Package agi.foundation.propagators

Contains types used in producing the state of an object from a known element set.

See: Description

Interface Summary

Interface	Description
IGpsElements	An interface to a GPS element set that contains data items needed for GPS ephemeris propagation.
IUpdatePriorToStep	An interface to an object created by a PropagationStateElement that has special behavior that takes place each time step prior to propagation.

Class Summary

Class	Description
AuxiliaryStateScalar	Represents a scalar value which may depend on integrated quantities in the state and is evaluated and stored for output during propagation.
AuxiliaryStateVector	An auxiliary state vector which is not integrated with the rest of the state but is evaluated for the propagation output during propagation.
BallisticPropagator	This class calculates a ballistic trajectory (two body gravity only) between two locations on a CentralBody (get / set).
BallisticTrajectoryInformation	An object with many metrics that describe a ballistic trajectory from an initial point to a target point.
CartesianOnePointPropagator	The base class for simple one-point propagators that produce only Motion1.
CelestrakGeneralPerturbationElements	Celestrak general perturbation (GP) orbital elements.
ConstantStateStoppablePropagator	A StoppablePropagator that always returns the initial state passed in at propagation time.
DynamicStateStoppablePropagator	A StoppablePropagator that evaluates a StateEvaluator in time until a StoppingCondition is tripped.
ExceptionDuringPropagationEventArgs	Provides information about the exception during propagation event conditions.
GpsRinexPropagator	GPS RINEX Propagator class propagates GPS orbits - providing GPS satellite positions based on RINEX broadcast ephemeris sets.
InitialOrbitSolver	Solves for an initial orbit under two body conditions.
InitialOrbitSolverResults	Contains the results produced by the InitialOrbitSolver.
J2Propagator	An analytic propagator that uses a first order J2 perturbation algorithm which models only the secular effects on the orbital elements.
J4Propagator	An analytic propagator that uses a second order J2/J4 perturbation algorithm which models only the secular effects on the orbital elements.
LambertOrbitSolver	Solves the orbit targeting problem and initial orbit determination.
LambertOrbitSolver.FailedToConvergeEventArgs	Holds details of the FailedToConvergeEvent (add / remove) event.
LambertResult	Contains the results produced by the LambertOrbitSolver.
LifetimeOrbitPropagator	Propagates a set of initial conditions using a long-term propagation technique to determine when the orbit is expected to decay, based on the evolution of the mean orbital elements under the effects of gravitational, atmospheric, and solar perturbations.
NavstarISGps200DPropagator	Propagates the orbit of a Global Positioning System (GPS) satellite according to the propagation scheme defined in the Navstar Interface Specific (IS) GPS-200D.
NumericalIntegrationInformation	Contains information about the behavior of an integrator in a given integration step.
NumericalPropagationStateHistory	Contains a collection of data resulting from propagating the state over a span of time.
NumericalPropagator	A propagator which can advance the state from initial conditions by either taking individual integration steps or by propagating over a given time span.
NumericalPropagatorDefinition	The definitional object that creates a NumericalPropagator.
NumericalPropagatorState	A state representing every propagated value in a particular NumericalPropagator.
OrbitLifetimeResults	A set of results indicating the time at which an orbit is expected to decay and the time history of the mean elements.
PropagationEulerianAxes	A PropagationStateElement representing the attitude (and angular velocity) of a rigid body with its angular acceleration represented by Euler's equations of motion.
PropagationEventArgs	Provides information about the current propagation event conditions and provides a means of indicating how the propagation should continue.
PropagationNewtonianPoint	An PropagationStateElement representing the position (and velocity) of a body with its second derivative defined by Newton's second law of motion: Acceleration = AppliedForce / Mass
PropagationScalar	An PropagationStateElement representing a scalar value to be integrated over time.
PropagationStateArray	Provides a means of specifying an indexable object which represents a set of values mapping a subset of the overall state elements.
PropagationStateConverter	A converter which can take raw data from the output of propagation and turn it into useful data by using PropagationStateElement and AuxiliaryStateElement converter types to convert to their corresponding output types.
PropagationVector	A PropagationStateElement representing a vector value to be integrated over time.
PropagatorPoint	A point with its location computed by a propagator.
Sgp4Elements	A set of orbital elements intended to be propagated with the SGP4 propagator.
Sgp4ElementsSwitchByClosestApproach	An algorithm which determines when to switch from one element set to another by propagating each element set against the next to determine the time at which the range between the positions of the two orbits is the smallest.
Sgp4ElementsSwitchByEpoch	An algorithm which determines when to switch from one element set to another by comparing their respective Epoch (get / set) values.
Sgp4ElementsSwitchByMidpoint	An algorithm which determines when to switch from one element set to another by comparing their respective Epoch (get / set) values.
Sgp4ElementsSwitching	An algorithm for determining when to switch from one set of elements to another.
Sgp4Propagator	Propagates an orbit using the NORAD SGP4/SDP4 model as defined by the Center for Space Standards and Innovation (CSSI).
Sgp4Propagator.Sgp4EstimationInput	A class containing configuration information for the static estimation methods available on the Sgp4Propagator.
Sgp4Propagator.Sgp4EstimationOutput	A class containing the estimated Sgp4Elements along with the associated information from the fit.
SimpleAscentPropagator	Propagates a simple (point) launch vehicle from a CentralBody (get / set) to a specified burnout motion.
SimpleAscentPropagatorWarnings	The arguments passed to any event handlers listening for propagation warnings that may be produced when using the SimpleAscentPropagator.
SinglePointStoppablePropagator	Samples a Point at a specified time step until a StoppingCondition is satisfied, returning the ephemeris computed and all events found by the StoppingConditions (get).
SinglePointStoppablePropagatorDefinition	Provides the infrastructure to use a Point as a basis for propagating a trajectory that can be stopped with StoppingConditions.
SinglePointStoppablePropagatorResults	The StoppablePropagatorResults returned from a SinglePointStoppablePropagator.
SpecializedOrbitSolver	Create propagators that model specialized orbit types, including: circular, critically-inclined, stationary, Molniya, repeat ground trace, and Sun-synchronous.
StateTransitionMatrix	An extended state transition matrix, if consider parameters are not used then it functions as a normal state transition matrix: mapping the value of the state parameters from one time to another time.
StoppableNumericalPropagator	A StoppablePropagator that wraps a PropagatorDefinition (get / set) and will find events and stop based on a set of StoppingConditions.
StoppableNumericalPropagatorResults	Stores the ephemeris computed by a NumericalPropagator and information about how the propagation was stopped.
StoppablePropagator	A propagator that wraps some type that generates states and will sample some derived value from those states searching for events and eventually an event that will stop propagation with StoppingConditionEvaluators.
StoppablePropagatorDefinition	Defines a propagator that can propagate to arbitrary events and stop on any StoppingCondition.
StoppablePropagatorResults	The results of a StoppablePropagator.
StoppablePropagatorStepTakenArgs	The data for the event that gets raised when a StoppablePropagator takes a step or resteps.
TwoBodyPropagator	Propagates an orbit using a simple two-body model.
TwoBodyStateTransitionMatrixPropagator	Propagates the state transition matrix of an object using a simple two-body model.
TwoBodyStoppablePropagator	A StoppablePropagator that propagates an orbit using a simple two-body model.
TwoLineElementSet	A NORAD two-line element set (TLE).
UsafGeneralPerturbationElements	United States Air Force (USAF) general perturbation (GP) orbital elements.
WalkerConstellation	Supports the creation of Walker constellations of satellites.
WalkerConstellationPlane<TPropagator>	A collection of satellite propagators with the same inclination and right ascension of the ascending node but differing true anomalies.
WalkerConstellationResult<TPropagator>	A collection of satellite orbital planes with the same inclination but differing right ascensions of the ascending node.
Waypoint	Defines the characteristics at a waypoint.
WaypointCollection	A collection of Waypoints.
WaypointPropagator	Propagates a path connecting waypoints relative to an ellipsoid.

