See: Description
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  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  
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 onepoint 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  
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  
LambertResult 
Contains the results produced by the
LambertOrbitSolver . 
LifetimeOrbitPropagator 
Propagates a set of initial conditions using a longterm 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) GPS200D.

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  
Sgp4ElementsSwitchByMidpoint  
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  
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, criticallyinclined, stationary, Molniya, repeat ground trace, and Sunsynchronous.

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  
TwoBodyPropagator 
Propagates an orbit using a simple twobody model.

TwoBodyStateTransitionMatrixPropagator 
Propagates the state transition matrix of an object using a simple twobody model.

TwoBodyStoppablePropagator 
A
StoppablePropagator that propagates an orbit using a simple twobody model. 
TwoLineElementSet 
A NORAD twoline 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  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  
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  Description 

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