Struct ICRS 

pub struct ICRS;

International Celestial Reference System (ICRS).

The system — i.e. the abstract definition of the reference frame: quasi-inertial, kinematically non-rotating, with origin at the solar- system barycentre and axes fixed by the positions of distant quasars. Adopted by the IAU at the XXIIIrd General Assembly (1997, Resolution B2) as the fundamental celestial reference system replacing FK5/J2000.

ICRS is the definition; ICRF is the materialisation.

Relationship to neighbouring frames

Pair	Rotation	Magnitude
ICRS ↔ ICRF	exact identity	0
ICRS ↔ GCRS (direction-only)	identity (translation only on positions)	0
ICRS ↔ EME2000	IAU 2006 frame bias B	≈ 23 mas

The frame-bias rotation between ICRS and EME2000 is the same matrix that connects GCRS to EME2000. The bias constants and transform methods live in siderust::astro::frame_bias.

References

• IAU 1997 Resolution B2 (definition of the ICRS).
• IAU 2000 Resolution B1.3 (relationship to the GCRS).
• IERS Conventions (2010), §3.2 and §5.4.4.

Implementations

impl ICRS

pub fn direction_rotation_to_icrf() -> Rotation3

Direction-frame rotation from ICRS to ICRF.

At the catalog level used by affn the ICRS and its realisation ICRF are bit-identical: the rotation is exactly Rotation3::IDENTITY.

pub fn direction_rotation_to_gcrs() -> Rotation3

Direction-frame rotation from ICRS to GCRS.

Per IAU 2000 Resolution B1.3 the GCRS axes are kinematically non-rotating with respect to ICRS, so for directions the rotation is exactly Rotation3::IDENTITY. (Origin translation is encoded in the center type, not here.)

Trait Implementations

impl Clone for ICRS

fn clone(&self) -> ICRS

Returns a duplicate of the value.

fn clone_from(&mut self, source: &Self)

Performs copy-assignment from source.

impl Copy for ICRS

impl Debug for ICRS

fn fmt(&self, f: &mut Formatter<'_>) -> Result<(), Error>

Formats the value using the given formatter.

impl Default for ICRS

fn default() -> ICRS

Returns the “default value” for a type.

impl<'de> Deserialize<'de> for ICRS

fn deserialize<__D>( __deserializer: __D, ) -> Result<ICRS, <__D as Deserializer<'de>>::Error>

where __D: Deserializer<'de>,

Deserialize this value from the given Serde deserializer.

impl Eq for ICRS

impl FrameRotationProvider<CIRS, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ECEF, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<EME2000, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<EclipticMeanJ2000, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<EquatorialMeanJ2000, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( _jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<EquatorialMeanOfDate, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<EquatorialTrueOfDate, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<FK4B1950, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( _jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<GCRS, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( _jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<Galactic, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( _jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRF, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( _jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, CIRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, ECEF> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, EME2000> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, EclipticMeanJ2000> for ()

ICRS → EclipticMeanJ2000 rotation (J2000 mean ecliptic).

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( _jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, EquatorialMeanJ2000> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( _jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, EquatorialMeanOfDate> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, EquatorialTrueOfDate> for ()

ICRS → EquatorialTrueOfDate rotation.

Combines nutation (dispatched via Nut) with IERS celestial-pole corrections (dX, dY) from the EOP provider into a full precession–nutation matrix.

The first-order correction is: dψ_eop = dX / sin(εA), dε_eop = dY

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, FK4B1950> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( _jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, GCRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( _jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, Galactic> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( _jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, ICRF> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, ITRF> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, JupiterSystemIII> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, MarsFixed> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, MercuryFixed> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, MoonPrincipalAxes> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, NeptuneFixed> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, PlutoFixed> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, SaturnFixed> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, TEME> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, TIRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, UranusFixed> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ICRS, VenusFixed> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<ITRF, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<JupiterSystemIII, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<MarsFixed, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<MercuryFixed, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<MoonPrincipalAxes, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<NeptuneFixed, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<PlutoFixed, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<SaturnFixed, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<TEME, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<TIRS, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<UranusFixed, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl FrameRotationProvider<VenusFixed, ICRS> for ()

fn rotation<Eph, Eop: EopProvider, Nut: NutationModel>( jd: JulianDate, _ctx: &AstroContext<Eph, Eop>, ) -> Rotation3

Computes the rotation matrix from frame F1 to frame F2.

impl IcrsFrameBias for ICRS

fn frame_bias_to_eme2000() -> Rotation3

Constant IAU 2006 frame-bias rotation B from ICRS to EME2000.

impl MutableFrame for ICRS

impl PartialEq for ICRS

fn eq(&self, other: &ICRS) -> bool

Tests for self and other values to be equal, and is used by ==.

fn ne(&self, other: &Rhs) -> bool

Tests for !=. The default implementation is almost always sufficient, and should not be overridden without very good reason.

impl ReferenceFrame for ICRS

fn frame_name() -> &'static str

Returns the canonical name of this reference frame.

fn spherical_names() -> Option<(&'static str, &'static str, &'static str)>

Returns frame-specific names for spherical coordinate components.

impl Serialize for ICRS

fn serialize<__S>( &self, __serializer: __S, ) -> Result<<__S as Serializer>::Ok, <__S as Serializer>::Error>

where __S: Serializer,

Serialize this value into the given Serde serializer.

impl SphericalNaming for ICRS

fn polar_name() -> &'static str

Returns the name for the polar/elevation angle (e.g., “dec”, “lat”, “alt”, “b”).

fn azimuth_name() -> &'static str

Returns the name for the azimuthal angle (e.g., “ra”, “lon”, “az”, “l”).

fn distance_name() -> &'static str

Returns the name for the radial distance (e.g., “distance”, “altitude”, “radius”).

impl StructuralPartialEq for ICRS