133 lines
1.8 KiB
C++
133 lines
1.8 KiB
C++
#ifndef ORBITALELEMENTS_H_
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#define ORBITALELEMENTS_H_
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#include "Util.h"
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#include "DateTime.h"
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class Tle;
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/**
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* @brief The extracted orbital elements used by the SGP4 propagator.
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*/
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class OrbitalElements
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{
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public:
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OrbitalElements(const Tle& tle);
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virtual ~OrbitalElements()
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{
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}
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/*
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* XMO
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*/
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double MeanAnomoly() const
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{
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return mean_anomoly_;
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}
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/*
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* XNODEO
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*/
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double AscendingNode() const
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{
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return ascending_node_;
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}
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/*
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* OMEGAO
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*/
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double ArgumentPerigee() const
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{
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return argument_perigee_;
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}
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/*
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* EO
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*/
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double Eccentricity() const
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{
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return eccentricity_;
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}
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/*
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* XINCL
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*/
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double Inclination() const
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{
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return inclination_;
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}
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/*
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* XNO
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*/
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double MeanMotion() const
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{
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return mean_motion_;
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}
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/*
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* BSTAR
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*/
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double BStar() const
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{
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return bstar_;
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}
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/*
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* AODP
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*/
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double RecoveredSemiMajorAxis() const
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{
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return recovered_semi_major_axis_;
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}
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/*
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* XNODP
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*/
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double RecoveredMeanMotion() const
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{
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return recovered_mean_motion_;
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}
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/*
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* PERIGE
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*/
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double Perigee() const
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{
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return perigee_;
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}
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/*
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* Period in minutes
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*/
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double Period() const
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{
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return period_;
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}
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/*
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* EPOCH
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*/
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DateTime Epoch() const
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{
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return epoch_;
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}
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private:
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double mean_anomoly_;
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double ascending_node_;
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double argument_perigee_;
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double eccentricity_;
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double inclination_;
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double mean_motion_;
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double bstar_;
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double recovered_semi_major_axis_;
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double recovered_mean_motion_;
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double perigee_;
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double period_;
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DateTime epoch_;
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};
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#endif
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