Uses of Interface
org.orekit.propagation.numerical.TimeDerivativesEquations

Packages that use TimeDerivativesEquations

fr.cnes.sirius.patrius.assembly.properties
fr.cnes.sirius.patrius.forces
fr.cnes.sirius.patrius.forces.radiation
org.orekit.forces	This package provides the interface for force models that will be used by the NumericalPropagator, as well as some classical spacecraft models for surface forces (spherical, box and solar array ...).
org.orekit.forces.drag
org.orekit.forces.gravity
org.orekit.forces.gravity.tides
org.orekit.forces.gravity.variations
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation
org.orekit.forces.relativistic
org.orekit.propagation.numerical

Uses of TimeDerivativesEquations in fr.cnes.sirius.patrius.assembly.properties

Methods in fr.cnes.sirius.patrius.assembly.properties with parameters of type TimeDerivativesEquations

void	MassEquation.computeDerivatives(SpacecraftState s, TimeDerivativesEquations adder) Compute the derivatives related to the additional state parameters.

Uses of TimeDerivativesEquations in fr.cnes.sirius.patrius.forces

Methods in fr.cnes.sirius.patrius.forces with parameters of type TimeDerivativesEquations

void	EmpiricalForce.addContribution(SpacecraftState state, TimeDerivativesEquations adder)

Uses of TimeDerivativesEquations in fr.cnes.sirius.patrius.forces.radiation

Methods in fr.cnes.sirius.patrius.forces.radiation with parameters of type TimeDerivativesEquations

void	PatriusSolarRadiationPressure.addContribution(SpacecraftState s, TimeDerivativesEquations adder)

Uses of TimeDerivativesEquations in org.orekit.forces

Methods in org.orekit.forces with parameters of type TimeDerivativesEquations

void	ForceModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.

Uses of TimeDerivativesEquations in org.orekit.forces.drag

Methods in org.orekit.forces.drag with parameters of type TimeDerivativesEquations

void	DragForce.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the drag to the perturbing acceleration.

Uses of TimeDerivativesEquations in org.orekit.forces.gravity

Methods in org.orekit.forces.gravity with parameters of type TimeDerivativesEquations

void	BalminoAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	DrozinerAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	ThirdBodyAttraction.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	CunninghamAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	NewtonianAttraction.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.

Uses of TimeDerivativesEquations in org.orekit.forces.gravity.tides

Methods in org.orekit.forces.gravity.tides with parameters of type TimeDerivativesEquations

void	AbstractTides.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.

Uses of TimeDerivativesEquations in org.orekit.forces.gravity.variations

Methods in org.orekit.forces.gravity.variations with parameters of type TimeDerivativesEquations

void	VariablePotentialAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.

Uses of TimeDerivativesEquations in org.orekit.forces.maneuvers

Methods in org.orekit.forces.maneuvers with parameters of type TimeDerivativesEquations

void	ConstantThrustManeuver.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	ConstantThrustError.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the constant thrust error model to the perturbing acceleration.
void	VariableThrustManeuver.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.

Uses of TimeDerivativesEquations in org.orekit.forces.radiation

Methods in org.orekit.forces.radiation with parameters of type TimeDerivativesEquations

void	RediffusedRadiationPressure.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	SolarRadiationPressure.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.

Uses of TimeDerivativesEquations in org.orekit.forces.relativistic

Methods in org.orekit.forces.relativistic with parameters of type TimeDerivativesEquations

void	SchwarzschildRelativisticEffect.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	LenseThirringRelativisticEffect.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	CoriolisRelativisticEffect.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.

Uses of TimeDerivativesEquations in org.orekit.propagation.numerical

Methods in org.orekit.propagation.numerical with parameters of type TimeDerivativesEquations

void	PartialDerivativesEquations.computeDerivatives(SpacecraftState s, TimeDerivativesEquations adder) Compute the derivatives related to the additional state parameters.
void	AdditionalEquations.computeDerivatives(SpacecraftState s, TimeDerivativesEquations adder) Compute the derivatives related to the additional state parameters.