How do I install the Satellitetoolbox Transformations skill?

Run npx skillmds add majiayu000/satellitetoolbox-transformations in your terminal (requires Node.js), paste this page's agent-chat prompt into Claude, Cursor, or any MCP-connected agent, or download the SKILL.md file and copy it into your agent's skills directory.

Is Satellitetoolbox Transformations safe to use?

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Is Satellitetoolbox Transformations free to use?

Yes. Installing skills from SkillMD is free, and the skill stays under its author's original license.

Who published Satellitetoolbox Transformations?

majiayu000 (@majiayu000) published this skill. Their other Agent Skills are listed on their SkillMD profile.

Satellitetoolbox Transformations by majiayu000

Name: Satellitetoolbox Transformations
Rating: 4.2 (5 reviews)
Author: majiayu000

Satellitetoolbox Transformations

SatelliteToolboxTransformations.jl for reference frame rotations (ECI/ECEF), geodetic/geocentric conversions, time epoch conversions, and Earth Orientation Parameters. Use when transforming between reference frames (GCRF, J2000, TOD, MOD, TEME, ITRF, PEF), converting geodetic coordinates, or handling EOP data.

majiayu000 eedb9c6 2 files · 3.5 KB Updated Sep 9, 2026 567 repo stars

File contents

SatelliteToolboxTransformations.jl

Reference frame transformations, geodetic/geocentric conversions, and time epoch handling. Repo: JuliaSpace/SatelliteToolboxTransformations.jl

Frame Selectors (zero-arg functions returning Val singletons)

IAU-76/FK5 ECI: GCRF(), J2000(), TOD(), MOD(), TEME() IAU-76/FK5 ECEF: ITRF(), PEF() IAU-2006/2010 ECI: CIRS(), TIRS(), ERS(), MOD06(), MJ2000()

Do NOT mix IAU-76/FK5 and IAU-2006/2010 frames in one transformation.

Frame Rotations

# Get rotation matrix (DCM by default, or Quaternion)
D = r_eci_to_ecef(GCRF(), ITRF(), jd_utc, eop)
D = r_ecef_to_eci(ITRF(), J2000(), jd_utc, eop)
D = r_eci_to_eci(J2000(), MOD(), jd_utc)
Q = r_eci_to_ecef(Quaternion, GCRF(), ITRF(), jd_utc, eop)

# Transform state vectors and orbits directly
sv_ecef = sv_eci_to_ecef(sv, GCRF(), ITRF(), jd_utc, eop)
sv_eci  = sv_ecef_to_eci(sv, ITRF(), J2000(), jd_utc, eop)
orb_mod = orb_eci_to_eci(orb, J2000(), MOD(), jd_utc)

EOP is optional for some frame pairs but required for ITRF transformations.

EOP Data

eop = fetch_iers_eop()                # IAU-1980 (default)
eop = fetch_iers_eop(Val(:IAU2000A))  # IAU-2000A

Geodetic/Geocentric Conversions

All positions in meters, angles in radians.

(lat, lon, h) = ecef_to_geodetic(r_ecef)                    # rad, rad, m
r_ecef        = geodetic_to_ecef(lat, lon, h)                # -> SVector{3}
(lat, lon, r) = ecef_to_geocentric(r_ecef)                   # rad, rad, m
r_ecef        = geocentric_to_ecef(lat, lon, r)              # -> SVector{3}
(phi_gc, r)   = geodetic_to_geocentric(phi_gd, h)
(phi_gd, h)   = geocentric_to_geodetic(phi_gc, r)

Time Conversions

jd_ut1 = jd_utc_to_ut1(jd_utc, eop)
jd_tt  = jd_utc_to_tt(jd_utc)
DeltaAT = get_Deltaat(jd)   # Accumulated leap seconds

Key Conventions

Units: meters, m/s, radians, Julian Day
Re-exports SatelliteToolboxBase (all base types/constants available)
DCM output by default; pass Quaternion as first arg for quaternion output

---name: satellitetoolbox-transformationsdescription: SatelliteToolboxTransformations.jl for reference frame rotations (ECI/ECEF), geodetic/geocentric conversions, time epoch conversions, and Earth Orientation Parameters. Use when transforming between reference frames (GCRF, J2000, TOD, MOD, TEME, ITRF, PEF), converting geodetic coordinates, or handling EOP data.--- # SatelliteToolboxTransformations.jl Reference frame transformations, geodetic/geocentric conversions, and time epoch handling. Repo: [JuliaSpace/SatelliteToolboxTransformations.jl](https://github.com/JuliaSpace/SatelliteToolboxTransformations.jl) ## Frame Selectors (zero-arg functions returning Val singletons) **IAU-76/FK5 ECI:** `GCRF()`, `J2000()`, `TOD()`, `MOD()`, `TEME()` **IAU-76/FK5 ECEF:** `ITRF()`, `PEF()` **IAU-2006/2010 ECI:** `CIRS()`, `TIRS()`, `ERS()`, `MOD06()`, `MJ2000()` Do NOT mix IAU-76/FK5 and IAU-2006/2010 frames in one transformation. ## Frame Rotations ```julia # Get rotation matrix (DCM by default, or Quaternion) D = r_eci_to_ecef(GCRF(), ITRF(), jd_utc, eop) D = r_ecef_to_eci(ITRF(), J2000(), jd_utc, eop) D = r_eci_to_eci(J2000(), MOD(), jd_utc) Q = r_eci_to_ecef(Quaternion, GCRF(), ITRF(), jd_utc, eop) # Transform state vectors and orbits directly sv_ecef = sv_eci_to_ecef(sv, GCRF(), ITRF(), jd_utc, eop) sv_eci = sv_ecef_to_eci(sv, ITRF(), J2000(), jd_utc, eop) orb_mod = orb_eci_to_eci(orb, J2000(), MOD(), jd_utc) ``` EOP is optional for some frame pairs but required for ITRF transformations. ## EOP Data ```julia eop = fetch_iers_eop() # IAU-1980 (default) eop = fetch_iers_eop(Val(:IAU2000A)) # IAU-2000A ``` ## Geodetic/Geocentric Conversions All positions in **meters**, angles in **radians**. ```julia (lat, lon, h) = ecef_to_geodetic(r_ecef) # rad, rad, m r_ecef = geodetic_to_ecef(lat, lon, h) # -> SVector{3} (lat, lon, r) = ecef_to_geocentric(r_ecef) # rad, rad, m r_ecef = geocentric_to_ecef(lat, lon, r) # -> SVector{3} (phi_gc, r) = geodetic_to_geocentric(phi_gd, h) (phi_gd, h) = geocentric_to_geodetic(phi_gc, r) ``` ## Time Conversions ```julia jd_ut1 = jd_utc_to_ut1(jd_utc, eop) jd_tt = jd_utc_to_tt(jd_utc) DeltaAT = get_Deltaat(jd) # Accumulated leap seconds ``` ## Key Conventions - Units: **meters**, **m/s**, **radians**, Julian Day - Re-exports SatelliteToolboxBase (all base types/constants available) - DCM output by default; pass `Quaternion` as first arg for quaternion output

Frequently asked questions