## FormationFlying Module |

AnalyzeVariableTimeDV | Plot the behavior of the first and third delta-v in a 3-burn sequence |

CheckDeltaVs | Plot the trajectory that will result from a planned maneuver. |

CompareHills | Compare closed form Hills equations with other methods of propagation. |

DFFSim | Simulation routine for testing DFF guidance and control laws. |

DeltaVAnalysis | Compute the total delta-v assoc. w/ several types of reconfigurations. |

DriftRateSigma | Find the standard deviation of along-track drift per orbit due to rel nav errors. |

FFEccFrameCompare | Compare two methods of computing the relative motion in an eccentric orbit. |

FFMaintenancePlotter | Plot the results from "FFMaintenanceSim". |

FFMaintenanceSim | Formation flying maintenance simulation. |

FFMaintenanceTests | Returns data associated with various test runs for "FFMaintenanceSim". |

FindDriftTerm | Find the "deadband over drift rate sigma" term that results in the specified |

LPvsCF | Compare the delta-v and trajectory for two methods of relative orbit control. |

RelativeVelocityError | Compute max. navigation error that maintains the specified performance. |

TestFFEccLinOrb | Test the FFEccLinOrb function. An initial reference state in the ECI frame |

TestLPCircular | Test the LPEccentric function. Provide the reference orbital elements, an |

TestLPEccentric | Test the LPEccentric function. |

TestLPEccentricGVE | Test the LPEccentricGVE function. |

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CoarseProb | Coarse probability estimate consisting of the integral outbound of the |

CollProbSet | Calculates the probability of collision given two ellipsoid sets. For |

CollProbVol | Calculates the probability of collision given two ellipsoids |

CollisionInit | Sample data for collision algorithm initialization. |

CollisionMonAlg | Collision monitoring algorithm for maneuvering spacecraft. |

CollisionMonitor | Runs the collision monitoring algorithm. Checks the ellipsoids for self |

CollisionMonteCarlo | Perform a Monte-Carlo analysis of a relative orbit dynamics simulation |

CollisionSurvey | Runs the collision monitoring algorithm for n maneuvering spacecraft. |

ConjunctionPlane | Transformation matrix for relative conjunction geometry. The inertial |

DistantPtToEll | Finds the distance (and the corresponding point) from a distant |

EllipsePatch | 2D elliptical patch, with axes a along x and b along y |

EllipsePropCirc | Function finds the propagated state uncertainty ellipsoid |

Ellipsoid | Calculates an ellipsoid given the ellipsoid matrix, semimajor axes, |

GenerateTimeVector | Generate a time vector evenly spaced over true anomaly |

HillsDisturb | Disturbances in Hills frame. Includes uncertainty. |

Laguerre | Finds the polynomial roots using Laguerre's method. There is a fix in |

MinDEllipsoid | Computes the minimum distance between two ellipsoids. |

Plot3DEllipsoids | Plots ellipsoids given the ellipsoid centers and matrices |

PredictCollision | Runs the collision monitoring algorithm. Propagates forward for a fixed time |

RelativeDisturb | Relative disturbances for use with a relative state. |

VerifyCollStruct | Update computed fields in the collision data structure fields. |

ViewEllipsoid | Plots ellipsoids for Collision Monitoring given the ellipsoid centers and |

WorstCasePerturbations | Worst-case differential accelerations for spacecraft in formation. |

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ImpulsiveLPManeuver | Computes the delta-v sequence for a relative orbit maneuver. |

ImpulsiveManeuver | Computes a delta-v sequence for a relative orbit maneuver in a circular orbit |

InPlane | Computes the delta-v's required for an in-plane maneuver. |

IterativeImpulsiveManeuver | Computes the delta-v's required to implement a formation flying maneuver for |

LinOrbLQG | Generate an LQG controller for linearized relative orbit dynamics. |

Lyapunov | Compute a constant gain feedback controller for relative orbital motion. |

OptimalInPlaneDeltaV | Computes the delta-v's and half-orbit delays for an in-plane maneuver. |

OutOfPlane | Computes the delta-v's required for an out-of-plane maneuver. |

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AddGoals | Add one set of geometric goals to the other. |

AlignThruster | Computes the desired Hills-to-Body frame quaternion for a thruster firing. |

CirclePhase | Compute the desired phase on the circle from the desired phase on the ellipse. |

EllipsePhase | Compute the desired phase on the ellipse from the desired phase on the circle. |