Enum Summary

Enum	Description
BallisticPropagatorSolutionType	Species the kind of solution that was calculated by a BallisticPropagator, IE whether the desired trajectory was successfully calculated, the propagator failed to converge on a solution, or the specified constraint was invalid.
GeneralPerturbationObjectType	The classification of an orbiting body for a UsafGeneralPerturbationElements.
LambertPathType	Indicates which type of path to take in the LambertOrbitSolver.
LifetimeCalculationLimitType	Specifies how the LifetimeOrbitPropagator should behave when determining completion of the computation.
LifetimeCalculationStatus	An indication of the final state of the LifetimeOrbitPropagator calculation.
PropagationEventIndication	An indication of how the propagator should proceed.
PropagationEventTrigger	Indicates which kind of propagation method triggered the StepTaken (add / remove) event.
PropagationStage	An enumerator that communicates the which stage of propagation an evaluator is called during.
SimpleAscentPropagatorAscentType	The type of spline to use in the SimpleAscentPropagator.
SimpleAscentPropagatorBurnoutVelocityFrame	Sets the CentralBody-relative frame used to specify the burnout velocity in SimpleAscentPropagator.
SortingFormat	An enumeration that defines the order in which entries in a NumericalPropagationStateHistory are sorted.
TransitionType	An enumeration that defines the format of transformation described by a StateTransitionMatrix.
WalkerConstellationPattern	Determines whether a Walker constellation has a delta pattern or a star pattern.

Exception Summary

Exception	Description
NumericalPropagationException	An exception that indicates an error was encountered during propagation.

Package agi.foundation.propagators Description

Contains types used in producing the state of an object from a known element set.