OrbitObserver Class Reference

#include <OrbitObserver.h>

Inheritance diagram for OrbitObserver:

[legend]List of all members.


Public Member Functions
	OrbitObserver ()
virtual	~OrbitObserver ()
virtual int	Run ()=0
virtual int	Initialize ()=0
Matrix	DirectionCosMatrix1Axis (double _angle)
	Direction Cosine Matrix about the 1 axis.
Matrix	DirectionCosMatrix2Axis (double _angle)
	Direction Cosine Matrix about the 2 axis.
Matrix	DirectionCosMatrix3Axis (double _angle)
	Direction Cosine Matrix about the 3 axis.
Vector	WGS2ECEFPosition (double _latitude, double _longitude, double _altitude)
	Convert from WGS84 ( latitude (rad), longitude (rad), altitude (m) ) to ECEF poisiton (m) ).
Vector	NED2ECEFVelocity (double _latitude, double _longitude, double _altitude, double _velocityNorth, double _velocityEast, double _velocityDown)
	Convert from NED velocity (m/s) to ECEF velocity (m/s).
Vector	WGS842ECEF (double _latitude, double _longitude, double _altitude, double _velocityNorth, double _velocityEast, double _velocityDown)
	Convert from WGS84 ( latitude (rad), longitude (rad), altitude (m) ) to ECEF poisiton (m) and velocity (m/s).
Vector	ECEFPosition2WGS84 (double _x, double _y, double _z)
	Convert from ECEF position (m) to WGS84 ( latitude (rad), longitude (rad), altitude (m) ).
Vector	ECEF2NEDVelocity (double _latitude, double _longitude, double _altitude, double _Vx, double _Vy, double _Vz)
	Convert from ECEF velocity (m/s) to NED velocity (m/s).
Vector	ECEF2WGS84 (double _x, double _y, double _z, double _Vx, double _Vy, double _Vz)
	Convert from ECEF position (m) and velocity (m/s) to WGS84 ( latitude (rad), longitude (rad), altitude (m) ).
Vector	ECEF2ECI (CAMdoubleVector _ECEFVector, double _jDay)
Vector	ECI2ECEF (CAMdoubleVector _ECIVector, double _jDay)
double	lat_lon (double latlon, char sector)
	Convert Latitude and Longitude in the form of DEG 'N/S' 'E/W' to +/-RAD.
void	TangentPlaneState (AshtechG12_GPS_PhysicalDevice::Position recPos, CAMdoubleVector &_WGS84Vector)
void	ECI2COE (Vector ECI, Vector VECI, Keplerian &myCOE, double &a, double &e, double &i, double &Lon, double &Arg, double &tru)

Constructor & Destructor Documentation

OrbitObserver::OrbitObserver ( )

Definition at line 12 of file OrbitObserver.cpp.

OrbitObserver::~OrbitObserver ( ) [virtual]

Definition at line 17 of file OrbitObserver.cpp.

Member Function Documentation

Matrix OrbitObserver::DirectionCosMatrix1Axis ( double _angle )

Direction Cosine Matrix about the 1 axis.

Parameters:

_angle the single axis rotation angle

Returns:
_DCM 3x3 matrix

Definition at line 28 of file OrbitObserver.cpp.
References O_SESSAME::Matrix.
Referenced by ECEF2NEDVelocity(), and NED2ECEFVelocity().

Matrix OrbitObserver::DirectionCosMatrix2Axis ( double _angle )

Direction Cosine Matrix about the 2 axis.

Parameters:

_angle the single axis rotation angle

Returns:
_DCM 3x3 matrix

Definition at line 44 of file OrbitObserver.cpp.
References O_SESSAME::Matrix.
Referenced by ECEF2NEDVelocity(), and NED2ECEFVelocity().

Matrix OrbitObserver::DirectionCosMatrix3Axis ( double _angle )

Direction Cosine Matrix about the 3 axis.

Parameters:

_angle the single axis rotation angle

Returns:
_DCM 3x3 matrix

Definition at line 60 of file OrbitObserver.cpp.
References O_SESSAME::Matrix.
Referenced by ECEF2NEDVelocity(), and NED2ECEFVelocity().

Vector OrbitObserver::ECEF2ECI ( CAMdoubleVector _ECEFVector,

double _jDay

)

Referenced by GPSObserver::Run().

Vector OrbitObserver::ECEF2NEDVelocity ( double _latitude,

double _longitude,

double _altitude,

double _Vx,

double _Vy,

double _Vz

)

Convert from ECEF velocity (m/s) to NED velocity (m/s).

Equation:
$V_{NED} = DCM_{321}(\phi, \phi+\frac{\pi}{2}, 0 )V_{ECEF}$

Parameters:

_latitude (rad)

_longitude (rad)

_altitude (m)

_Vx (m/s)

_Vy (m/s)

_Vz (m/s)

Returns:
_NEDVector (3x1) [ Vx, Vy, Vz ] (m/s)

Definition at line 217 of file OrbitObserver.cpp.
References _, DirectionCosMatrix1Axis(), DirectionCosMatrix2Axis(), DirectionCosMatrix3Axis(), O_SESSAME::Matrix, PI, and O_SESSAME::Vector.
Referenced by ECEF2WGS84().

Vector OrbitObserver::ECEF2WGS84 ( double _x,

double _y,

double _z,

double _Vx,

double _Vy,

double _Vz

)

Convert from ECEF position (m) and velocity (m/s) to WGS84 ( latitude (rad), longitude (rad), altitude (m) ).

