FormationFlying Module

Directory List

Analysis

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.

Collision

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.

Control

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.

Coord

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.

DataStructures

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.

Demos/Collision

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.

Demos/Control

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

Demos/Coord

RotateStateDemo	Demonstrate the RotateState function
TransECIToHills	Two orbits are initialized with a small inclination difference. The orbits

Demos/Dynamics

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.

Demos/Eccentric

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.

Demos/Guidance

AssignmentDemo	Demonstrate the different solutions found by the optimal assignment method and the privileged assignment method.
DFFReconDemo	Run a formation flying simulation with "DFFSim".

Demos/LP

LPConvergenceDemo	Examine the "convergence rate" for an impulsive LP solution
LPPerformanceDemo	Analyze the performance of the LPEccentric algorithm.

Demos/SafeGuidance

SafeEllipseDemo	Demonstrate the safe ellipse for safe relative orbit guidance
SafeGuidanceDemo	Demonstrate the performance of Safe Guidance Mode

Demos/Visual

IllustrateEccentricGeometry

Visualization of eccentric relative orbits

Dynamics

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.

EccDynamics

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.

Guidance

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.

IntegratedSim

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.

LP

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

SafeGuidance

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

Transformation

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.

Utility

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

Visual

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.

SVN Revision: 42334

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