Package org.orekit.files.ccsds.ndm.cdm
Class AdditionalParameters
- java.lang.Object
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- org.orekit.files.ccsds.section.CommentsContainer
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- org.orekit.files.ccsds.ndm.CommonPhysicalProperties
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- org.orekit.files.ccsds.ndm.cdm.AdditionalParameters
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- All Implemented Interfaces:
Section
public class AdditionalParameters extends CommonPhysicalProperties
Container for additional parameters data block.- Since:
- 11.2
- Author:
- Melina Vanel
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Constructor Summary
Constructors Constructor Description AdditionalParameters()
Simple constructor.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description double
getApoapsisAltitude()
Get the distance of the furthest point in the objects orbit above the equatorial radius of the central body.double
getAreaDRG()
Get the effective area of the object exposed to atmospheric drag.double
getAreaPC()
Get the actual area of the object.double
getAreaPCMax()
Get the maximum area of the object to be used to compute the collision probability.double
getAreaPCMin()
Set the minimum area of the object to be used to compute the collision probability.double
getAreaSRP()
Get the effective area of the object exposed to solar radiation pressure.double
getCDAreaOverMass()
Get the object’s Cd x A/m used to propagate the state vector and covariance to TCA.double
getCovConfidence()
Get the measure of the confidence in the covariance errors matching reality.String
getCovConfidenceMethod()
Get the method used for the calculation of COV_CONFIDENCE.double
getCRAreaOverMass()
Get the object’s Cr x A/m used to propagate the state vector and covariance to TCA.double
getHbr()
Get the object hard body radius.double
getInclination()
Get the angle between the objects orbit plane and the orbit centers equatorial plane.double
getMass()
Get the mass of the object.double
getPeriapsisAltitude()
Get the distance of the closest point in the objects orbit above the equatorial radius of the central body.double
getSedr()
Get the amount of energy being removed from the object’s orbit by atmospheric drag.double
getThrustAcceleration()
Get the object’s acceleration due to in-track thrust used to propagate the state vector and covariance to TCA.void
setApoapsisAltitude(double apoapsisAltitude)
Set the distance of the furthest point in the objects orbit above the equatorial radius of the central body.void
setAreaDRG(double areaDRG)
Set the effective area of the object exposed to atmospheric drag.void
setAreaPC(double areaPC)
Set the actual area of the object.void
setAreaPCMax(double areaPCMax)
Set the maximum area for the object to be used to compute the collision probability.void
setAreaPCMin(double areaPCMin)
Get the minimum area of the object to be used to compute the collision probability.void
setAreaSRP(double areaSRP)
Set the effective area of the object exposed to solar radiation pressure.void
setCDAreaOverMass(double CDAreaOverMass)
Set the object’s Cd x A/m used to propagate the state vector and covariance to TCA.void
setCovConfidence(double covConfidence)
Set the measure of the confidence in the covariance errors matching reality.void
setCovConfidenceMethod(String covConfidenceMethod)
Set the method used for the calculation of COV_CONFIDENCE.void
setCRAreaOverMass(double CRAreaOverMass)
Set the object’s Cr x A/m used to propagate the state vector and covariance to TCA.void
setHbr(double hbr)
Set the object hard body radius.void
setInclination(double inclination)
Set the angle between the objects orbit plane and the orbit centers equatorial plane.void
setMass(double mass)
Set the mass of the object.void
setPeriapsisAltitude(double periapsisAltitude)
Set the distance of the closest point in the objects orbit above the equatorial radius of the central body.void
setSedr(double SEDR)
Set the amount of energy being removed from the object’s orbit by atmospheric drag.void
setThrustAcceleration(double thrustAcceleration)
Set the object’s acceleration due to in-track thrust used to propagate the state vector and covariance to TCA.void
validate(double version)
Check is all mandatory entries have been initialized.-
Methods inherited from class org.orekit.files.ccsds.ndm.CommonPhysicalProperties
getMaxRcs, getMinRcs, getOebAreaAlongIntermediate, getOebAreaAlongMax, getOebAreaAlongMin, getOebIntermediate, getOebMax, getOebMin, getOebParentFrame, getOebParentFrameEpoch, getOebQ, getRcs, getReflectance, getVmAbsolute, getVmApparent, getVmApparentMax, getVmApparentMin, setMaxRcs, setMinRcs, setOebAreaAlongIntermediate, setOebAreaAlongMax, setOebAreaAlongMin, setOebIntermediate, setOebMax, setOebMin, setOebParentFrame, setOebParentFrameEpoch, setOebQ, setRcs, setReflectance, setVmAbsolute, setVmApparent, setVmApparentMax, setVmApparentMin
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Methods inherited from class org.orekit.files.ccsds.section.CommentsContainer
acceptComments, addComment, checkAllowed, checkNotNaN, checkNotNegative, checkNotNull, getComments, refuseFurtherComments, setComments
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Method Detail
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validate
public void validate(double version)
Check is all mandatory entries have been initialized.This method should throw an exception if some mandatory entries are missing or not compatible with version number.
