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dep / spacecraft / src / orbit / orbitstaterep

Keplerian.h File Reference

Detailed Description

Implementation of the Keplerian Orbit State Representation Class.

Author:
Author
jayhawk_hokie
Version:
Revision
1.6
Date:
Date
2007/05/21 17:25:29

Definition in file Keplerian.h.

#include <matrix/Matrix.h>
#include <orbit/orbitstaterep/OrbitStateRepresentation.h>
#include <string>
#include <stdlib.h>
#include <sstream>
#include <math.h>

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Namespaces

namespace  O_SESSAME

Classes

struct  O_SESSAME::tleStruct
class  O_SESSAME::Keplerian
 Keplerian orbital element representation of the orbital position. More...

Defines

#define MU   3.986012e5
#define Re   6378.145
#define J2   0.00108263
#define EARTH_ANGULAR_RATE   7.292115856e-5
#define PI   M_PI
#define NUM_KEPLERIAN_ELEMENTS   6
#define NUM_KEPLERIAN_PARAMETERS   7

Variables

const int SEMIMAJOR_AXIS = VectorIndexBase + 0
const int ECCENTRICITY = VectorIndexBase + 1
const int INCLINATION = VectorIndexBase + 2
const int LONG_ASC_NODE = VectorIndexBase + 3
const int ARG_PERIGEE = VectorIndexBase + 4
const int TRUE_ANOMALY = VectorIndexBase + 5
const int ECCENTRIC_ANOMALY = VectorIndexBase + 0
const int ECCENTRIC_ANOMALY_0 = VectorIndexBase + 1
const int MEAN_ANOMALY = VectorIndexBase + 2
const int MEAN_ANOMALY_0 = VectorIndexBase + 3
const int ARG_LATTITUDE = VectorIndexBase + 4
const int LONG_PERIGEE = VectorIndexBase + 5
const int TRUE_LONGITUDE = VectorIndexBase + 6

Define Documentation

#define EARTH_ANGULAR_RATE   7.292115856e-5
 

Definition at line 26 of file Keplerian.h.

#define J2   0.00108263
 

Definition at line 25 of file Keplerian.h.

Referenced by O_SESSAME::OsculatingOrbitalElements::MeanToOsculating(), and O_SESSAME::OsculatingOrbitalElements::OsculatingToMean().

#define MU   3.986012e5
 

Definition at line 23 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetMeanMotion(), O_SESSAME::Keplerian::GetPositionVelocityPQW(), O_SESSAME::Keplerian::ReadTwoLineElementSet(), and O_SESSAME::Keplerian::SetPositionVelocity().

#define NUM_KEPLERIAN_PARAMETERS   7
 

number of parameters

Definition at line 44 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::Keplerian().

#define PI   M_PI
 

Definition at line 30 of file Keplerian.h.

#define Re   6378.145
 

Definition at line 24 of file Keplerian.h.

Referenced by O_SESSAME::OsculatingOrbitalElements::MeanToOsculating(), and O_SESSAME::OsculatingOrbitalElements::OsculatingToMean().

Variable Documentation

const int O_SESSAME::ARG_LATTITUDE = VectorIndexBase + 4
 

position of the Argument of Latitude, $\theta$, in the element vector

Definition at line 49 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetArgLattitude(), O_SESSAME::Keplerian::SetKeplerianRepresentationEccentricAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationMeanAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationTrueAnomaly(), and O_SESSAME::Keplerian::SetPositionVelocity().

const int O_SESSAME::ARG_PERIGEE = VectorIndexBase + 4
 

position of the argument of perigee, $\omega$, in the element vector

Definition at line 41 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetArgLattitude(), O_SESSAME::Keplerian::GetArgPerigee(), O_SESSAME::Keplerian::GetLongPerigee(), O_SESSAME::Keplerian::GetTrueLongitude(), O_SESSAME::Keplerian::ReadTwoLineElementSet(), O_SESSAME::Keplerian::SetKeplerianRepresentationEccentricAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationMeanAnomaly(), and O_SESSAME::Keplerian::SetPositionVelocity().

const int O_SESSAME::ECCENTRIC_ANOMALY = VectorIndexBase + 0
 

position of the Eccentric Anomaly, $E$, in the element vector

Definition at line 45 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetEccentricAnomaly(), O_SESSAME::Keplerian::GetEccentricAnomalyFromTrueAnomaly(), O_SESSAME::Keplerian::GetMeanAnomalyFromEccentricAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationEccentricAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationMeanAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationTrueAnomaly(), and O_SESSAME::Keplerian::SetPositionVelocity().