GetHillsMats | This function takes the position and velocity of a satellite in the ECI |

GetLVLHMats | This function takes the position and velocity of a satellite in the ECI |

InitializeFormation | Generate the initial orbital elements for a cluster of spacecraft given |

IsCircGeom | Check whether the supplied data structure is for circular geometry or not. |

IsEccGeom | Check whether the supplied data structure is for eccentric geometry or not. |

LFState | Computes the position and velocity of a satellite in the Hills frame for a |

PCState | Computes the position and velocity of a satellite on the local ellipse |

ProjCirc | Calculates orbital elements for projected circular formation. |

ProjLine | Calculates orbital elements for an in-line formation. |

QFrenet | Generate the quaternion that transforms from the ECI to the Frenet frame. |

QHillsToBody | Compute the Hills-to-Body quaternion given the ECI position and velocity, and |

RotateState | Rotate a geometric state to the circular phase angle phi. |

ScaleState | Scale a relative state represented by a geometric goal set. This |

SubGoals | Subtract one set of geometric goals from the other. |

TeamGoals2Geom | Extract the geometry data from the team goals data structure |

ThrusterAlignment | Computes body vectors to align with velocity and nadir for a thruster firing. |

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BurnData_Structure | Initialize a burn data structure. |

Command_Structure | Command data structure for external commands supplied to DFF system. |

Constraints_Structure | Initialize a constraints data structure. |

CostEstimate_Structure | Initialize a cost estimate data structure. |

DeltaVCommand_Structure | Initialize a delta-v command data structure. |

EccGeometry_Structure | Initialize an eccentric geometry data structure. |

EccTeamGoals_Structure | Initialize a team goals data structure (for eccentric geometries) |

Geometry_Structure | Initialize a geometry data structure. |

ISLMessage_Structure | The ISL message data structure format. |

Maneuver_Structure | Initialize a maneuver data structure. |

Orientation_Structure | Initialize an orientation command data structure. |

PlanningParameters_Structure | Initialize a planning parameters data structure. |

State_Structure | Initialize a state data structure. |

TeamGoals_Structure | Initialize a team goals data structure. |

Team_Structure | Initialize a team data structure. |

Window_Structure | Initialize a window data structure. |

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AssignmentDemoMvr | Extension of AssignmentDemo to include collision monitoring. |

CoarseProbDemo | Coarse probability demo |

CollDetectSim | Simulation for testing the collision monitoring algorithms. |

CollMonDemo | Collision monitoring demo. |

CollisionCompareDemo | Collision monitoring demo: compare CollisionSurvey and coarse methods. |

DistantPtToEllDemo | Ellipsoid minimum distance demo |

ReconfigCollisionDemo | Collision monitoring demo for highly eccentric reconfiguration. |

SetProbabilityDemo | Set membership probability demo. Verify shape of function. |

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EccentricControlAnalysis | Analyze the performance of relative orbit control in eccentric orbits |

ExampleFFAnalysis | Demonstrate the use of FFMaintenanceSim to analyze disturbance effects. |

LQGEccDemo | Demonstrate LQG control of relative motion in an eccentric orbit |

LQGOrbitControlDemo | Relative orbit control using LQG |

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RotateStateDemo | Demonstrate the RotateState function |

TransECIToHills | Two orbits are initialized with a small inclination difference. The orbits |

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FFHEOSolarDist | Simulate relative motion in a HEO orbit with solar pressure disturbance |

PropagationExample | Compares the relative motion predicted by propagation of the discrete state-space system with the motion predicted by Hills equations. |

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EccTrajDemo | Demonstrate an example relative trajectory with an eccentric reference orbit |

FFEccAssignmentDemo | Demonstrate the different solutions found by the optimal assignment method and the privileged assignment method, in an eccentric orbit. |

FFEccInitDemo | Demonstrate how relative motion changes when the same relative state is initialized at different true anomalies. |

FFEccPropDemo | Compare discrete propagation with continuous solution. |

FFEccReconfigDemo | Compute several reconfiguation maneuvers of varying duration for an elliptical reference orbit. |

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AssignmentDemo | Demonstrate the different solutions found by the optimal assignment method and the privileged assignment method. |

DFFReconDemo | Run a formation flying simulation with "DFFSim". |

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LPConvergenceDemo | Examine the "convergence rate" for an impulsive LP solution |

