Uses of Class
fr.cnes.sirius.patrius.stela.orbits.StelaEquinoctialOrbit

Packages that use StelaEquinoctialOrbit

fr.cnes.sirius.patrius.stela.forces
fr.cnes.sirius.patrius.stela.forces.drag
fr.cnes.sirius.patrius.stela.forces.gravity
fr.cnes.sirius.patrius.stela.forces.noninertial
fr.cnes.sirius.patrius.stela.forces.radiation
fr.cnes.sirius.patrius.stela.orbits
fr.cnes.sirius.patrius.stela.propagation

Uses of StelaEquinoctialOrbit in fr.cnes.sirius.patrius.stela.forces

Methods in fr.cnes.sirius.patrius.stela.forces that return StelaEquinoctialOrbit

static StelaEquinoctialOrbit[]

Squaring.computeSquaringPointsEccentric(int numPoints, StelaEquinoctialOrbit orbit) Computation of squaring points equally distributed according to eccentric anomaly.

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

protected double[][][]	AbstractStelaGaussContribution.computeGaussDerivativeEquations(StelaEquinoctialOrbit orbit) Computation of the Gauss equation derivatives matrix in TNW frame.
protected double[][]	AbstractStelaGaussContribution.computeGaussEquations(StelaEquinoctialOrbit orbit) Compute the TNW Gauss Equation for GTO.
double[][][]	StelaLagrangeEquations.computeLagrangeDerivativeEquations(StelaEquinoctialOrbit orbit) Computation of the Lagrange equation derivatives matrix (Poisson Bracket derivatives).
double[][]	StelaLagrangeEquations.computeLagrangeEquations(StelaEquinoctialOrbit orbit) Compute the Lagrange Equation for GTO (Poisson Bracket).
double[][]	StelaLagrangeEquations.computeLagrangeEquations(StelaEquinoctialOrbit orbit, double mu) Compute the Lagrange Equation for GTO (Poisson Bracket) with specific mu.
double[][]	StelaForceModel.computePartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives for a given spacecraft state.
abstract double[]	AbstractStelaLagrangeContribution.computePerturbation(StelaEquinoctialOrbit orbit) Compute the dE/dt force derivatives for a given spacecraft state.
abstract double[]	AbstractStelaGaussContribution.computePerturbation(StelaEquinoctialOrbit orbit, OrbitNatureConverter converter) Compute the dE/dt force derivatives for a given spacecraft state.
double[]	StelaForceModel.computeShortPeriods(StelaEquinoctialOrbit orbit) Compute the short periodic variations for a given spacecraft state.
static double[][]	Squaring.computeSquaringPoints(int numPoints, StelaEquinoctialOrbit orbit, double startPoint, double endPoint) Computation of squaring points equally distributed according to true anomaly.
static StelaEquinoctialOrbit[]	Squaring.computeSquaringPointsEccentric(int numPoints, StelaEquinoctialOrbit orbit) Computation of squaring points equally distributed according to eccentric anomaly.

Uses of StelaEquinoctialOrbit in fr.cnes.sirius.patrius.stela.forces.drag

Methods in fr.cnes.sirius.patrius.stela.forces.drag with parameters of type StelaEquinoctialOrbit

double[][]	StelaAtmosphericDrag.computePartialDerivatives(StelaEquinoctialOrbit orbit)
double[]	StelaAtmosphericDrag.computePerturbation(StelaEquinoctialOrbit orbit, OrbitNatureConverter converter)
double[]	StelaAtmosphericDrag.computeShortPeriods(StelaEquinoctialOrbit orbit)

Uses of StelaEquinoctialOrbit in fr.cnes.sirius.patrius.stela.forces.gravity

Methods in fr.cnes.sirius.patrius.stela.forces.gravity with parameters of type StelaEquinoctialOrbit

