Table of Contents

Class RelativeElements

Namespace
NominalSystems.Universe
Assembly
NominalSystems.Universe.dll

This structure contains the set of Relative orbital elements that define the relative state between two spacecraft

public class RelativeElements
Inheritance
RelativeElements
Derived

Constructors

RelativeElements()

Default constructor for the relative orbital elements

public RelativeElements()

RelativeElements(ClassicElements, ClassicElements)

Construct the relative orbital elements from classical orbital elements by first converting them to non-singular orbital elements.

public RelativeElements(ClassicElements leader, ClassicElements follower)

Parameters

leader ClassicElements

Classical orbital elements of the leader spacecraft

follower ClassicElements

Classical orbital element of the follower spacecraft

RelativeElements(NonSingularElements, NonSingularElements)

Calculate the relative orbital elements based on input non-singular orbital elements

public RelativeElements(NonSingularElements nsoeLeader, NonSingularElements nsoeFollower)

Parameters

nsoeLeader NonSingularElements

The non-singular orbital elements of the lead spacecraft

nsoeFollower NonSingularElements

The non-singular orbital elements of the follower spacecraft

RelativeElements(double, VectorElements, VectorElements) 

public RelativeElements(double mu, VectorElements leader, VectorElements follower)

Parameters

mu double
leader VectorElements
follower VectorElements

RelativeElements(double, double, double, double, double, double)

construct the relative orbital elements

public RelativeElements(double da, double dex, double dey, double dix, double diy, double daoml)

Parameters

da double

The relative semi-major axis

dex double

The relative x component of eccentricity

dey double

The relative y component of eccentricity

dix double

The relative x component of inclination

diy double

The relative y component of inclination

daoml double

The relative argument of mean latitude

Fields

Da

[rad] the relative semi-major axis

public double Da

Field Value

double

Daoml

[rad] the relative mean argument of latitude

public double Daoml

Field Value

double

Dex

[rad] the relative x component of eccentricity

public double Dex

Field Value

double

Dey

[rad] the relative y component of eccentricity

public double Dey

Field Value

double

Dix

[rad] the relative x component of inclination

public double Dix

Field Value

double

Diy

[rad] the relative y component of inclination

public double Diy

Field Value

double

NSOEFollower

The non-singular orbital elements of the follower spacecraft

public NonSingularElements NSOEFollower

Field Value

NonSingularElements

NSOELeader

the non-singular orbital elements of the leader spacecraft

public NonSingularElements NSOELeader

Field Value

NonSingularElements

Methods

ClassicElem2RelativeElem(ClassicElements, ClassicElements)

A method that return the relative elements from input classic elements

public RelativeElements ClassicElem2RelativeElem(ClassicElements leader, ClassicElements follower)

Parameters

leader ClassicElements

The classical orbital elements for the leader spacecraft

follower ClassicElements

The classical orbital elements for the follower spacecraft

Returns

RelativeElements

VectorElem2RelativeElem(double, VectorElements, VectorElements)

A method that returns the relative orbital elements from an input state vector

public RelativeElements VectorElem2RelativeElem(double mu, VectorElements leader, VectorElements follower)

Parameters

mu double

The gravitational parameter of the primary body

leader VectorElements

The vector elements of the leader spacecraft

follower VectorElements

The vector elements of the follower spacecraft

Returns

RelativeElements