LPPerformanceDemo | Analyze the performance of the LPEccentric algorithm. |

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SafeEllipseDemo | Demonstrate the safe ellipse for safe relative orbit guidance |

SafeGuidanceDemo | Demonstrate the performance of Safe Guidance Mode |

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IllustrateEccentricGeometry | Visualization of eccentric relative orbits |

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DiscreteHills | Computes the state trajectory (xS) of a satellite given the initial state (x0) |

FFIntegrate | Integrate two neighboring orbits, with applied relative accelerations |

HillsEqns | Closed form solution of relative orbital motion using Hills equations. |

RelativeOrbitRHS | Continuous-time linear model of Hills equations in Hills frame. |

ShortArcToHills | Convert short arc measurements to an approximate Hill's state. |

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FFEccDDX | Compute the second derivative of x with respect to true anomaly. |

FFEccDDY | Compute the second derivative of y with respect to true anomaly. |

FFEccDDZ | Compute the second derivative of z with respect to true anomaly. |

FFEccDX | Compute the first derivative of x with respect to true anomaly. |

FFEccDY | Compute the first derivative of y with respect to true anomaly. |

FFEccDYDX | Compute the slope of an ellipse, dy/dx, at a particular true anomaly. |

FFEccDYDX2 | Compute the second derivative of y with respect to x on an ellipse. |

FFEccDZ | Compute the first derivative of z with respect to true anomaly. |

DiscreteGVE | Computes the relative state trajectory in an eccentric reference orbit. |

FFEccDH | Compute integration constant dH for homogeneous solution to LTV diff eqs |

FFEccDMatPeriodic | Given an initial Hills state (xH0) at a particular true anomaly (nu0) |

FFEccDiscreteHills | Computes the relative state trajectory in an eccentric reference orbit. |

FFEccGoals | Compute integration constants and initial state given the geometric goals. |

FFEccH | Compute the H term for the homogeneous solution to LTV diff eqs |

FFEccIntConst | Compute integration constants for homogeneous solution to LTV diff eqs |

FFEccLawdensEqns | Compute Hills frame state given initial state, true anomaly, and eccentricity |

FFEccLinOrb | Compute the continous A,B matrices for linearized relative motion in an |

FFEccProp | Compute Hills frame state at nu given integ. constants and eccentricity. |

FFEccRMat | Compute the state-transition matrix, R, given the eccentricity and true anomaly. |

FFEccXExt | Compute extreme x-values and associated true anomalies for given relative motion. |

FFEccYExt | Compute extreme y-values and associated true anomalies for given relative motion. |

FFEccZExt | Compute extreme z-values and associated true anomalies for given relative motion. |

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AutoFormGeometry | Define new geometric goals for a single satellite, such that any semi-major |

CostMatrixRows | Given the team goals, determines the starting row (a) and ending row (b) |

DistributeClusterGoals | Given a set of geometric goals for the cluster, with corresponding target |

EstimateCost | Estimate the (weighted) cost to achieve all specified unique target states. |

FFEccEstimateCost | Estimate the weighted cost to achieve all specified unique target states |

FFEccGenerateTeamGoals | Generate a Team Goals data structure given the formation type and size. |

FFEccHexahedronGeometry | Compute the geometric goals for a formation that achieves a hexahedron |

FFEccTetrahedronGeometry | Compute the geometric goals for a formation that achieves a tetrahedron shape |

FindMinSet | Find the order of columns in a square matrix which minimizes |

GenerateTeamGoals | Generate a Team Goals data structure given the formation type and size. |

InitializeCostMatrix | Given the team goals, initialize the cost matrix "f" with the right size. |

IsDuplicateState | Determine whether two geometric goal sets are duplicates or not. |

NearestOffset | Determine the nearest along-track offset for a trajectory that is safe. |

OptimalAssignment | Compute the optimal configuration for a group of objects. |

PCGoals | Generate the geometric goals for a cluster in a projected circular formation. |

PopulateCostMatrix | Fill in a single column of the cost matrix. |

PrivilegedAssignment | Assign target states to satellites using the priveleged assignment method. |

RestrictIDSet | Given an initial set of relative spacecraft IDs, examine the constraints |

SetupAssignmentProblem | Set up the parameters for the assignment problem given the team goals struct. |

SortTeamGoals | Sort the team goals with fixed states listed before variable states. |

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DFFThrusters | Thruster pulsewidth model for DFF. |

IdealActuator | Ideal actuator |

CheckAlignment | Post simulation analysis. First load a data file from a DFF simulation into |

