101 lines
3.1 KiB
C
101 lines
3.1 KiB
C
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#ifndef ORIBTMODELOPERATOR_H_
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#define ORIBTMODELOPERATOR_H_
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#include <QFile>
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#include <QDomDocument>
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#include <QVector3D>
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#include <QDebug>
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#include <QList>
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#include <Eigen/Core>
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#include <Eigen/Dense>
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#include "BaseConstVariable.h"
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QList<SatellitePos> loadNodesFromXml(const QString& filename);
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void saveNodesToXml(const QString& filename, const QList<SatellitePos>& inposes);
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class OrbitModelAbstract {
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public:
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OrbitModelAbstract();
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~OrbitModelAbstract();
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public:
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virtual SatellitePos predictNode(double time) ;
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};
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class OrbitElements {
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public:
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double semiMajorAxis; // <20>볤<EFBFBD><EBB3A4> (a)
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double eccentricity; // <20><><EFBFBD><EFBFBD><EFBFBD><EFBFBD> (e)
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double inclination; // <20><>б<EFBFBD><D0B1> (i)
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double longitudeOfAscendingNode; // <20><><EFBFBD><EFBFBD><EFBFBD><EFBFBD><EFBFBD>ྭ (<28><>)
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double argumentOfPeriapsis; // <20><><EFBFBD>ص<EFBFBD><D8B5><EFBFBD><EFBFBD><EFBFBD> (<28><>)
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double trueAnomaly; // <20><><EFBFBD><EFBFBD><EFBFBD><EFBFBD><EFBFBD><EFBFBD> (<28><>)
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OrbitElements();
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};
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class OrbitEstimator :public OrbitModelAbstract {
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public:
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OrbitEstimator();
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void estimateOrbit(const SatellitePos& node);
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void saveToXml(const QString& filename) const;
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bool loadFromXml(const QString& filename);
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SatellitePos calculateNode(double time) const;
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virtual SatellitePos predictNode(double time) override;
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private:
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OrbitElements elements;
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OrbitElements estimateKeplerianElements(const SatellitePos& node);
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SatellitePos calculateKeplerianNode(const OrbitElements& elements, double time) const;
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double solveKeplerEquation(double M, double e) const;
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};
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class PolynomialOrbitModel :public OrbitModelAbstract {
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public:
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void fitPolynomial(const QList<SatellitePos>& nodes, int degree=3);
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SatellitePos predictPosition(double time);
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void saveToXml(const QString& filename) const;
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bool loadFromXml(const QString& filename);
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virtual SatellitePos predictNode(double time) override;
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private:
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Eigen::VectorXd coefficientsX;
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Eigen::VectorXd coefficientsY;
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Eigen::VectorXd coefficientsZ;
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Eigen::VectorXd coefficientsVx;
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Eigen::VectorXd coefficientsVy;
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Eigen::VectorXd coefficientsVz;
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Eigen::VectorXd leastSquaresFit(const QList<double>& x, const QList<double>& y, int degree);
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void saveCoefficientsToXml(QDomElement& parent, const Eigen::VectorXd& coefficients, const QString& tagName) const;
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bool loadCoefficientsFromXml(const QDomElement& parent, Eigen::VectorXd& coefficients, const QString& tagName);
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};
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class TwoLineElements :public OrbitModelAbstract {
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public:
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TwoLineElements();
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bool loadFromTleFile(const QString& filename);
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SatellitePos calculateNode(double time) const;
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virtual SatellitePos predictNode(double time) override;
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private:
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std::string line1;
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std::string line2;
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void parseTleLines();
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double meanMotion() const;
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double semiMajorAxis() const;
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double eccentricity() const;
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double inclination() const;
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double longitudeOfAscendingNode() const;
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double argumentOfPeriapsis() const;
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double meanAnomaly() const;
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double revolutionNumberAtEpoch() const;
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double epochTime() const;
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double solveKeplerEquation(double M, double e) const;
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SatellitePos calculateKeplerianNode(double time) const;
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};
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#endif
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