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OrbitFrameECEF Class Reference
[Orbit Frames]

#include <OrbitFrameECEF.h>

Inheritance diagram for OrbitFrameECEF:

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Collaboration diagram for OrbitFrameECEF:

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List of all members.

Detailed Description

Earth-Centered, Earth-Fixed Satellite Coordinate System.

Detailed Description.

Definition at line 21 of file OrbitFrameECEF.h.

Public Member Functions

Rotation GetRotationFromIJK () const
 Return the rotation $R^{ECEF-IJK}$ ignores transformation due to precession, nutation, and polar motion. $\vec{r}_{ECEF} = R_{3}\left(\theta_{AST}\right)\vec{r}_{IJK}$.
virtual Rotation GetRotation2IJK () const =0
virtual OrbitFrame * NewPointer ()=0
virtual OrbitFrame * Clone ()=0

Public Attributes

OrbitFrameECEF(const double
&_ApparentSiderealTime) Rotatio 		GetRotation2IJK )() const
 Constructor Return the rotation $R^{IJK-ECEF}$ ignores transformation due to precession, nutation, and polar motion. $\vec{r}_{IJK} = R_{3}\left(-\theta_{AST}\right)\vec{r}_{ECEF}$.

Member Function Documentation

virtual OrbitFrame* OrbitFrame::Clone (   )  [pure virtual, inherited]
 

Implemented in OrbitFrameIJK, OrbitFrameNTW, OrbitFramePQW, and OrbitFrameRSW.

Referenced by O_SESSAME::OrbitState::operator=(), O_SESSAME::OrbitState::OrbitState(), and O_SESSAME::OrbitState::SetOrbitFrame().

virtual Rotation OrbitFrame::GetRotation2IJK (   )  const [pure virtual, inherited]
 

Implemented in OrbitFrameIJK, OrbitFrameNTW, OrbitFramePQW, and OrbitFrameSEZ.

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

Rotation OrbitFrameECEF::GetRotationFromIJK (   )  const [inline, virtual]
 

Return the rotation $R^{ECEF-IJK}$ ignores transformation due to precession, nutation, and polar motion. $\vec{r}_{ECEF} = R_{3}\left(\theta_{AST}\right)\vec{r}_{IJK}$.

Parameters:
_ApparentSiderealTime Apparent Sidereal Time (rad)
Returns:
rotation from IJK to ECEF

Implements OrbitFrame.

Definition at line 43 of file OrbitFrameECEF.h.

virtual OrbitFrame* OrbitFrame::NewPointer (   )  [pure virtual, inherited]
 

Implemented in OrbitFrameIJK, OrbitFrameNTW, OrbitFramePQW, and OrbitFrameRSW.

Member Data Documentation

OrbitFrameECEF (const double &_ApparentSiderealTime) Rotatio OrbitFrameECEF::GetRotation2IJK)() const [inline]
 

Constructor Return the rotation $R^{IJK-ECEF}$ ignores transformation due to precession, nutation, and polar motion. $\vec{r}_{IJK} = R_{3}\left(-\theta_{AST}\right)\vec{r}_{ECEF}$.

Parameters:
_ApparentSiderealTime Apparent Sidereal Time (rad)
Returns:
rotation from ECEF to IJK

Definition at line 35 of file OrbitFrameECEF.h.

The documentation for this class was generated from the following file:
Generated on Wed Sep 5 12:54:41 2007 for DSACSS Operational Code by  doxygen 1.3.9.1