MessageAnalysis | Post-simulation message analysis for DFF. |

TestDFFModules | Test each DFF Module individually, in batch mode. |

AutoDualPCCommandList | Command list for the following scenario. |

AutoFormCommandList | Command list for testing autonomous formation and bridging of teams. |

ClusterGoalsDemoCommandList | Command list for demonstrating the achievement of cluster goals in a |

CollisionCommandList | Command list for monitoring a collision. Same as ProjCircCommandList |

CollisionDemoCommandList | Command list for collision monitoring demo scenario. |

CollisionDetectCommandList | Command list for Collision Detection Simulation |

DefaultCommandList | Command list template. |

DemoManeuverCommandList | Command list for the testing the controller. Two spacecraft initialized |

EccentricTetrahedronCommandList | Command list for achieving a tetrahedron formation in an eccentric orbit |

MainDemoCommandList | Command list for the main demo. Involves autonomous team formation |

ProjCircCommandList | Command list for achieving a dual-plane projected circle, |

SimpleManeuverCommandList | Command list for implementing a simple maneuver with 2 spacecraft. |

TeamManagementCommandList | Command list for exercising the team management functionality. |

TestADCSCommandList | Command list for testing the proper function of the ADCS. |

TestControlCommandList | Command list for the testing the controller. Two spacecraft initialized |

TestMonitoringCommandList | Command list for Collision Detection Simulation |

TestOrbAttControlCommandList | Command list for the testing the controller. Two spacecraft initialized |

TestTeamMgtCommandList | Command list for testing the functionality of the Team Management agent. |

DFFAttitudeTarget | Generate a reference quaternion for a variety of targets. There |

DFFControl | The executive function that initializes and runs the DFF software modules. |

DFFRHS | Right-hand-side of the spacecraft dynamic equations for the DFF system. |

DFFSimGUI | Computes the time left to go in the simulation, the predicted finish |

DFFSimulation | Initialize and run a multiple spacecraft simulation with the DFF software. |

DefaultTankData | Generate a data structure for fuel tank info. |

ParameterUploadDictionary | Load the dictionary of parameters that may be uploaded to the DFF system. |

SoftwareCommandDictionary | Load the dictionary of known software commands for the DFF system. |

SpacecraftParameters | Obtain the specified set of fixed spacecraft parameters (for DFF system). |

TelemetryDictionary | Load the dictionary of telemetry data to be gathered for the DFF system. |

AutoDualPCSimStruct | Define the simulation data structure for the following scenario. |

AutoFormSimStruct | Set up the data structure for a DFF simulation involving autonomous |

ClusterGoalsDemoSimStruct | Set up the data structure for a demonstration of achieving cluster goals |

CollisionDemoSimStruct | ProjCircSimStruct with a new command list to run collision survey. |

CollisionDetectSimStruct | Set up a DFF simulation data structure to demonstrate collision detection |

CollisionSimStruct | ProjCircSimStruct with a new command list to run collision survey. |

DFFSimStruct | Set up the data structure for a DFF simulation. All inputs are optional. |

DemoManeuverSimStruct | Set up the data structure for testing the controller. |

EccentricTetrahedronSimStruct | Initialize a DFF simulation data structure for a 4 spacecraft |

MainDemoSimStruct | Define the simulation data structure for the main demo |

ProjCircSimStruct | Set up the data structure for a DFF simulation involving a |

SimpleManeuverSimStruct | Set up the data structure for testing the controller. |

TeamManagementSimStruct | Set up the data structure for a Team Management demonstration of the DFF system. |

TestADCSSimStruct | Set up the data structure for a DFF simulation which tests the |

TestCollisionSimStruct | Set up a DFF simulation data structure to demonstrate collision detection |

TestControlSimStruct | Set up the data structure for testing the controller. |

TestOrbAttControlSimStruct | Set up the data structure for testing both orbit and attitude control. |

TestTeamMgtSimStruct | Set up the data structure for a DFF simulation which tests the |

RK4_DFFRHS | Fourth order Runge-Kutta for the DFF simulation right-hand-side. |

StateSensor | State sensor. Gives the ideal states of the system. |

DFFAttitudeController | This routine implements attitude control for the DFF system. PID |

DFFAttitudeCoordination | The attitude coordination component of the decentralized framework. |

DFFAttitudeManagement | The attitude management component of the decentralized framework. |

