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Packages that use AdditionalEquations | |
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fr.cnes.sirius.patrius.assembly.models | |
fr.cnes.sirius.patrius.assembly.properties | |
fr.cnes.sirius.patrius.propagation.numerical.multi | |
org.orekit.propagation | This package provides tools to propagate orbital states with different methods. |
org.orekit.propagation.numerical |
Uses of AdditionalEquations in fr.cnes.sirius.patrius.assembly.models |
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Methods in fr.cnes.sirius.patrius.assembly.models that return AdditionalEquations | |
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AdditionalEquations |
InertiaSimpleModel.getAdditionalEquation(String partName)
Get the mass equation related to the part. |
AdditionalEquations |
InertiaComputedModel.getAdditionalEquation(String name)
Get the mass equation related to the part. |
AdditionalEquations |
MassModel.getAdditionalEquation(String name)
Get the mass equation related to the part. |
Uses of AdditionalEquations in fr.cnes.sirius.patrius.assembly.properties |
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Classes in fr.cnes.sirius.patrius.assembly.properties that implement AdditionalEquations | |
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class |
MassEquation
This class represents the mass equation with a name in the form "MASS_ |
Uses of AdditionalEquations in fr.cnes.sirius.patrius.propagation.numerical.multi |
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Methods in fr.cnes.sirius.patrius.propagation.numerical.multi with parameters of type AdditionalEquations | |
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void |
MultiNumericalPropagator.addAdditionalEquations(AdditionalEquations addEqu,
String satId)
Add a set of user-specified equations to be integrated along with the orbit propagation. |
Uses of AdditionalEquations in org.orekit.propagation |
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Methods in org.orekit.propagation that return AdditionalEquations | |
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AdditionalEquations |
MassProvider.getAdditionalEquation(String name)
Get the mass equation related to the part. |
AdditionalEquations |
SimpleMassModel.getAdditionalEquation(String name)
Get the mass equation related to the part. |
Uses of AdditionalEquations in org.orekit.propagation.numerical |
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Classes in org.orekit.propagation.numerical that implement AdditionalEquations | |
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class |
AttitudeEquation
This interface allows users to add their own attitude differential equations to a numerical propagator. |
class |
PartialDerivativesEquations
Set of additional equations computing the partial derivatives
of the state (orbit) with respect to initial state and force models parameters. |
Methods in org.orekit.propagation.numerical with parameters of type AdditionalEquations | |
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void |
NumericalPropagator.addAdditionalEquations(AdditionalEquations addEqu)
Add a set of user-specified equations to be integrated along with the orbit propagation. |
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