ElementConvert Function

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Description

Converts the Spacecraft's orbital state from one element set to another, and returns the results in array form. The order of the elements for each element set are listed below (using the Spacecraft properties):

 

- CARTESIAN: X, Y, Z, VX, VY, VZ

- KEPLERIAN: A, E, I, RAAN, W, TA

- NONSINGULAR_KEPLERIAN: NonSingularA, NonSingularE1, NonSingularE2, NonSingularE3, NonSingularE4, NonSingularE5

- EQUINOCTIAL: EquinoctialA, EquinoctialH, EquinoctialK, EquinoctialP, EquinoctialQ, EquinoctialLongitude

- BROUWER_MEAN: BL_A, BL_E, BL_I, BL_RAAN, BL_W, BL_MA

- J2_BROUWER_MEAN: BLJ2A, BLJ2E, BLJ2I, BLJ2RAAN, BLJ2W, BLJ2MA

- SPHERICAL: SphericalRadius, RA, DEC, Vi, SphericalAzimuth, VerticalFPA

- SPHERICAL_LATLONG: LatLongRadius, Latitude, Longitude, LatLongVi, LatLongAzimuth, HorizontalFPA

- SGP4: Mean I, Mean RAAN, Mean E, Mean W, Mean MA, Mean MeanMotion

- MODIFIED_EQUINOCTIAL: ModifiedEquinoctialP, ModifiedEquinoctialF, ModifiedEquinoctialG, ModifiedEquinoctialH, ModifiedEquinoctialK, ModifiedEquinoctialL

- SGP4 EQUINOCTIAL: Mean EquinoctialH, Mean EquinoctialK, Mean EquinoctialP, Mean EquinoctialQ, Mean EquinoctialLongitude, Mean EquinoctialMeanMotion

 

Note, when used to convert an element set into SGP4 elements this function is not compatible with the SGP4/SDP4 propagator.

 

Timing Precision Mode

This page describes functionality in nanosecond timing precision mode.

Click here to see the documentation for this object in millisecond timing precision mode.

 

Overload List

Signatures

Return Value

Description

ElementConvert(Variable fromSystem, Variable toSystem, Array elementArray)

Array

Converts the orbital state specified by elementArray from the fromSystem element set to the toSystem element set. Assumes the central body is Earth. The order of the elements for each element set are listed below (using the Spacecraft properties):

 

- CARTESIAN: X, Y, Z, VX, VY, VZ

- KEPLERIAN: A, E, I, RAAN, W, TA

- NONSINGULAR_KEPLERIAN: NonSingularA, NonSingularE1, NonSingularE2, NonSingularE3, NonSingularE4, NonSingularE5

- EQUINOCTIAL: EquinoctialA, EquinoctialH, EquinoctialK, EquinoctialP, EquinoctialQ, EquinoctialLongitude

- BROUWER_MEAN: BL_A, BL_E, BL_I, BL_RAAN, BL_W, BL_MA

- J2_BROUWER_MEAN: BLJ2A, BLJ2E, BLJ2I, BLJ2RAAN, BLJ2W, BLJ2MA

- SPHERICAL: SphericalRadius, RA, DEC, Vi, SphericalAzimuth, VerticalFPA

- SPHERICAL_LATLONG: LatLongRadius, Latitude, Longitude, LatLongVi, LatLongAzimuth, HorizontalFPA

- SGP4: Mean I, Mean RAAN, Mean E, Mean W, Mean MA, Mean MeanMotion

- MODIFIED_EQUINOCTIAL: ModifiedEquinoctialP, ModifiedEquinoctialF, ModifiedEquinoctialG, ModifiedEquinoctialH, ModifiedEquinoctialK, ModifiedEquinoctialL

- SGP4_EQUINOCTIAL: Mean EquinoctialH, Mean EquinoctialK, Mean EquinoctialP, Mean EquinoctialQ, Mean EquinoctialLongitude, Mean EquinoctialMeanMotion

 

Note, when used to convert an element set into Norad elements this function is not compatible with the SGP4/SDP4 propagator.