Parameters:

_x (m)

_y (m)

_z (m)

_Vx (m/s)

_Vy (m/s)

_Vz (m/s)

Returns:
_WGS84Vector (6x1) [ latitude, longitude, altitude, velocity North, velocity East, velocity Down ] (rad, rad, m, m/s, m/s, m/s)

Definition at line 243 of file OrbitObserver.cpp.
References _, ECEF2NEDVelocity(), ECEFPosition2WGS84(), and O_SESSAME::Vector.

Vector OrbitObserver::ECEFPosition2WGS84 ( double _x,

double _y,

double _z

)

Convert from ECEF position (m) to WGS84 ( latitude (rad), longitude (rad), altitude (m) ).

Equation: ( www.colorado.edu/geographyy/gcraft/notes/datum/datum_f.html )
$\phi = atan{ \left( \frac{ z+e^{'2}b\sin^2{\theta} }{ p-e^2 acos^2{\theta} } \right) }$

$\lambda = atan{ \frac{y}{x} }$

$h = \frac{p}{\cos{\phi}} - N(\phi)$

where: $\phi, \lambda, h$ are the geodetic latitude, longitude, and height above ellipsoid

$p = \sqrt{x^2+y^2}$

$\theta = atan \frac{ za }{ pb }$

$e^{'2} = \frac{a^2-b^2}{b^2}$

$N = \frac{a}{ \sqrt{ 1-e^2\sin^2{ \phi } } }$

$e^2 = 2f-f^2$

Parameters:

_x (m)

_y (m)

_z (m)

Returns:
_WGS84Vector (3x1) [ latitude, longitude, altitude ] (rad, rad, m)

Definition at line 165 of file OrbitObserver.cpp.
References f(), and O_SESSAME::Vector.
Referenced by ECEF2WGS84().

void OrbitObserver::ECI2COE ( Vector ECI,

Vector VECI,

Keplerian & myCOE,

double & a,

double & e,

double & i,

double & Lon,

double & Arg,

double & tru

)

Vector OrbitObserver::ECI2ECEF ( CAMdoubleVector _ECIVector,

double _jDay

)

virtual int OrbitObserver::Initialize ( ) [pure virtual]

Initializes the observer (pure virtual function
Implemented in GPSObserver, and OrbitPropObserver.

double OrbitObserver::lat_lon ( double latlon,

char sector

)

Convert Latitude and Longitude in the form of DEG 'N/S' 'E/W' to +/-RAD.

Parameters:

latlon

sector return value (+/-rad) of conversion.

Definition at line 322 of file OrbitObserver.cpp.
References O_SESSAME::Deg2Rad().

Vector OrbitObserver::NED2ECEFVelocity ( double _latitude,

double _longitude,

double _altitude,

double _velocityNorth,

double _velocityEast,

double _velocityDown

)

Convert from NED velocity (m/s) to ECEF velocity (m/s).

Equation:
$V_{ECEF} = DCM_{321}(\phi, -\phi-\frac{\pi}{2}, 0 )^{-1}V_{NED}$

Parameters:

_latitude (rad)

_longitude (rad)

_altitude (m)

_velocityNorth (m/s)

_velocityEast (m/s)

_velocityDown (m/s)

Returns:
_ECEFVector (3x1) [ Vx, Vy, Vz ] (m/s)

Definition at line 109 of file OrbitObserver.cpp.
References _, DirectionCosMatrix1Axis(), DirectionCosMatrix2Axis(), DirectionCosMatrix3Axis(), O_SESSAME::Matrix, PI, and O_SESSAME::Vector.
Referenced by WGS842ECEF().

virtual int OrbitObserver::Run ( ) [pure virtual]

Runs the observer (pure virtual function)
Implemented in GPSObserver, and OrbitPropObserver.

void OrbitObserver::TangentPlaneState ( AshtechG12_GPS_PhysicalDevice::Position recPos,

CAMdoubleVector & _WGS84Vector

)

Referenced by GPSObserver::Run().

Vector OrbitObserver::WGS2ECEFPosition ( double _latitude,

double _longitude,

double _altitude

)

Convert from WGS84 ( latitude (rad), longitude (rad), altitude (m) ) to ECEF poisiton (m) ).

Parameters:

_latitude (rad)

_longitude (rad)

_altitude (m)

Definition at line 78 of file OrbitObserver.cpp.
References f(), and O_SESSAME::Vector.
Referenced by WGS842ECEF().

Vector OrbitObserver::WGS842ECEF ( double _latitude,

double _longitude,

double _altitude,

double _velocityNorth,

double _velocityEast,

double _velocityDown

)

Convert from WGS84 ( latitude (rad), longitude (rad), altitude (m) ) to ECEF poisiton (m) and velocity (m/s).

Parameters:

_latitude (rad)

_longitude (rad)

_altitude (m)

_velocityNorth (m/s)

_velocityEast (m/s)

_velocityDown (m/s)

Returns:
_ECEFVector (6x1) [ x, y, z, Vx, Vy, Vz ] (m & m/s)

Definition at line 134 of file OrbitObserver.cpp.
References _, NED2ECEFVelocity(), O_SESSAME::Vector, and WGS2ECEFPosition().
Referenced by GPSObserver::Run().

The documentation for this class was generated from the following files:

Generated on Wed Sep 5 12:54:41 2007 for DSACSS Operational Code by

1.3.9.1

OrbitObserver Class Reference

Public Member Functions

Constructor & Destructor Documentation

Member Function Documentation