Package org.orekit.gnss.attitude

Class GPSBlockIIR

java.lang.Object

org.orekit.gnss.attitude.GPSBlockIIR

All Implemented Interfaces:

AttitudeProvider, GNSSAttitudeProvider, EventDetectorsProvider

public class GPSBlockIIR
extends Object

Attitude providers for GPS block IIR navigation satellites.

This class is based on the May 2017 version of J. Kouba eclips.f subroutine available at IGS Analysis Center Coordinator site. The eclips.f code itself is not used ; its hard-coded data are used and its low level models are used, but the structure of the code and the API have been completely rewritten.

Since:

9.2

Author:

J. Kouba original fortran routine, Luc Maisonobe Java translation

Field Summary

Fields

Modifier and Type	Field	Description
static double	DEFAULT_YAW_RATE	Default yaw rates for all spacecrafts in radians per seconds.

Fields inherited from interface org.orekit.propagation.events.EventDetectorsProvider

DATATION_ACCURACY

Constructor Summary

Constructors

Constructor	Description
GPSBlockIIR(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.

Method Summary

Modifier and Type	Method	Description
protected TimeStampedAngularCoordinates	correctedYaw(org.orekit.gnss.attitude.GNSSAttitudeContext context)	Select the /** Compute GNSS attitude with midnight/noon yaw turn correction.
protected <T extends CalculusFieldElement<T>> TimeStampedFieldAngularCoordinates<T>	correctedYaw(org.orekit.gnss.attitude.GNSSFieldAttitudeContext<T> context)	Compute GNSS attitude with midnight/noon yaw turn correction.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
protected Frame	getInertialFrame()	Get inertial frame where velocity are computed.
protected ExtendedPositionProvider	getSun()	Get provider for Sun position.
AbsoluteDate	validityEnd()	Get end of validity for this provider.
AbsoluteDate	validityStart()	Get start of validity for this provider.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from interface org.orekit.attitudes.AttitudeProvider

getAttitudeRotation, getAttitudeRotation, getEventDetectors, getFieldEventDetectors

Methods inherited from interface org.orekit.propagation.events.EventDetectorsProvider

getEventDetectors, getFieldEventDetectors

Field Detail

DEFAULT_YAW_RATE

public static final double DEFAULT_YAW_RATE

Default yaw rates for all spacecrafts in radians per seconds.

Constructor Detail

GPSBlockIIR

public GPSBlockIIR(double yawRate,
                   AbsoluteDate validityStart,
                   AbsoluteDate validityEnd,
                   ExtendedPositionProvider sun,
                   Frame inertialFrame)

Simple constructor.

Parameters:

yawRate - yaw rate to use in radians per seconds (typically DEFAULT_YAW_RATE)

validityStart - start of validity for this provider

validityEnd - end of validity for this provider

sun - provider for Sun position

inertialFrame - inertial frame where velocity are computed

Method Detail

correctedYaw

protected TimeStampedAngularCoordinates correctedYaw(org.orekit.gnss.attitude.GNSSAttitudeContext context)

Select the /** Compute GNSS attitude with midnight/noon yaw turn correction.

Parameters:

context - context data for attitude computation

Returns:

corrected yaw, using inertial frame as the reference

correctedYaw

protected <T extends CalculusFieldElement<T>> TimeStampedFieldAngularCoordinates<T> correctedYaw(org.orekit.gnss.attitude.GNSSFieldAttitudeContext<T> context)

Compute GNSS attitude with midnight/noon yaw turn correction.

Type Parameters:

T - type of the field elements

Parameters:

context - context data for attitude computation

Returns:

corrected yaw, using inertial frame as the reference

validityStart

public AbsoluteDate validityStart()

Get start of validity for this provider.

Specified by:

validityStart in interface GNSSAttitudeProvider

Returns:

start of validity for this provider

validityEnd

public AbsoluteDate validityEnd()

Get end of validity for this provider.

Specified by:

validityEnd in interface GNSSAttitudeProvider

Returns:

end of validity for this provider

getAttitude

public Attitude getAttitude(PVCoordinatesProvider pvProv,
                            AbsoluteDate date,
                            Frame frame)

Compute the attitude corresponding to an orbital state.

Specified by:

getAttitude in interface AttitudeProvider

Parameters:

pvProv - local position-velocity provider around current date

date - current date

frame - reference frame from which attitude is computed

Returns:

attitude on the specified date and position-velocity state

getAttitude

public <T extends CalculusFieldElement<T>> FieldAttitude<T> getAttitude(FieldPVCoordinatesProvider<T> pvProv,
                                                                        FieldAbsoluteDate<T> date,
                                                                        Frame frame)

Compute the attitude corresponding to an orbital state.

Specified by:

getAttitude in interface AttitudeProvider

Type Parameters:

T - type of the field elements

Parameters:

pvProv - local position-velocity provider around current date

date - current date

frame - reference frame from which attitude is computed

Returns:

attitude on the specified date and position-velocity state

getSun

protected ExtendedPositionProvider getSun()

Get provider for Sun position.

Returns:

provider for Sun position

Since:

12.0

getInertialFrame

protected Frame getInertialFrame()

Get inertial frame where velocity are computed.

Returns:

inertial frame where velocity are computed