demos/Comsat

Simulate the AKM firing for the ComStar spacecraft.
The acquisition sequence for the ComStar satellite.
Generates the mass properties for the ComStar demo satellite.
Simulate the ComStar dual spin turn.
Computes the total disturbance torque for the ComStar satellite.
Designs earth sensor noise filters for the ComStar satellite.
Demonstrate a pointing budget for a typical satellite.
Design a PD controller for pitch for the ComStar satellite.
Tests the MWA pitch loop for the ComStar satellite.
Design and test the low frequency roll/yaw control system.
Design and test the nutation compensator.
Compensate the flexible solar array on the ComStar Spacecraft.
Simulate a spin precession maneuver for ComStar.
Demonstrate the automatic spin up for ComStar.
Simulates transfer orbit for ComStar.
Analyze the flexible solar array on the ComStar Spacecraft.
Design a roll/yaw controller using a double pivot

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Demos/FastReorientation

Simulate the fast reorientation system.
Simulate the fast reorientation system and demonstrate quaternion propagation

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Demos/LunarLanding

Demonstrate lunar lander guidance
Least Squares Optimization
Test fmincon against an analytical solution for the linear tangent law
Test fmincon against an analytical solution for the linear tangent law

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Demos/LunarMission

Generate lunar lander CAD model
Analyze the thruster layout for the lunar lander
Lunar mission planning
Lunar transfer simulation
Lunar polar mission planning
A lunar visibility analysis

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Demos/MarsOrbiter

Spacecraft simulation around Mars with Phobos and Deimos

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Demos/Pluto

Direct Fusion Drive (DFD) Pluto Orbiter
Pluto mission beamed power
Pluto mission using DFD
3D lander simulation.
Pluto lander model
Pluto mission using DFD

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Demos/SunNadir

Implements and simulates Sun nadir pointing control.

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FastReorientation

Executes the fast reorientation system slew maneuver.
Plans the fast reorientation system slew maneuver.
Propagates the target profile for the fast reorientation slew maneuver.
Compute the target quaternion for the fast reorientation system.
Calculates the torque for the fast reorientation system slew maneuver.

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LunarLanding

YALMIP constraint function.
Computes the fuel mass to achieve the desired acceleration vector.
Equality constraints for the landing for a 2D flat planet problem.
Equality constraints for the landing for a 2D flat planet problem.
Cost for the landing for a 2D flat planet problem.
Cost for the landing for a 3D planet problem.
Lunar landing target state
YALMIP objective function.
Generate the orbit state matrices
Compare the state transition matrix to numerical integration
Propagate the 2D state for the landing problem.
Propagate the 3D state for the landing problem.
Cartesian orbital equations in a planet fixed (rotating) frame.
This function computes the matrices a and b for dx/dt = a*x + b*u .
Implements a 2nd order guidance law
Simulate the 2D landing problem and generate plots.
Simulate a 3D landing and generate plots.

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LunarMission

Computes Apollo guidance coordinates
Apollo lunar module landing guidance
Generates an Apollo lunar landing trajectory.
Processes command lists.
Returns thrust and exhaust velocity for a rocket engine.
Landing energy
Generates a CAD component for a lunar module first stage legs.
Implements a lunar mission control system.
Computes parameters for a lunar orbit insertion.
Generate transfer orbit elements for a lunar mission.
Computes visibility of a satellite in lunar orbit.
Generate vertices and faces for a planet patch with terrain.
Plot a 3D orbit around the moon.
Right hand side for translational motion in the planet fixed frame.
Fourth order Runge-Kutta.

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MarsOrbiter

Right hand side for a Mars orbit simulation.

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SunNadir

Control demand distribution
Transform core frame to solar array frame
Transform sun vector from I frame to body frame
Initial quaternion and solar array angle given the sun geometry.
Spacecraft sun-nadir RHS with 4 RWA's and 2 solar arrays.
Transform a vector from the sun sensor frame to the core frame
Creates a small angle transformation matrix.
Sun sensor attitude determination for sun-nadir pointing.
Models the output for array mounted analog sun sensors.
Compute the sun beta angle from the sun vector and orbit.
Compute the orbit right ascension angle

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SVN Revision: 42425


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