Base class for StateVector objects. More...

Inheritance diagram for EECFI::StateVector:

Public Member Functions
	StateVector ()
	Default constructor.
	StateVector (const Time &time, const Coord &coord)
	Class constructor with parameters.
	StateVector (const StateVector &other)
	~StateVector () NOEXCEPT
	Class destructor.
StateVector &	operator= (const StateVector &other)
StateVector	change (const ModelId &modelId, long deriv, long newCS) const
	Change coordinate system.
void	setSun (const ModelId &modelId, Time &time)
	Set Sun state vector.
void	setMoon (const ModelId &modelId, Time &time)
	Set Moon state vector.
void	setPlanet (const ModelId &modelId, Time &time, long planet)
	Set state vector for the requested planet.
void	getPositionOnOrbit (const ModelId &modelId, long angleType, long deriv, double &angle, double &angleRate, double &angleRateRate) const
	Get the true latitude corresponding to the state vector.
Public Attributes
Time	time
	Time object.
Coord	coord
	Coordinates.

Detailed Description

Base class for StateVector objects.

Constructor & Destructor Documentation

EECFI::StateVector::StateVector ( ) [inline]

Default constructor.

Referenced by change().

EECFI::StateVector::StateVector	(	const Time &	time,
		const Coord &	coord
	)

Class constructor with parameters.

Parameters:

	time	Time of the state vector.
	coord	Coordinates.

EECFI::StateVector::StateVector ( const StateVector & other )

Copy constructor.

Parameters:

other

The StateVector to copy from

EECFI::StateVector::~StateVector ( ) [inline]

Class destructor.

Member Function Documentation

StateVector EECFI::StateVector::change	(	const ModelId &	modelId,
		long	deriv,
		long	newCS
	)			const

Change coordinate system.

This method transforms a cartesian state vector between different reference frames. The transformation are done sequentially following the schema in next figure:

The attribute Time must have initialized time correlations. . Note that the transformations between BM2000, HM2000 and GM2000 involve a translation of the input vectors (TR3 and TR3�). In case that the input vector is a direction and not a location, the transformation should only apply the rotations between frames, so the transformation should be done in several steps with StateVector::change, skipping the translations.
Permitted CS = XLCFI_CS_GALACTIC, XLCFI_CS_BM1950, XLCFI_CS_BM2000, XLCFI_CS_HM2000, XLCFI_CS_GM2000, XLCFI_CS_MOD, XLCFI_CS_TOD or XLCFI_CS_EF.

Parameters:

	modelId	Model Id.
	deriv	derivative to be computed (XLCFI_NO_DER or XLCFI_1ST_DER).
	newCS	New coordinate frame (CoordinateSystemEnum).

Returns:: State vector in new reference system.

References EECFI::Coord::acc, coord, EECFI::Coord::cs, EECFI::Coord::pos, EECFI::Time::ref, StateVector(), EECFI::CfiClass::throwWarn, EECFI::Time::time, time, and EECFI::Coord::vel.

void EECFI::StateVector::getPositionOnOrbit	(	const ModelId &	modelId,
		long	angleType,
		long	deriv,
		double &	angle,
		double &	angleRate,
		double &	angleRateRate
	)			const

Get the true latitude corresponding to the state vector.

Get the true/mean latitude describing the position on the orbit. The latitude angle is the angle between the satellite position and the intersection of the orbital plane with a given reference plane. Asumption: the state vector is given in EF.
COMPATIBILITY NOTE: The output of this function is consistent with the calculation of orbit number and time from ANX within the EO CFI only when the required angle type is compliant with [EO_OPS] and [MCD] i.e. either ToD or EF.

Parameters:

	modelId	Model Id.
	angleType	Type of angle(AngleTypeEnum). It defines the reference plane.
	deriv	Derivative (DerivEnum).
	angle	[OUTPUT] Angle describing the position in the orbit [deg].
	angleRate	[OUTPUT] Angle describing the position in the orbit-rate [deg/s].
	angleRateRate	[OUTPUT] Angle describing the position in the orbit-rate-rate [deg/s^2].