public class EquatorialParameters extends AbstractOrbitalParameters
The parameters used internally are the following elements:
a semi-major axis (m) e eccentricity pomega = ω + Ω , longitude of the periapsis; ix = 2 sin(i/2) cos(Ω), first component of inclination vector iy = 2 sin(i/2) sin(Ω), second component of inclination vector anomaly (M or E or v);, mean, eccentric or true anomaly (rad)where ω stands for the Periapsis Argument, Ω stands for the Right Ascension of the Ascending Node.
When orbit is either equatorial or circular, some keplerian elements (more precisely ω and Ω) become
ambiguous so this class should not be used for such orbits. For this reason, equinoctial
parameters
is the recommended way to represent orbits.
Constructor and Description |
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EquatorialParameters(double aIn,
double eIn,
double pomegaIn,
double ixIn,
double iyIn,
double anomaly,
PositionAngle type,
double mu)
Creates a new instance.
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Modifier and Type | Method and Description |
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boolean |
equals(Object object)
Test for the equality of two orbits.
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double |
getA()
Get the semi-major axis.
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AlternateEquinoctialParameters |
getAlternateEquinoctialParameters()
Convert current orbital parameters into alternate equinoctial parameters.
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double |
getAnomaly(PositionAngle type)
Get the anomaly.
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ApsisAltitudeParameters |
getApsisAltitudeParameters(double ae)
Convert current orbital parameters into apsis (using altitude) parameters.
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ApsisRadiusParameters |
getApsisRadiusParameters()
Convert current orbital parameters into apsis (using radius) parameters.
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CartesianParameters |
getCartesianParameters()
Convert current orbital parameters into cartesian parameters.
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CircularParameters |
getCircularParameters()
Convert current orbital parameters into circular parameters.
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double |
getE()
Get the eccentricity.
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double |
getEccentricAnomaly()
Get the eccentric anomaly.
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EquatorialParameters |
getEquatorialParameters()
Convert current orbital parameters into equatorial parameters.
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EquinoctialParameters |
getEquinoctialParameters()
Convert current orbital parameters into equinoctial parameters.
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double |
getIx()
Get the first component of the inclination vector.
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double |
getIy()
Get the second component of the inclination vector.
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KeplerianParameters |
getKeplerianParameters()
Convert current orbital parameters into Keplerian parameters.
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double |
getMeanAnomaly()
Get the mean anomaly.
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double |
getPomega()
Get the longitude of the periapsis (ω + Ω).
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ReentryParameters |
getReentryParameters(double ae,
double f)
Convert current orbital parameters into reentry parameters.
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StelaEquinoctialParameters |
getStelaEquinoctialParameters()
Convert current orbital parameters into Stela equinoctial parameters.
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double |
getTrueAnomaly()
Get the true anomaly.
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int |
hashCode()
Get a hashCode for the orbit.
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String |
toString()
Returns a string representation of this non circular equatorial
orbital parameters object.
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getMu
public EquatorialParameters(double aIn, double eIn, double pomegaIn, double ixIn, double iyIn, double anomaly, PositionAngle type, double mu)
aIn
- semi-major axis (m)eIn
- eccentricitypomegaIn
- ω + Ω (rad)ixIn
- 2 sin(i/2) cos(Ω), first component of inclination vectoriyIn
- 2 sin(i/2) sin(Ω), second component of inclination vectoranomaly
- (M or E or v) = anomaly mean, eccentric or true anomaly (rad)type
- type of anomalymu
- central attraction coefficient (m3/s2)IllegalArgumentException
- if orbit is hyperbolicIllegalArgumentException
- if orbit mismatch with conic typeIllegalArgumentException
- if inclination vector is not valid, meaning ix^2 + iy^2 > 4public double getA()
public double getE()
public double getIx()
public double getIy()
public double getPomega()
public double getAnomaly(PositionAngle type)
type
- type of the anglepublic double getTrueAnomaly()
public double getMeanAnomaly()
public double getEccentricAnomaly()
public CartesianParameters getCartesianParameters()
CartesianParameters
public KeplerianParameters getKeplerianParameters()
KeplerianParameters
public CircularParameters getCircularParameters()
CircularParameters
public EquatorialParameters getEquatorialParameters()
EquatorialParameters
public EquinoctialParameters getEquinoctialParameters()
EquinoctialParameters
public ApsisAltitudeParameters getApsisAltitudeParameters(double ae)
ae
- equatorial radius (m)ApsisAltitudeParameters
public ApsisRadiusParameters getApsisRadiusParameters()
ApsisRadiusParameters
public ReentryParameters getReentryParameters(double ae, double f)
ae
- equatorial radius (m)f
- flattening (f = (a-b)/a)ReentryParameters
public StelaEquinoctialParameters getStelaEquinoctialParameters()
StelaEquinoctialParameters
public AlternateEquinoctialParameters getAlternateEquinoctialParameters()
AlternateEquinoctialParameters
public String toString()
public boolean equals(Object object)
Orbits are considered equals if they have the same type and all their attributes are equals. In particular, the orbits frame are considered equals if they represent the same instance. If they have the same attributes but are not the same instance, the method will return false.
equals
in interface IOrbitalParameters
equals
in class Object
object
- Object to test for equality to thispublic int hashCode()
hashCode
in interface IOrbitalParameters
hashCode
in class Object
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