double[]	StelaZonalAttraction.computeJ10(StelaEquinoctialOrbit orbit) Compute the effect of the 10th degree development of the Zonal Perturbation
double[]	StelaZonalAttraction.computeJ11(StelaEquinoctialOrbit orbit) Compute the effect of the 11th degree development of the Zonal Perturbation
double[]	StelaZonalAttraction.computeJ12(StelaEquinoctialOrbit orbit) Compute the effect of the 12th degree development of the Zonal Perturbation
double[]	StelaZonalAttraction.computeJ13(StelaEquinoctialOrbit orbit) Compute the effect of the 13th degree development of the Zonal Perturbation
double[]	StelaZonalAttraction.computeJ14(StelaEquinoctialOrbit orbit) Compute the effect of the 14th degree development of the Zonal Perturbation
double[]	StelaZonalAttraction.computeJ15(StelaEquinoctialOrbit orbit) Compute the effect of the 15th degree development of the Zonal Perturbation
double[]	StelaZonalAttraction.computeJ2(StelaEquinoctialOrbit orbit) Compute the effect of the 2nd degree development of the Zonal Perturbation
double[]	StelaZonalAttraction.computeJ2(StelaEquinoctialOrbit orbit, double mu) Compute the effect of the 2nd degree development of the Zonal Perturbation with specific mu.
double[][]	StelaZonalAttraction.computeJ2PartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives due to J2 Potential effect
double[]	StelaZonalAttraction.computeJ2ShortPeriods(StelaEquinoctialOrbit orbit) Compute the short periods linked to J2 Potential effect
double[]	StelaZonalAttraction.computeJ2Square(StelaEquinoctialOrbit orbit) Compute the effect of the J2² of the Zonal Perturbation.
double[][]	StelaZonalAttraction.computeJ2SquarePartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives due to J2² Potential effect
double[]	StelaZonalAttraction.computeJ3(StelaEquinoctialOrbit orbit) Compute the effect of the 3rd degree development of the Zonal Perturbation
double[]	StelaZonalAttraction.computeJ3(StelaEquinoctialOrbit orbit, double mu) Compute the effect of the 3rd degree development of the Zonal Perturbation with specific mu
double[][]	StelaZonalAttraction.computeJ3PartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives due to J3 Potential effect
double[]	StelaZonalAttraction.computeJ4(StelaEquinoctialOrbit orbit) Compute the effect of the 4th degree development of the Zonal Perturbation
double[][]	StelaZonalAttraction.computeJ4PartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives due to J4 Potential effect
double[]	StelaZonalAttraction.computeJ5(StelaEquinoctialOrbit orbit) Compute the effect of the 5th degree development of the Zonal Perturbation
double[][]	StelaZonalAttraction.computeJ5PartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives due to J5 Potential effect
double[]	StelaZonalAttraction.computeJ6(StelaEquinoctialOrbit orbit) Compute the effect of the 6th degree development of the Zonal Perturbation
double[][]	StelaZonalAttraction.computeJ6PartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives due to J6 Potential effect
double[]	StelaZonalAttraction.computeJ7(StelaEquinoctialOrbit orbit) Compute the effect of the 7th degree development of the Zonal Perturbation
double[][]	StelaZonalAttraction.computeJ7PartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives due to J7 Potential effect
double[]	StelaZonalAttraction.computeJ8(StelaEquinoctialOrbit orbit) Compute the effect of the 8th degree development of the Zonal Perturbation
double[]	StelaZonalAttraction.computeJ9(StelaEquinoctialOrbit orbit) Compute the effect of the 9th degree development of the Zonal Perturbation
double[][]	SolidTidesAcc.computePartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives for a given spacecraft state.
double[][]	StelaTesseralAttraction.computePartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives for a given spacecraft state.
double[][]	StelaZonalAttraction.computePartialDerivatives(StelaEquinoctialOrbit orbit)
double[][]	StelaThirdBodyAttraction.computePartialDerivatives(StelaEquinoctialOrbit orbit)
double[]	SolidTidesAcc.computePerturbation(StelaEquinoctialOrbit orbit) Compute the dE/dt force derivatives for a given spacecraft state.
double[]	StelaTesseralAttraction.computePerturbation(StelaEquinoctialOrbit orbit) Compute the dE/dt force derivatives for a given spacecraft state.
double[]	StelaZonalAttraction.computePerturbation(StelaEquinoctialOrbit orbit)
double[]	StelaThirdBodyAttraction.computePerturbation(StelaEquinoctialOrbit orbit)
double[]	SolidTidesAcc.computeShortPeriods(StelaEquinoctialOrbit orbit) Compute the short periodic variations for a given spacecraft state.
double[]	StelaTesseralAttraction.computeShortPeriods(StelaEquinoctialOrbit orbit) Compute the short periodic variations for a given spacecraft state.
double[]	StelaZonalAttraction.computeShortPeriods(StelaEquinoctialOrbit orbit)
double[]	StelaThirdBodyAttraction.computeShortPeriods(StelaEquinoctialOrbit orbit)