DFFAttitudeManeuver | This routine performs attitude maneuver planning. It takes a target |

DFFCollisionAvoidance | The Collision Avoidance module for the DFF system. |

DFFCollisionMonitor | The Collision monitoring component for the decentralized framework |

DFFCommandProcessing | Receive ground commands and route them to the appropriate module(s). |

DFFControlLaw | The decentralized control law. |

DFFCoordinateTransformation | The coordinate transformation element of the software. |

DFFDeltaVManagement | The delta-v management component of the control software. |

DFFGuidanceLaw | The decentralized guidance law. |

DFFISLManagement | The ISL management software for the decentralized framework. |

DFFModuleTemplate | Template for DFF software module. Describe the basic functionality here. |

DFFParameterDatabase | The parameter database for the decentralized formation flying framework. |

DFFRelativeNavigation | This routine estimates the absolute orbit of the local satellite, as |

DFFTeamManagement | The team management software for the decentralized satellite framework. |

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LPCircular | Computes the thrust trajectory to go from an initial state x0 |

LPCircularTimeWeight | Determine the target state on the desired trajectory that gives the minimum |

LPEccentric | Computes the thrust trajectory to go from an initial state x0 |

LPEccentricGVE | Computes the thrust trajectory to go from an initial state x0 to a |

LPEccentricTimeWeight | Determine the target state on the desired trajectory that gives the minimum |

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AlongTrackMotion | Compute attributes of along-track motion from relative state vector |

AnimateRE | Animate the evolution of the desired "safe ellipse" with the position |

ComputeRE | Compute a safe 2x1 relative in-plane ellipse. |

CrossTrackDeltaV | Compute the DV to achieve a min. cross-track dist. at along-track crossing. |

DeltaVChart | Generate a stacked bar chart showing delta-v directions over time |

EllipseDeltaV | Compute a delta-v that will change the current relative trajectory to a |

HillsEqnsSLO | Closed form solution of relative orbital motion using Hills equations. |

NominalSafeGuidance | The Nominal Safe Guidance method. |

PlotRun3D | Generate a 3D plot of a relative trajectory. |

PositionDeltaV | Compute delta-v required to reach a target position, given pos. and vel. |

RE2Hills | Compute the Hills-frame state associated with a relative ellipse. |

RE2SLO | Compute the SLO-frame state associated with a relative ellipse. |

RadialOscillation | Compute the radial oscillation of the relative motion using Hills eqns. |

RestrictDeltaV | Restrict the in-plane and cross-track components of the delta-v |

SafeEllipseParams | Compute the "safe ellipse" parameters from relative SLO-frame pos & vel |

SafeEllipsePosVel | Compute the relative SLO-frame position and velocity that corresponds to |

SafeGuidance | The Safe Guidance Mode. |

SafeGuidanceBurnData | Find index values for separation, nominal and cross-track burns. |

SafeGuidanceParameters | Tunable parameters for Safe Guidance and Collison Detection algorithms |

SafeGuidanceSim | Relative dynamic simulation for two LEO satellites with safe guidance. |

SafeGuidanceSimInit | Returns input data for various test cases for SafeGuidanceSim |

SafeGuidanceSimPlots | Plot select results from a simulation |

SeparationGuidance | The Separation Guidance method. |

YRMax | Compute the maximum value of yR |

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AbsRelECI2Hills | This function takes the absolute position and velocity in the ECI frame along |

DeltaAlfriend2El | Compute standard differential elements from Alfriend differential elements. |

DeltaEl2Alfriend | Compute Alfriend differential elements from standard differential elements. |

DeltaElem2Goals | Reconstructs the geometric goals from the element differences. |

DeltaElem2Hills | Computes the Hills frame state from orbital element differences and |

ECI2Hills | Compute the relative state in Hills frame given two ECI state vectors. |

ECI2LVLH | This function takes two ECI state vectors, and returns the relative state in |

ECI2MeanElements | Computes mean orbital elements from reference ECI position and velocity |

FFEccDeltaElem2Goals | Convert element differences to eccentric geometric goals. |

FFEccDeltaElem2Hills | Convert element differences to Hills frame coordinates in an eccentric orbit. |

FFEccFrenet2Goals | Compute geometric goals given Frenet frame state and orbit info |

FFEccGoals2Hills | Compute Hills frame state (time-domain) given geometric goals and orbit info |

FFEccHills2DeltaElem | Compute element differences from Hills frame state and ref. elements |