- Specified by:
validate
in interfaceSection
- Overrides:
validate
in classCommonPhysicalProperties
- Parameters:
version
- format version
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getAreaPC
public double getAreaPC()
Get the actual area of the object.- Returns:
- the object area (in m²)
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setAreaPC
public void setAreaPC(double areaPC)
Set the actual area of the object.- Parameters:
areaPC
- area (in m²) value to be set
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getAreaDRG
public double getAreaDRG()
Get the effective area of the object exposed to atmospheric drag.- Returns:
- the object area (in m²) exposed to atmospheric drag
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setAreaDRG
public void setAreaDRG(double areaDRG)
Set the effective area of the object exposed to atmospheric drag.- Parameters:
areaDRG
- area (in m²) value to be set
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getAreaSRP
public double getAreaSRP()
Get the effective area of the object exposed to solar radiation pressure.- Returns:
- the object area (in m²) exposed to solar radiation pressure
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setAreaSRP
public void setAreaSRP(double areaSRP)
Set the effective area of the object exposed to solar radiation pressure.- Parameters:
areaSRP
- area (in m²) to be set
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getMass
public double getMass()
Get the mass of the object.- Returns:
- the mass (in kg) of the object
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setMass
public void setMass(double mass)
Set the mass of the object.- Parameters:
mass
- mass (in kg) of the object to be set
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getCDAreaOverMass
public double getCDAreaOverMass()
Get the object’s Cd x A/m used to propagate the state vector and covariance to TCA.- Returns:
- the object’s Cd x A/m (in m²/kg)
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setCDAreaOverMass
public void setCDAreaOverMass(double CDAreaOverMass)
Set the object’s Cd x A/m used to propagate the state vector and covariance to TCA.- Parameters:
CDAreaOverMass
- object’s Cd x A/m (in m²/kg) value to be set
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getCRAreaOverMass
public double getCRAreaOverMass()
Get the object’s Cr x A/m used to propagate the state vector and covariance to TCA.- Returns:
- the object’s Cr x A/m (in m²/kg)
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setCRAreaOverMass
public void setCRAreaOverMass(double CRAreaOverMass)
Set the object’s Cr x A/m used to propagate the state vector and covariance to TCA.- Parameters:
CRAreaOverMass
- object’s Cr x A/m (in m²/kg) value to be set
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getThrustAcceleration
public double getThrustAcceleration()
Get the object’s acceleration due to in-track thrust used to propagate the state vector and covariance to TCA.- Returns:
- the object’s acceleration (in m/s²) due to in-track thrust
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setThrustAcceleration
public void setThrustAcceleration(double thrustAcceleration)
Set the object’s acceleration due to in-track thrust used to propagate the state vector and covariance to TCA.- Parameters:
thrustAcceleration
- object’s acceleration (in m/s²) due to in-track thrust
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getSedr
public double getSedr()
Get the amount of energy being removed from the object’s orbit by atmospheric drag. This value is an average calculated during the OD. SEDR = Specific Energy Dissipation Rate.- Returns:
- the amount of energy (in W/kg) being removed from the object’s orbit by atmospheric drag
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setSedr
public void setSedr(double SEDR)
Set the amount of energy being removed from the object’s orbit by atmospheric drag. This value is an average calculated during the OD. SEDR = Specific Energy Dissipation Rate.- Parameters:
SEDR
- amount of energy (in W/kg) being removed from the object’s orbit by atmospheric drag
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getAreaPCMin
public double getAreaPCMin()
Set the minimum area of the object to be used to compute the collision probability.- Returns:
- the areaPCMin
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setAreaPCMin
public void setAreaPCMin(double areaPCMin)
Get the minimum area of the object to be used to compute the collision probability.- Parameters:
areaPCMin
- the areaPCMin to set
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getAreaPCMax
public double getAreaPCMax()
Get the maximum area of the object to be used to compute the collision probability.- Returns:
- the areaPCMax
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setAreaPCMax
public void setAreaPCMax(double areaPCMax)
Set the maximum area for the object to be used to compute the collision probability.- Parameters:
areaPCMax
- the areaPCMax to set
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getHbr
public double getHbr()
Get the object hard body radius.- Returns:
- the object hard body radius.
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setHbr
public void setHbr(double hbr)
Set the object hard body radius.- Parameters:
hbr
- the object hard body radius.
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getApoapsisAltitude
public double getApoapsisAltitude()
Get the distance of the furthest point in the objects orbit above the equatorial radius of the central body.- Returns:
- the apoapsisAltitude
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setApoapsisAltitude
public void setApoapsisAltitude(double apoapsisAltitude)
Set the distance of the furthest point in the objects orbit above the equatorial radius of the central body.- Parameters:
apoapsisAltitude
- the apoapsisHeight to set
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getPeriapsisAltitude
public double getPeriapsisAltitude()
Get the distance of the closest point in the objects orbit above the equatorial radius of the central body.- Returns:
- the periapsissAltitude
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setPeriapsisAltitude
public void setPeriapsisAltitude(double periapsisAltitude)
Set the distance of the closest point in the objects orbit above the equatorial radius of the central body.- Parameters:
periapsisAltitude
- the periapsissHeight to set
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getInclination
public double getInclination()
Get the angle between the objects orbit plane and the orbit centers equatorial plane.- Returns:
- the inclination
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setInclination
public void setInclination(double inclination)
Set the angle between the objects orbit plane and the orbit centers equatorial plane.- Parameters:
inclination
- the inclination to set
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getCovConfidence
public double getCovConfidence()
Get the measure of the confidence in the covariance errors matching reality.- Returns:
- the covConfidence
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setCovConfidence
public void setCovConfidence(double covConfidence)
Set the measure of the confidence in the covariance errors matching reality.- Parameters:
covConfidence
- the covConfidence to set
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getCovConfidenceMethod
public String getCovConfidenceMethod()
Get the method used for the calculation of COV_CONFIDENCE.- Returns:
- the covConfidenceMethod
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setCovConfidenceMethod
public void setCovConfidenceMethod(String covConfidenceMethod)
Set the method used for the calculation of COV_CONFIDENCE.- Parameters:
covConfidenceMethod
- the covConfidenceMethod to set
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