SBASOrbitalElements.java
/* Copyright 2002-2022 CS GROUP
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* contributor license agreements. See the NOTICE file distributed with
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* CS licenses this file to You under the Apache License, Version 2.0
* (the "License"); you may not use this file except in compliance with
* the License. You may obtain a copy of the License at
*
* http://www.apache.org/licenses/LICENSE-2.0
*
* Unless required by applicable law or agreed to in writing, software
* distributed under the License is distributed on an "AS IS" BASIS,
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package org.orekit.propagation.analytical.gnss.data;
import org.orekit.propagation.analytical.gnss.SBASPropagator;
import org.orekit.time.TimeStamped;
/** This interface provides the minimal set of orbital elements needed by the {@link SBASPropagator}.
*
* @author Bryan Cazabonne
* @since 10.1
*
*/
public interface SBASOrbitalElements extends TimeStamped {
/**
* Gets the PRN number of the SBAS satellite.
*
* @return the PRN number of the SBAS satellite
*/
int getPRN();
/**
* Gets the Reference Week of the SBAS orbit.
*
* @return the Reference Week of the SBAS orbit
*/
int getWeek();
/**
* Gets the Reference Time of the SBAS orbit in GPS seconds of the week.
*
* @return the Reference Time of the SBAS orbit (s)
*/
double getTime();
/**
* Get the ECEF-X component of satellite coordinates.
*
* @return the ECEF-X component of satellite coordinates (m)
*/
double getX();
/**
* Get the ECEF-X component of satellite velocity vector.
*
* @return the the ECEF-X component of satellite velocity vector (m/s)
*/
double getXDot();
/**
* Get the ECEF-X component of satellite acceleration vector.
*
* @return the GLONASS ECEF-X component of satellite acceleration vector (m/s²)
*/
double getXDotDot();
/**
* Get the ECEF-Y component of satellite coordinates.
*
* @return the ECEF-Y component of satellite coordinates (m)
*/
double getY();
/**
* Get the ECEF-Y component of satellite velocity vector.
*
* @return the ECEF-Y component of satellite velocity vector (m/s)
*/
double getYDot();
/**
* Get the ECEF-Y component of satellite acceleration vector.
*
* @return the ECEF-Y component of satellite acceleration vector (m/s²)
*/
double getYDotDot();
/**
* Get the ECEF-Z component of satellite coordinates.
*
* @return the ECEF-Z component of satellite coordinates (m)
*/
double getZ();
/**
* Get the ECEF-Z component of satellite velocity vector.
*
* @return the the ECEF-Z component of satellite velocity vector (m/s)
*/
double getZDot();
/**
* Get the ECEF-Z component of satellite acceleration vector.
*
* @return the ECEF-Z component of satellite acceleration vector (m/s²)
*/
double getZDotDot();
/**
* Gets the Issue Of Data Navigation (IODN).
*
* @return the IODN
*/
default int getIODN() {
return 0;
}
/**
* Gets the Zeroth Order Clock Correction.
*
* @return the Zeroth Order Clock Correction (s)
*/
default double getAGf0() {
return 0.0;
}
/**
* Gets the First Order Clock Correction.
*
* @return the First Order Clock Correction (s/s)
*/
default double getAGf1() {
return 0.0;
}
/**
* Gets the clock correction reference time toc.
*
* @return the clock correction reference time (s)
*/
default double getToc() {
return 0.0;
}
}