const int O_SESSAME::ECCENTRIC_ANOMALY_0 = VectorIndexBase + 1
 

position of the Initial Eccentric Anomaly, $E_o$, in the element vector

Definition at line 46 of file Keplerian.h.

const int O_SESSAME::ECCENTRICITY = VectorIndexBase + 1
 

position of the eccentricity, $e$, in the element vector

Definition at line 38 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetEccentricAnomalyFromMeanAnomaly(), O_SESSAME::Keplerian::GetEccentricAnomalyFromTrueAnomaly(), O_SESSAME::Keplerian::GetEccentricity(), O_SESSAME::Keplerian::GetMeanAnomalyFromEccentricAnomaly(), O_SESSAME::Keplerian::GetTrueAnomalyFromEccentricAnomaly(), O_SESSAME::Keplerian::ReadTwoLineElementSet(), and O_SESSAME::Keplerian::SetPositionVelocity().

const int O_SESSAME::INCLINATION = VectorIndexBase + 2
 

position of the inclination, $i$, in the element vector

Definition at line 39 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetInclination(), O_SESSAME::Keplerian::ReadTwoLineElementSet(), and O_SESSAME::Keplerian::SetPositionVelocity().

const int O_SESSAME::LONG_ASC_NODE = VectorIndexBase + 3
 

position of the longitude of the ascending node, $\Omega$, in the element vector

Definition at line 40 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetLongAscNode(), O_SESSAME::Keplerian::GetLongPerigee(), O_SESSAME::Keplerian::GetTrueLongitude(), O_SESSAME::Keplerian::ReadTwoLineElementSet(), and O_SESSAME::Keplerian::SetPositionVelocity().

const int O_SESSAME::LONG_PERIGEE = VectorIndexBase + 5
 

position of the Longitude of Perigee, $\Pi$, in the element vector

Definition at line 50 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetLongPerigee(), O_SESSAME::Keplerian::SetKeplerianRepresentationEccentricAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationMeanAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationTrueAnomaly(), and O_SESSAME::Keplerian::SetPositionVelocity().

const int O_SESSAME::MEAN_ANOMALY = VectorIndexBase + 2
 

position of the Mean Anomaly, $M$, in the element vector

Definition at line 47 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetMeanAnomaly(), O_SESSAME::Keplerian::GetMeanAnomalyFromEccentricAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationEccentricAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationMeanAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationTrueAnomaly(), and O_SESSAME::Keplerian::SetPositionVelocity().

const int O_SESSAME::MEAN_ANOMALY_0 = VectorIndexBase + 3
 

position of the Initial Mean Anomaly, $M$, in the element vector

Definition at line 48 of file Keplerian.h.

const int O_SESSAME::SEMIMAJOR_AXIS = VectorIndexBase + 0
 

position of the Semimajor axis, $a$, in the element vector

Definition at line 37 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetSemimajorAxis(), O_SESSAME::Keplerian::GetTrueAnomalyFromEccentricAnomaly(), O_SESSAME::Keplerian::ReadTwoLineElementSet(), O_SESSAME::Keplerian::SetKeplerianRepresentationEccentricAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationMeanAnomaly(), and O_SESSAME::Keplerian::SetPositionVelocity().

const int O_SESSAME::TRUE_ANOMALY = VectorIndexBase + 5
 

position of the true anomaly, $\nu$, in the element vector

Definition at line 42 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetArgLattitude(), O_SESSAME::Keplerian::GetEccentricAnomalyFromTrueAnomaly(), O_SESSAME::Keplerian::GetTrueAnomaly(), O_SESSAME::Keplerian::GetTrueAnomalyFromEccentricAnomaly(), O_SESSAME::Keplerian::GetTrueLongitude(), and O_SESSAME::Keplerian::SetPositionVelocity().

const int O_SESSAME::TRUE_LONGITUDE = VectorIndexBase + 6
 

position of the True Longitude, $\ell$, in the element vector

Definition at line 51 of file Keplerian.h.

Referenced by O_SESSAME::Keplerian::GetTrueLongitude(), O_SESSAME::Keplerian::SetKeplerianRepresentationEccentricAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationMeanAnomaly(), O_SESSAME::Keplerian::SetKeplerianRepresentationTrueAnomaly(), and O_SESSAME::Keplerian::SetPositionVelocity().

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