Propagator Toolkit

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Detailed Description

The propagator toolkit contains all the functionality required to propagate the full dynamics of a spacecraft. This can include only attitude or orbit dynamics, combined, or even propagation using an external source of states, such as another simulation program or hardware.

The Propagator class offers an abstract interface to the specific propagation strategies that implement each of the examples given above, as well as any further user defined algorithms. A propagator requires the following parts:

• Orbit object (if propagating with an orbit), including:
  • Dynamic equations, the right-hand side, or time derivate equations (odeFunctor)
  • A state conversion function that converts the integrated state variables to an object stored in OrbitHistory.
  • An Interpolator in the OrbitHistory.
• Attitude object (if propagating with an attitude), including:
  • Dynamic equations, the right-hand side, or time derivate equations (odeFunctor)
  • A state conversion function that converts the integrated state variables to an object stored in AttitudeHistory
  • An Interpolator in the AttitudeHistory
• An attitude state propagator
  • Use either an Integrator
  • Tie in the external source to the AttitudeHistory object (Exporter, Communications)
• An orbit state propagator
  • Use either an Integrator
  • Tie in the external source to the OrbitHistory object (Exporter, Communications)
• An Environment object
  • Environmental force and torque disturbance functions (EnvFunction)
  • A CentralBody (EarthCentralBody, MoonCentralBody, etc.)

An example of a propagator use is included in testPropagation.cpp.

Extension Points:

The propagation toolkit currently has functionality for independent attitude & orbit propagation, as well as combined propagation using weak coupling, and full coupling. Any new propagation schemes should be derived from the appropriate AnalyticPropagator or NumericPropagator interface classes as necessary.

Classes
class	O_SESSAME::AnalyticPropagator
	Encapsulation of the propagation of the spacecraft dynamics (attitude, orbital, etc.). More...
class	O_SESSAME::Propagator
	Encapsulation of the propagation of the spacecraft dynamics (attitude, orbital, etc.). More...
Typedefs
typedef void(*	O_SESSAME::IntegratedAttitudeStateConversionFunction )(const Matrix &_meshPoint, AttitudeState &_convertedAttitudeState)
	Defined function pointer to integrated attitude state conversion function.
typedef void(*	O_SESSAME::IntegratedOrbitStateConversionFunction )(const Matrix &_meshPoint, OrbitState &_convertedOrbitState)
	Defined function pointer to integrated orbital state conversion function.

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Typedef Documentation

typedef void(* O_SESSAME::IntegratedAttitudeStateConversionFunction)(const Matrix &_meshPoint, AttitudeState &_convertedAttitudeState)

Defined function pointer to integrated attitude state conversion function. Converts a vector of meshpoints (from integrated states) to the corresponding generalized AttitudeState. Parameters: _meshPoint  vector of values of the meshpoint to be converted _convertedAttitudeState  Calculated AttitudeState from the converted meshpoint that is returned to the caller. Definition at line 32 of file Attitude.h. Referenced by O_SESSAME::Attitude::GetStateConversion().

typedef void(* O_SESSAME::IntegratedOrbitStateConversionFunction)(const Matrix &_meshPoint, OrbitState &_convertedOrbitState)

Defined function pointer to integrated orbital state conversion function. Converts a vector of meshpoints (from integrated states) to the corresponding generalized OrbitState. Parameters: _meshPoint  vector of values of the meshpoint to be converted _convertedOrbitState  Calculated Orbit state from the converted meshpoint that is returned to the caller. Definition at line 33 of file Orbit.h. Referenced by O_SESSAME::Orbit::GetStateConversion().

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