ElementConvert(Variable fromSystem, Variable toSystem, Array elementArray, Variable mu)

Array

Converts the orbital state specified by elementArray from the fromSystem element set to the toSystem element set, using the central body gravitational parameter specified by mu. The order of the elements for each element set are listed below (using the Spacecraft properties):

 

- CARTESIAN: X, Y, Z, VX, VY, VZ

- KEPLERIAN: A, E, I, RAAN, W, TA

- NONSINGULAR_KEPLERIAN: NonSingularA, NonSingularE1, NonSingularE2, NonSingularE3, NonSingularE4, NonSingularE5

- EQUINOCTIAL: EquinoctialA, EquinoctialH, EquinoctialK, EquinoctialP, EquinoctialQ, EquinoctialLongitude

- BROUWER_MEAN: BL_A, BL_E, BL_I, BL_RAAN, BL_W, BL_MA

- J2_BROUWER_MEAN: BLJ2A, BLJ2E, BLJ2I, BLJ2RAAN, BLJ2W, BLJ2MA

- SPHERICAL: SphericalRadius, RA, DEC, Vi, SphericalAzimuth, VerticalFPA

- SPHERICAL_LATLONG: LatLongRadius, Latitude, Longitude, LatLongVi, LatLongAzimuth, HorizontalFPA

- SGP4: Mean I, Mean RAAN, Mean E, Mean W, Mean MA, Mean MeanMotion

- MODIFIED_EQUINOCTIAL: ModifiedEquinoctialP, ModifiedEquinoctialF, ModifiedEquinoctialG, ModifiedEquinoctialH, ModifiedEquinoctialK, ModifiedEquinoctialL

- SGP4 EQUINOCTIAL: Mean EquinoctialH, Mean EquinoctialK, Mean EquinoctialP, Mean EquinoctialQ, Mean EquinoctialLongitude, Mean EquinoctialMeanMotion

 

Note, when used to convert an element set into SGP4 elements this function is not compatible with the SGP4/SDP4 propagator.

ElementConvert(Variable fromSystem, Variable toSystem, TimeSpan epoch, Array elementArray)

Array

Converts the orbital state specified by elementArray from the fromSystem element set to the toSystem element set. This overload can only be used when the fromSystem or toSystem is Spherical Lat-Long. Assumes the central body is Earth. The order of the elements for each element set are listed below (using the Spacecraft properties):

 

- CARTESIAN: X, Y, Z, VX, VY, VZ

- KEPLERIAN: A, E, I, RAAN, W, TA

- NONSINGULAR_KEPLERIAN: NonSingularA, NonSingularE1, NonSingularE2, NonSingularE3, NonSingularE4, NonSingularE5

- EQUINOCTIAL: EquinoctialA, EquinoctialH, EquinoctialK, EquinoctialP, EquinoctialQ, EquinoctialLongitude

- BROUWER_MEAN: BL_A, BL_E, BL_I, BL_RAAN, BL_W, BL_MA

- J2_BROUWER_MEAN: BLJ2A, BLJ2E, BLJ2I, BLJ2RAAN, BLJ2W, BLJ2MA

- SPHERICAL: SphericalRadius, RA, DEC, Vi, SphericalAzimuth, VerticalFPA

- SPHERICAL_LATLONG: LatLongRadius, Latitude, Longitude, LatLongVi, LatLongAzimuth, HorizontalFPA

- SGP4: Mean I, Mean RAAN, Mean E, Mean W, Mean MA, Mean MeanMotion

- MODIFIED_EQUINOCTIAL: ModifiedEquinoctialP, ModifiedEquinoctialF, ModifiedEquinoctialG, ModifiedEquinoctialH, ModifiedEquinoctialK, ModifiedEquinoctialL

- SGP4 EQUINOCTIAL: Mean EquinoctialH, Mean EquinoctialK, Mean EquinoctialP, Mean EquinoctialQ, Mean EquinoctialLongitude, Mean EquinoctialMeanMotion

 

Note, when used to convert an element set into SGP4 elements this function is not compatible with the SGP4/SDP4 propagator.