FFEccHills2Goals | Compute geometric goals given Hills frame state and orbit info |

Frenet2Hills | Rotate the Frenet frame state to the Hills frame, where x is radial |

GeometryCirc2Ecc | Convert a circular geometry structure to an eccentric geometry structure. |

GeometryEcc2Circ | Convert an eccentric geometry structure to a circular geometry structure. |

Goals2DeltaElem | Computes the desired orbital element differences, given the formation flying |

Goals2Hills | Computes the desired relative position and velocity in Hills frame, given the |

Hills2DeltaElem | Computes the orbital element differences from the Hills frame state and the |

Hills2ECI | Given the reference state in ECI, converts a Hills frame state to ECI. |

Hills2Frenet | Rotate the Hills frame state to the Frenet frame, where x is along-track |

Hills2Goals | Reconstructs the geometric goals from the relative position and velocity in |

Hills2LVLH | Converts a state vector from the Hills to the LVLH coordinate frame. |

LVLH2ECI | Given the reference state in ECI, converts an LVLH frame state to ECI. |

LVLH2Hills | Converts a state vector from the LVLH to the Hills coordinate frame. |

Mean2Osc | Transforms mean orbital elements to osculating orbital elements. |

Mean2OscS | Transforms mean orbital elements to osculating orbital elements. |

Osc2Mean | Transforms osculating orbital elements to mean orbital elements. |

TransformGeom2Hills | Transform geometric goals to hills-frame coordinates. |

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AccelVector2ManeuverStruct | Build a "maneuver" data structure from acceleration and time vectors. |

ApplyDeltaV | Apply delta-v over a specified time interval with a simulation timestep |

DataSize | Find the size in bytes of a piece of data. |

FFEccTargetTrueAnom | Compute the future true anomaly (unwrapped) at the specified number of orbits |

Hexahedron | Compute the 5 points of a regular tetrahedron, the surface area and volume. |

JD2SS1970 | Converts a Julian Date to seconds since 00:00:00 GMT, Jan. 1, 1970. |

ManeuverStruct2AccelVector | Compute a 3xN acceleration vector from a "maneuver" data structure. |

MeanAnom2TrueLat | Convert mean anomaly to true latitude. |

NOrbVector | Compute a vector of maneuver durations from time window data |

NewtRaph2 | Finds the solution to f(x) = 0 given df(x)/dx when only one |

Nu2TimeDomain | Convert a relative state from the nu-domain to the time-domain. |

NuDot | Compute the time-derivative of the true anomaly. |

RVOrbGenDV | Generate an orbit by propagating Keplerian elements with impulsive delta-vs. |

SS19702JD | Converts seconds since 00:00:00 GMT, Jan. 1, 1970 to a Julian date. |

Tetrahedron | Compute the 4 points of a regular tetrahedron, the surface area and volume. |

Time2NuDomain | Convert a relative state from the time-domain to the nu-domain. |

TimeUntilTheta | Computes the time in seconds until the latitude "theta2" is reached from the |

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CostVis | Visualize the cost to achieve each target state on the trajectory. |

DisplayPlugin | Display Plugin for the Formation Design GUI. |

FFEccAnalyzeShape | Interactively analyze the shape of a relative trajectory in an eccentric reference orbit. |

FFEccShapes | Compute the shape of the relative motion in the orbital plane. |

FormationDesignGUI | Formation Design GUI. |

GeometryPlugin | Geometry Plugin for the Formation Design GUI. |

HillsFramePlot | Plot the trajectory in Hills frame and show the x-z, x-y projections. |

OrbitDataPlugin | Orbit Data Plugin for the Formation Design GUI. |

RelativeStatePlugin | Relative State Plugin for the Formation Design GUI. |

SatellitePlugin | Satellite Plugin for the Formation Design GUI. |

ShowTeams | Graphically show the hierarchy of teams. |

TeamLevels | Assign a hierarchical level to each team in the array. |

TeamPlugin | Team Plugin for the Formation Design GUI. |

ViewFormation | View the 3-D trajectory of a formation in Hills frame. |

ViewGeometry | View the geometry created by a formation of spacecraft |

ViewHills | Given the reference orbital elements, a time span, and the spacecrafts' |

ViewRelativeMotion | View the relative motion associated with a set of geometric goals and a |

ViewRotatingHillsFrame | Animate a satellite's relative trajectory in the inertial frame. |

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SVN Revision: 42334

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