C# Class Extensions.Extensions

ファイルを表示 Open project: bengarney/RendezMe

Public Methods

Method	Description
FindAN ( Orbit orbit, Orbit tgtorbit ) : double	Orbit foo, this finds the nodes of two orbits
GetEccentricAtTrue ( this orb, double TrueAnom ) : double	Takes a true anomaly(degrees from Periapsis), and computes Eccentric Anomaly at that target undefined if eccentricity > 1
GetMeanAnomalyAtTime ( this orbit, double t ) : double	Gets the mean anomaly at a time.
GetMeanAtEccentric ( this orb, double E ) : double	You provide the eccentric anomaly, this method will bring the mean.
GetTimeAtMean ( this orbit, double M ) : double	Gets the time at a given mean anomaly. Not compatible with eccentricity >=1
GetTimeAtTrue ( this orbit, double TAnom ) : double	Gets the time for a given true anomaly.
GetTimeToMean ( this orbit, double M ) : double	Time untill vessel reaches specified mean. Not compatible with eccentricyt >=1
GetTimeToRefAN ( this orbit ) : double	ETA to ascending node (Refference Plane).
GetTimeToRefDN ( this orbit ) : double	ETA to descending node(Refference Plane).
GetTimeToRelAN ( this orbit, Orbit tgtorbit ) : double	Eta to this orbits ascending node relative to a second orbit.
GetTimeToRelDN ( this orbit, Orbit tgtorbit ) : double	ETA to this orbits descending node relative to a second orbit
GetTimeToTrue ( this orbit, double Tanom ) : double	Eta to a given true anomaly.
LatLonofVector ( Vector3d vinput ) : double[]	Finds the coordinates of a state vector.
Syncorbits ( this orbit, Orbit tgt_orb, double anomaly, int orbitnum ) : double
TranslateAnomaly ( this orbit, Orbit tgt_Orbit, double anomaly ) : double	Translates a true anomaly from this orbit to the argument's. Orbits should have the same reference body.
f ( this orbit, Orbit tgt_orbit, double x ) : double
fprime ( this orbit, Orbit tgt_orbit, double x ) : double

Method Details

FindAN() public static method

Orbit foo, this finds the nodes of two orbits

public static FindAN ( Orbit orbit, Orbit tgtorbit ) : double
orbit	Orbit	/// Orbit. ///
tgtorbit	Orbit	/// Target Orbit ///
return	double

GetEccentricAtTrue() public static method

Takes a true anomaly(degrees from Periapsis), and computes Eccentric Anomaly at that target undefined if eccentricity > 1

public static GetEccentricAtTrue ( this orb, double TrueAnom ) : double
orb	this	Orbit
TrueAnom	double	/// True anomomaly (0-360) ///
return	double

GetMeanAnomalyAtTime() public static method

Gets the mean anomaly at a time.

public static GetMeanAnomalyAtTime ( this orbit, double t ) : double
orbit	this	/// Orbit. ///
t	double	/// Time from periapsis ///
return	double

GetMeanAtEccentric() public static method

You provide the eccentric anomaly, this method will bring the mean.

public static GetMeanAtEccentric ( this orb, double E ) : double
orb	this
E	double	/// orbit.eccentricAnomaly (0-2pi) ///
return	double

GetTimeAtMean() public static method

Gets the time at a given mean anomaly.

Not compatible with eccentricity >=1

public static GetTimeAtMean ( this orbit, double M ) : double
orbit	this	/// Orbit. ///
M	double	/// Mean anomaly (0-2pi) ///
return	double

GetTimeAtTrue() public static method

Gets the time for a given true anomaly.

public static GetTimeAtTrue ( this orbit, double TAnom ) : double
orbit	this
TAnom	double	/// True anomaly. (0-360) ///
return	double

GetTimeToMean() public static method

Time untill vessel reaches specified mean.

Not compatible with eccentricyt >=1

public static GetTimeToMean ( this orbit, double M ) : double
orbit	this
M	double	/// Mean anomaly ///
return	double

GetTimeToRefAN() public static method

ETA to ascending node (Refference Plane).

public static GetTimeToRefAN ( this orbit ) : double
orbit	this
return	double

GetTimeToRefDN() public static method

ETA to descending node(Refference Plane).

public static GetTimeToRefDN ( this orbit ) : double
orbit	this
return	double

GetTimeToRelAN() public static method

Eta to this orbits ascending node relative to a second orbit.

public static GetTimeToRelAN ( this orbit, Orbit tgtorbit ) : double
orbit	this	/// Orbit. ///
tgtorbit	Orbit	/// Target orbit ///
return	double

GetTimeToRelDN() public static method

ETA to this orbits descending node relative to a second orbit

public static GetTimeToRelDN ( this orbit, Orbit tgtorbit ) : double
orbit	this	/// Orbit. ///
tgtorbit	Orbit	/// Target orbit ///
return	double

GetTimeToTrue() public static method

Eta to a given true anomaly.

public static GetTimeToTrue ( this orbit, double Tanom ) : double
orbit	this	/// Orbit. ///
Tanom	double	/// True anomaly. (0-360) ///
return	double

LatLonofVector() public static method

Finds the coordinates of a state vector.

public static LatLonofVector ( Vector3d vinput ) : double[]
vinput	Vector3d	/// State vector ///
return	double[]

Syncorbits() public static method

public static Syncorbits ( this orbit, Orbit tgt_orb, double anomaly, int orbitnum ) : double
orbit	this
tgt_orb	Orbit
anomaly	double
orbitnum	int
return	double

TranslateAnomaly() public static method

Translates a true anomaly from this orbit to the argument's. Orbits should have the same reference body.

public static TranslateAnomaly ( this orbit, Orbit tgt_Orbit, double anomaly ) : double
orbit	this
tgt_Orbit	Orbit	/// Target Orbit ///
anomaly	double	/// True Anomaly from this orbit.(0-360) ///
return	double

f() public static method

public static f ( this orbit, Orbit tgt_orbit, double x ) : double
orbit	this
tgt_orbit	Orbit
x	double
return	double

fprime() public static method

public static fprime ( this orbit, Orbit tgt_orbit, double x ) : double
orbit	this
tgt_orbit	Orbit
x	double
return	double