Uses of StelaEquinoctialOrbit in fr.cnes.sirius.patrius.stela.forces.noninertial

Methods in fr.cnes.sirius.patrius.stela.forces.noninertial with parameters of type StelaEquinoctialOrbit

double[][]	NonInertialContribution.computePartialDerivatives(StelaEquinoctialOrbit orbit)
double[]	NonInertialContribution.computePerturbation(StelaEquinoctialOrbit orbit, OrbitNatureConverter converter)
double[]	NonInertialContribution.computeShortPeriods(StelaEquinoctialOrbit orbit)

Uses of StelaEquinoctialOrbit in fr.cnes.sirius.patrius.stela.forces.radiation

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

Vector3D	SRPSquaring.computeAcceleration(StelaEquinoctialOrbit orbit, PVCoordinates satSunVector) Compute the acceleration due to the force.
protected double[]	SRPSquaring.computeInOutTrueAnom(StelaEquinoctialOrbit orbit, PVCoordinates sunPV) Computation of in and out true anomalies of the shadowed part of the orbit.
double[][]	SRPPotential.computePartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives for a given spacecraft state.
double[][]	SRPSquaring.computePartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives for a given spacecraft state.
double[][]	StelaSRPSquaring.computePartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives for a given spacecraft state.
double[]	SRPPotential.computePerturbation(StelaEquinoctialOrbit orbit) Compute the dE/dt force derivatives for a given spacecraft state.
double[]	SRPSquaring.computePerturbation(StelaEquinoctialOrbit orbit, OrbitNatureConverter converter) Compute the dE/dt force derivatives for a given spacecraft state.
double[]	StelaSRPSquaring.computePerturbation(StelaEquinoctialOrbit orbit, OrbitNatureConverter converter) Compute the dE/dt force derivatives for a given spacecraft state.
double[]	StelaSRPSquaring.computePotentialPerturbation(StelaEquinoctialOrbit orbit)
double[]	SRPPotential.computeShortPeriods(StelaEquinoctialOrbit orbit) Compute the short periodic variations for a given spacecraft state.
double[]	SRPSquaring.computeShortPeriods(StelaEquinoctialOrbit orbit) Compute the short periodic variations for a given spacecraft state.
double[]	StelaSRPSquaring.computeShortPeriods(StelaEquinoctialOrbit orbit) Compute the short periodic variations for a given spacecraft state.
protected double[]	SRPSquaring.computeSunBetaPhi(StelaEquinoctialOrbit orbit, PVCoordinates sunPV) Computation of Sun's right ascension (φ) and declination (β) wrt the orbit plane.

Uses of StelaEquinoctialOrbit in fr.cnes.sirius.patrius.stela.orbits

Methods in fr.cnes.sirius.patrius.stela.orbits that return StelaEquinoctialOrbit

StelaEquinoctialOrbit	OrbitNatureConverter.toMean(StelaEquinoctialOrbit oscOrbit) Converts an osculating StelaEquinoctialOrbit to a mean one.
StelaEquinoctialOrbit	OrbitNatureConverter.toOsculating(StelaEquinoctialOrbit meanOrbit) Converts a mean StelaEquinoctialOrbit to an osculating one.

Methods in fr.cnes.sirius.patrius.stela.orbits with parameters of type StelaEquinoctialOrbit

static double[][]	JacobianConverter.computeEquinoctialToCartesianJacobian(StelaEquinoctialOrbit orbit) Computes Jacobian matrix from equinoctial to cartesian.
StelaEquinoctialOrbit	OrbitNatureConverter.toMean(StelaEquinoctialOrbit oscOrbit) Converts an osculating StelaEquinoctialOrbit to a mean one.
StelaEquinoctialOrbit	OrbitNatureConverter.toOsculating(StelaEquinoctialOrbit meanOrbit) Converts a mean StelaEquinoctialOrbit to an osculating one.

Uses of StelaEquinoctialOrbit in fr.cnes.sirius.patrius.stela.propagation

Methods in fr.cnes.sirius.patrius.stela.propagation with parameters of type StelaEquinoctialOrbit

void	StelaPartialDerivativesEquations.computeDerivatives(StelaEquinoctialOrbit orbit, double[] p, double[] pDot)
void	StelaAdditionalEquations.computeDerivatives(StelaEquinoctialOrbit o, double[] p, double[] pDot) Compute the derivatives related to the additional state parameters.