ElementConvert(Variable fromSystem, Variable toSystem, TimeSpan epoch, Array elementArray, Variable mu)

Array

Converts the orbital state specified by elementArray from the fromSystem element set to the toSystem element set, using the central body gravitational parameter specified by mu. This overload can only be used when the fromSystem or toSystem is Spherical Lat-Long. The order of the elements for each element set are listed below (using the Spacecraft properties):

 

- CARTESIAN: X, Y, Z, VX, VY, VZ

- KEPLERIAN: A, E, I, RAAN, W, TA

- NONSINGULAR_KEPLERIAN: NonSingularA, NonSingularE1, NonSingularE2, NonSingularE3, NonSingularE4, NonSingularE5

- EQUINOCTIAL: EquinoctialA, EquinoctialH, EquinoctialK, EquinoctialP, EquinoctialQ, EquinoctialLongitude

- BROUWER_MEAN: BL_A, BL_E, BL_I, BL_RAAN, BL_W, BL_MA

- J2_BROUWER_MEAN: BLJ2A, BLJ2E, BLJ2I, BLJ2RAAN, BLJ2W, BLJ2MA

- SPHERICAL: SphericalRadius, RA, DEC, Vi, SphericalAzimuth, VerticalFPA

- SPHERICAL_LATLONG: LatLongRadius, Latitude, Longitude, LatLongVi, LatLongAzimuth, HorizontalFPA

- SGP4: Mean I, Mean RAAN, Mean E, Mean W, Mean MA, Mean MeanMotion

- MODIFIED_EQUINOCTIAL: ModifiedEquinoctialP, ModifiedEquinoctialF, ModifiedEquinoctialG, ModifiedEquinoctialH, ModifiedEquinoctialK, ModifiedEquinoctialL

- SGP4 EQUINOCTIAL: Mean EquinoctialH, Mean EquinoctialK, Mean EquinoctialP, Mean EquinoctialQ, Mean EquinoctialLongitude, Mean EquinoctialMeanMotion

 

Note, when used to convert an element set into SGP4 elements this function is not compatible with the SGP4/SDP4 propagator.

ElementConvert(Variable fromSystem, Variable toSystem, TimeSpan epoch, Array elementArray, Variable mu, Variable bStar)

Array

Converts the orbital state specified by elementArray from the fromSystem element set to the toSystem element set, specifying the value of B* to use when converting to or from the SGP4 element set by bStar and the central body gravitational parameter by mu. B* can only be specified when fromSystem or toSystem is SGP4. The order of the elements for each element set are listed below (using the Spacecraft properties):

 

- CARTESIAN: X, Y, Z, VX, VY, VZ

- KEPLERIAN: A, E, I, RAAN, W, TA

- NONSINGULAR_KEPLERIAN: NonSingularA, NonSingularE1, NonSingularE2, NonSingularE3, NonSingularE4, NonSingularE5

- EQUINOCTIAL: EquinoctialA, EquinoctialH, EquinoctialK, EquinoctialP, EquinoctialQ, EquinoctialLongitude

- BROUWER_MEAN: BL_A, BL_E, BL_I, BL_RAAN, BL_W, BL_MA

- J2_BROUWER_MEAN: BLJ2A, BLJ2E, BLJ2I, BLJ2RAAN, BLJ2W, BLJ2MA

- SPHERICAL: SphericalRadius, RA, DEC, Vi, SphericalAzimuth, VerticalFPA

- SPHERICAL_LATLONG: LatLongRadius, Latitude, Longitude, LatLongVi, LatLongAzimuth, HorizontalFPA

- SGP4: Mean I, Mean RAAN, Mean E, Mean W, Mean MA, Mean MeanMotion

- MODIFIED_EQUINOCTIAL: ModifiedEquinoctialP, ModifiedEquinoctialF, ModifiedEquinoctialG, ModifiedEquinoctialH, ModifiedEquinoctialK, ModifiedEquinoctialL

- SGP4 EQUINOCTIAL: Mean EquinoctialH, Mean EquinoctialK, Mean EquinoctialP, Mean EquinoctialQ, Mean EquinoctialLongitude, Mean EquinoctialMeanMotion

 

Note, when used to convert an element set into SGP4 elements this function is not compatible with the SGP4/SDP4 propagator.

 

 

See also

Functions

Orbit Element Types