Example usage for org.apache.commons.math3.ode AbstractParameterizable subclass-usage

Introduction

In this page you can find the example usage for org.apache.commons.math3.ode AbstractParameterizable subclass-usage.

Usage

From source file org.orekit.propagation.conversion.KeplerianPropagatorBuilder.java

/** Builder for Keplerian propagator.
 * @author Pascal Parraud
 * @since 6.0
 */
public class KeplerianPropagatorBuilder extends AbstractParameterizable implements PropagatorBuilder {

From source file org.orekit.forces.gravity.NewtonianAttraction.java

/** Force model for Newtonian central body attraction.
 * @author Luc Maisonobe
 */
public class NewtonianAttraction extends AbstractParameterizable implements ForceModel {

    /** Name of the single parameter of this model: the central attraction coefficient. */

From source file org.orekit.propagation.conversion.EcksteinHechlerPropagatorBuilder.java

/** Builder for Eckstein-Hechler propagator.
 * @author Pascal Parraud
 * @since 6.0
 */
public class EcksteinHechlerPropagatorBuilder extends AbstractParameterizable implements PropagatorBuilder {

From source file org.orekit.forces.gravity.ThirdBodyAttraction.java

/** Third body attraction force model.
 *
 * @author Fabien Maussion
 * @author Véronique Pommier-Maurussane
 */
public class ThirdBodyAttraction extends AbstractParameterizable implements ForceModel {

From source file org.orekit.forces.gravity.Relativity.java

/**
 * Post-Newtonian correction force due to general relativity. The main effect is the
 * precession of perigee by a few arcseconds per year.
 *
 * <p> Implemented from Montenbruck and Gill equation 3.146.
 *

From source file org.orekit.forces.drag.DragForce.java

/** Atmospheric drag force model.
 *
 * The drag acceleration is computed as follows :
 *
 *  = (1/2 * ? * V * S / Mass) * DragCoefVector
 *

From source file org.orekit.forces.maneuvers.ConstantThrustManeuver.java

/** This class implements a simple maneuver with constant thrust.
 * <p>The maneuver is defined by a direction in satelliteframe.
 * The current attitude of the spacecraft, defined by the current
 * spacecraft state, will be used to compute the thrust direction in
 * inertial frame. A typical case for tangential maneuvers is to use a
 * {@link org.orekit.attitudes.LofOffset LOF aligned} attitude provider for state propagation and a

From source file org.orekit.forces.gravity.SolidTides.java

/** Solid tides force model.
 * @since 6.1
 * @author Luc Maisonobe
 */
public class SolidTides extends AbstractParameterizable implements ForceModel {

From source file org.orekit.forces.gravity.OceanTides.java

/** Ocean tides force model.
 * @since 6.1
 * @author Luc Maisonobe
 */
public class OceanTides extends AbstractParameterizable implements ForceModel {

From source file org.orekit.forces.radiation.SolarRadiationPressure.java

/** Solar radiation pressure force model.
 *
 * @author Fabien Maussion
 * @author Édouard Delente
 * @author Véronique Pommier-Maurussane
 * @author Pascal Parraud

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