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Element Access functions
[Orbit State Represenations]

Detailed Description

Functions to access the specific elements of the Keplerian Orbital Elements.


Functions

double O_SESSAME::Keplerian::GetSemiParameter () const
 Compute and return the Semiparameter $p$ of the orbit position.
double O_SESSAME::Keplerian::GetSemimajorAxis () const
 Return the Semimajor Axis $a$ of the orbit position. (km).
double O_SESSAME::Keplerian::GetEccentricity () const
 Return the Eccentricity $e$ of the orbit position. (-).
double O_SESSAME::Keplerian::GetInclination () const
 Return the Inclination $i$ of the orbit position. (-).
double O_SESSAME::Keplerian::GetLongAscNode () const
 Return the Longitude of the Ascending Node $\Omega$ of the orbit position. (rad).
double O_SESSAME::Keplerian::GetArgPerigee () const
 Return the Argument of Perigee $\omega$ of the orbit position. (rad).
double O_SESSAME::Keplerian::GetTrueAnomaly () const
 Return the True Anomaly $\nu$ of the orbit position. (rad).
double O_SESSAME::Keplerian::GetMeanMotion () const
 Return the Mean orbital motion $n$ of the orbit position. (rad/s).
double O_SESSAME::Keplerian::GetEccentricAnomaly () const
 Return the Eccentric Anomaly $E$ of the orbit position. (rad).
double O_SESSAME::Keplerian::GetMeanAnomaly () const
 Return the Mean Anomaly $M$ of the orbit position. (-).

Function Documentation

double O_SESSAME::Keplerian::GetArgPerigee (   )  const [inline, inherited]
 

Return the Argument of Perigee $\omega$ of the orbit position. (rad).

Definition at line 169 of file Keplerian.h.

References O_SESSAME::ARG_PERIGEE.

Referenced by O_SESSAME::TestKeplerian::CompareKeplerian(), O_SESSAME::TestKeplerian::DisplayKeplerian(), O_SESSAME::Keplerian::GetPositionVelocity(), O_SESSAME::AttitudeState::GetRotation2Orbital(), main(), O_SESSAME::OsculatingOrbitalElements::Mapping(), and GPSObserver::Run().

double O_SESSAME::Keplerian::GetEccentricAnomaly (   )  const [inline, inherited]
 

Return the Eccentric Anomaly $E$ of the orbit position. (rad).

Definition at line 178 of file Keplerian.h.

References O_SESSAME::ECCENTRIC_ANOMALY.

Referenced by O_SESSAME::TestKeplerian::CompareKeplerian(), O_SESSAME::TestKeplerian::DisplayKeplerian(), O_SESSAME::OsculatingOrbitalElements::Mapping(), and GPSObserver::Run().

double O_SESSAME::Keplerian::GetEccentricity (   )  const [inline, inherited]
 

Return the Eccentricity $e$ of the orbit position. (-).

Definition at line 160 of file Keplerian.h.

References O_SESSAME::ECCENTRICITY.

Referenced by O_SESSAME::TestKeplerian::CompareKeplerian(), O_SESSAME::TestKeplerian::DisplayKeplerian(), O_SESSAME::Keplerian::GetPositionVelocityPQW(), main(), O_SESSAME::OsculatingOrbitalElements::Mapping(), and GPSObserver::Run().

double O_SESSAME::Keplerian::GetInclination (   )  const [inline, inherited]
 

Return the Inclination $i$ of the orbit position. (-).

Definition at line 163 of file Keplerian.h.

References O_SESSAME::INCLINATION.

Referenced by O_SESSAME::TestKeplerian::CompareKeplerian(), O_SESSAME::TestKeplerian::DisplayKeplerian(), O_SESSAME::Keplerian::GetPositionVelocity(), O_SESSAME::AttitudeState::GetRotation2Orbital(), main(), O_SESSAME::OsculatingOrbitalElements::Mapping(), and GPSObserver::Run().

double O_SESSAME::Keplerian::GetLongAscNode (   )  const [inline, inherited]
 

Return the Longitude of the Ascending Node $\Omega$ of the orbit position. (rad).

Definition at line 166 of file Keplerian.h.

References O_SESSAME::LONG_ASC_NODE.

Referenced by O_SESSAME::TestKeplerian::CompareKeplerian(), O_SESSAME::TestKeplerian::DisplayKeplerian(), O_SESSAME::Keplerian::GetPositionVelocity(), O_SESSAME::AttitudeState::GetRotation2Orbital(), main(), O_SESSAME::OsculatingOrbitalElements::Mapping(), and GPSObserver::Run().

double O_SESSAME::Keplerian::GetMeanAnomaly (   )  const [inline, inherited]
 

Return the Mean Anomaly $M$ of the orbit position. (-).

Definition at line 181 of file Keplerian.h.

References O_SESSAME::MEAN_ANOMALY.

Referenced by O_SESSAME::TestKeplerian::CompareKeplerian(), O_SESSAME::TestKeplerian::DisplayKeplerian(), O_SESSAME::OsculatingOrbitalElements::Mapping(), and GPSObserver::Run().

double O_SESSAME::Keplerian::GetMeanMotion (   )  const [inline, inherited]
 

Return the Mean orbital motion $n$ of the orbit position. (rad/s).

Definition at line 175 of file Keplerian.h.

References MU.

Referenced by main(), and GPSObserver::Run().

double O_SESSAME::Keplerian::GetSemimajorAxis (   )  const [inline, inherited]
 

Return the Semimajor Axis $a$ of the orbit position. (km).

Definition at line 157 of file Keplerian.h.

References O_SESSAME::SEMIMAJOR_AXIS.

Referenced by O_SESSAME::TestKeplerian::CompareKeplerian(), O_SESSAME::TestKeplerian::DisplayKeplerian(), main(), O_SESSAME::OsculatingOrbitalElements::Mapping(), O_SESSAME::OsculatingOrbitalElements::MeanToOsculating(), O_SESSAME::OsculatingOrbitalElements::OsculatingToMean(), and GPSObserver::Run().

double O_SESSAME::Keplerian::GetSemiParameter (   )  const [inline, inherited]
 

Compute and return the Semiparameter $p$ of the orbit position.

Returns:
the semiparameter: $p = a * (1-e^{2})$. (km)

Definition at line 154 of file Keplerian.h.

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

double O_SESSAME::Keplerian::GetTrueAnomaly (   )  const [inline, inherited]
 

Return the True Anomaly $\nu$ of the orbit position. (rad).

Definition at line 172 of file Keplerian.h.

References O_SESSAME::TRUE_ANOMALY.

Referenced by O_SESSAME::TestKeplerian::CompareKeplerian(), O_SESSAME::TestKeplerian::DisplayKeplerian(), O_SESSAME::Keplerian::GetPositionVelocityPQW(), main(), O_SESSAME::OsculatingOrbitalElements::Mapping(), and GPSObserver::Run().

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