Class ConstellationLibrary
- Namespace
- NominalSystems.Universe
- Assembly
- NominalSystems.Universe.dll
[Nominal] This library is able to calculate spacecraft constellation parameters from a pre-configured design of constellation. This has helper functions for both Coplanar and Walker-Delta constellations.
public static class ConstellationLibrary- Inheritance
-
ConstellationLibrary
Methods
CoplanarToClassicElements(double, double, double, double, double, int)
Generates an array of ClassicElements representing the orbital elements of a constellation of satellites in coplanar orbits.
public static ClassicElements[] CoplanarToClassicElements(double semiMajorAxis, double inclination, double omegaAscension, double omegaPeriapsis, double trueAnomalyReference, int numSatellites)Parameters
semiMajorAxisdoubleThe semi-major axis of the orbits.
inclinationdoubleThe inclination of the orbits.
omegaAscensiondoubleThe right ascension of the ascending node.
omegaPeriapsisdoubleThe argument of periapsis.
trueAnomalyReferencedoubleThe true anomaly at the reference time.
numSatellitesintThe number of satellites in the constellation.
Returns
- ClassicElements[]
An array of ClassicElements, each representing the orbital elements of a satellite in the constellation.
CoplanarToRelativeElements(double, Spacecraft[])
Generates an array of RelativeElements representing the relative orbital elements of a constellation of satellites in coplanar orbits.
public static RelativeElements[] CoplanarToRelativeElements(double mu, Spacecraft[] spacecraft)Parameters
mudoubleThe gravitational parameter of the central body.
spacecraftSpacecraft[]An array of Spacecraft objects representing the satellites in the constellation.
Returns
- RelativeElements[]
An array of RelativeElements, each representing the relative orbital elements of a satellite in the constellation with respect to the first satellite.
CoplanarToRelativeElementsMean(double, double, double, Spacecraft[])
Generates an array of RelativeElements representing the mean relative orbital elements of a constellation of satellites in coplanar orbits.
public static RelativeElements[] CoplanarToRelativeElementsMean(double mu, double radius, double j2, Spacecraft[] spacecraft)Parameters
mudoubleThe gravitational parameter of the central body.
radiusdoubleThe equatorial radius of the central body.
j2doubleThe second zonal harmonic of the central body's gravitational potential.
spacecraftSpacecraft[]An array of Spacecraft objects representing the satellites in the constellation.
Returns
- RelativeElements[]
An array of RelativeElements, each representing the mean relative orbital elements of a satellite in the constellation with respect to the first satellite.
CoplanarToVectorElements(double, double, double, double, double, double, int)
Generates an array of VectorElements representing the orbital elements of a constellation of satellites in coplanar orbits.
public static VectorElements[] CoplanarToVectorElements(double mu, double semiMajorAxis, double inclination, double omegaAscension, double omegaPeriapsis, double trueAnomalyReference, int numSatellites)Parameters
mudoubleThe gravitational parameter of the central body.
semiMajorAxisdoubleThe semi-major axis of the orbits.
inclinationdoubleThe inclination of the orbits.
omegaAscensiondoubleThe right ascension of the ascending node.
omegaPeriapsisdoubleThe argument of periapsis.
trueAnomalyReferencedoubleThe true anomaly at the reference time.
numSatellitesintThe number of satellites in the constellation.
Returns
- VectorElements[]
An array of VectorElements, each representing the orbital elements of a satellite in the constellation.
WalkerDeltaToClassicElements(double, double, int, int, double, double, double, double)
Initialise the initial orbital conditions of a walker delta constellation returning the initial states as classical orbital elements.
public static ClassicElements[] WalkerDeltaToClassicElements(double semiMajorAxis, double inclination, int numSatellites, int numPlanes, double relativeSpacing, double omegaAscensionRef, double omegaPeriapsisRef, double trueAnomalyRef)Parameters
semiMajorAxisdoubleThe desired semi major axis for all spacecraft in the constellation
inclinationdoubleThe desired inclination for all spacecraft in the constellation
numSatellitesintThe number of spacecraft desired in the constellation
numPlanesintThe number of orbital planes desired in the walker-delta constellation
relativeSpacingdoubleThe relative spacing desired for the walker-delta constellation
omegaAscensionRefdoubleThe initial offset in right ascension of the ascending node
omegaPeriapsisRefdoubleThe initial offset in the argument of periapsis
trueAnomalyRefdoubleThe initial offset in the true anomaly
Returns
- ClassicElements[]
An array of classical orbital elements containing the initial state of spacecraft in the constellation
WalkerDeltaToVectorElements(double, double, double, int, int, double, double, double, double)
Generates an array of VectorElements representing the orbital elements of a Walker Delta constellation of satellites.
public static VectorElements[] WalkerDeltaToVectorElements(double mu, double semiMajorAxis, double inclination, int numSatellites, int numPlanes, double relativeSpacing, double omegaAscensionRef, double omegaPeriapsisRef, double trueAnomalyRef)Parameters
mudoubleThe gravitational parameter of the central body.
semiMajorAxisdoubleThe semi-major axis of the orbits.
inclinationdoubleThe inclination of the orbits.
numSatellitesintThe total number of satellites in the constellation.
numPlanesintThe number of orbital planes in the constellation.
relativeSpacingdoubleThe relative spacing between satellites in adjacent planes.
omegaAscensionRefdoubleThe right ascension of the ascending node at the reference time.
omegaPeriapsisRefdoubleThe argument of periapsis at the reference time.
trueAnomalyRefdoubleThe true anomaly at the reference time.
Returns
- VectorElements[]
An array of VectorElements, each representing the orbital elements of a satellite in the Walker Delta constellation.