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java.lang.Objectfr.cnes.sirius.patrius.stela.forces.AbstractStelaLagrangeContribution
fr.cnes.sirius.patrius.stela.forces.radiation.SRPPotential
public class SRPPotential
This class represents the PRS Lagrange contribution in the STELA propagator context.
Field Summary |
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Fields inherited from class fr.cnes.sirius.patrius.stela.forces.AbstractStelaLagrangeContribution |
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dPot |
Constructor Summary | |
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SRPPotential(PVCoordinatesProvider sun,
double m,
double s,
double c)
create a SRP Potential model using the sun and spacecraft characteristics. |
Method Summary | |
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double[][] |
computePartialDerivatives(StelaEquinoctialOrbit orbit)
Compute the partial derivatives for a given spacecraft state. |
double[] |
computePerturbation(StelaEquinoctialOrbit orbit)
Compute the dE/dt force derivatives for a given spacecraft state. |
double[] |
computeShortPeriods(StelaEquinoctialOrbit orbit)
Compute the short periodic variations for a given spacecraft state. |
Methods inherited from class fr.cnes.sirius.patrius.stela.forces.AbstractStelaLagrangeContribution |
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getdPot, getType |
Methods inherited from class java.lang.Object |
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clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait |
Constructor Detail |
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public SRPPotential(PVCoordinatesProvider sun, double m, double s, double c)
sun
- sun as a celestial bodym
- mass of spacecrafts
- surface of spacecraftc
- relexion coefficient of spacecraftMethod Detail |
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public double[] computePerturbation(StelaEquinoctialOrbit orbit) throws OrekitException
computePerturbation
in class AbstractStelaLagrangeContribution
orbit
- current orbit information: date, kinematics
OrekitException
- if perturbation computation failspublic double[] computeShortPeriods(StelaEquinoctialOrbit orbit)
orbit
- current orbit information: date, kinematics
public double[][] computePartialDerivatives(StelaEquinoctialOrbit orbit) throws OrekitException
orbit
- current orbit information: date, kinematics
OrekitException
- if partial derivatives computation fails
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