matlab-convert-aerospace-coordinates
This MATLAB skill provides aerospace unit conversion and coordinate transformation functions for converting between measurement systems (SI, imperial, nautical), transforming positions across reference frames (ECEF, ECI, LLA, NED), and working with rotation representations including Euler angles, quaternions, and direction cosine matrices. Use it when standardizing aerospace data units, establishing relationships between different coordinate systems, or performing frame transformations needed for navigation, guidance, or vehicle dynamics analysis.
git clone --depth 1 https://github.com/matlab/matlab-agentic-toolkit /tmp/matlab-convert-aerospace-coordinates && cp -r /tmp/matlab-convert-aerospace-coordinates/skills-catalog/aerospace/matlab-convert-aerospace-coordinates ~/.claude/skills/matlab-convert-aerospace-coordinatesSKILL.md
# Aerospace Fundamentals Core Aerospace Toolbox functions for unit conversions, time conversions, coordinate transformations, and rotation representations. ## When to Use - Converting between aerospace unit systems (SI, imperial, nautical) - Computing Julian dates, modified Julian dates, decimal years, or TDB time - Transforming positions between ECEF, ECI, LLA, or flat Earth frames - Converting between geodetic and geocentric latitude - Building DCMs for frame transformations (ECI↔ECEF, ECEF↔NED, body↔wind, body↔stability) - Converting between Euler angles, DCMs, quaternions, and Rodrigues vectors - Using the `quaternion` object for rotation math, interpolation, or composition - Identifying which coordinate frame data is expressed in ## When NOT to Use - Atmosphere models (`atmosisa`, `atmoscoesa`) — use `matlab-compute-aerospace-environment` - Airspeed corrections (`correctairspeed`) — not covered here - Orbit propagation or satellite maneuvers — use Aerospace Toolbox, Aerospace Blockset or Satellite Communications Toolbox - Navigation-specific transforms (`lla2enu`, `lla2ned`) — use Navigation Toolbox - Simulink blocks — use `/model-based-design-core:building-simulink-models` with Aerospace Blockset ## Workflow 1. **Identify the coordinate frame** — Determine what frame your data is in and what frame you need. See `references/coordinate-systems.md` for frame definitions and decision guide. 2. **Convert units first** — Ensure inputs match the function's expected units before calling transforms. 3. **Apply the transformation** — Use the appropriate function with correct argument ordering. 4. **Verify** — Round-trip the result back to the original frame; error should be < 1e-10. ## Key Functions ### Unit Conversions | Function | Converts | Units | |----------|----------|-------| | `convlength` | Length | `'ft'`, `'m'`, `'km'`, `'in'`, `'mi'`, `'naut mi'` | | `convvel` | Velocity | `'ft/s'`, `'m/s'`, `'km/s'`, `'in/s'`, `'km/h'`, `'mph'`, `'kts'`, `'ft/min'` | | `convang` | Angle | `'deg'`, `'rad'`, `'rev'` | | `convacc` | Acceleration | `'ft/s^2'`, `'m/s^2'`, `'km/s^2'`, `'in/s^2'`, `'km/h-s'`, `'mph/s'`, `'G''s'` | | `convangacc` | Angular acceleration | `'deg/s^2'`, `'rad/s^2'`, `'rpm/s'` | | `convangvel` | Angular velocity | `'deg/s'`, `'rad/s'`, `'rpm'` | | `convforce` | Force | `'N'`, `'lbf'` | | `convmass` | Mass | `'kg'`, `'lbm'`, `'slug'` | | `convpres` | Pressure | `'Pa'`, `'psi'`, `'psf'`, `'atm'` | | `convtemp` | Temperature | `'K'`, `'R'`, `'F'`, `'C'` | | `convdensity` | Density | `'kg/m^3'`, `'slug/ft^3'`, `'lbm/ft^3'`, `'lbm/in^3'` | All conversion functions use the same signature: `output = convXXX(value, fromUnit, toUnit)` ### Time Conversions | Function | Purpose | Since | |----------|---------|-------| | `juliandate` | Calendar → Julian Date | R2006b | | `mjuliandate` | Calendar → Modified Julian Date (JD − 2400000.5) | R2006b | | `decyear` | Calendar → decimal year | R2006b | | `leapyear` | Test if year is leap year | R2006b | | `tdbjuliandate` | Terrestrial Time → TDB Julian Date | R2015a | ### Coordinate Transformations | Function | From | To | Since | |----------|------|-----|-------| | `lla2ecef` | LLA (geodetic) | ECEF | R2006b | | `ecef2lla` | ECEF | LLA (geodetic) | R2006b | | `lla2eci` | LLA | ECI | R2014a | | `eci2lla` | ECI | LLA | R2014a | | `ecef2eci` | ECEF (pos/vel/acc) | ECI | R2019a | | `eci2ecef` | ECI (pos/vel/acc) | ECEF | R2019a | | `eci2aer` | ECI | AER (azimuth, elevation, range) | R2015a | | `lla2flat` | LLA | Flat Earth | R2011a | | `flat2lla` | Flat Earth | LLA | R2011a | | `geod2geoc` | Geodetic latitude | Geocentric latitude | R2006b | | `geoc2geod` | Geocentric latitude | Geodetic latitude | R2006b | | `ijk2keplerian` | ECI position/velocity | Keplerian elements | R2019a | | `keplerian2ijk` | Keplerian elements | ECI position/velocity | R2019a | | `siderealTime` | UTC Julian date | GMST (deg) / GAST (s) | R2021a | | `dcmeci2ecef` | — | ECI-to-ECEF DCM | R2013b | | `dcmecef2ned` | — | ECEF-to-NED DCM | R2006b | | `dcm2latlon` | ECEF-to-NED DCM | Lat/Lon | R2006b | | `dcmbody2wind` | Alpha, Beta | Body-to-Wind DCM | R2006b | | `dcm2alphabeta` | Body-to-Wind DCM | Alpha, Beta | R2006b | | `dcmbody2stability` | Alpha | Body-to-Stability DCM | R2022a | ### Rotation Representations | Function | From | To | Since | |----------|------|-----|-------| | `angle2dcm` | Euler angles | DCM | R2006b | | `dcm2angle` | DCM | Euler angles | R2006b | | `angle2quat` | Euler angles | Quaternion (1×4) | R2006b | | `quat2angle` | Quaternion (1×4) | Euler angles | R2007b | | `dcm2quat` | DCM | Quaternion (1×4) | R2006b | | `quat2dcm` | Quaternion (1×4) | DCM | R2006b | | `angle2rod` | Euler angles | Rodrigues vector | R2017a | | `rod2angle` | Rodrigues vector | Euler angles | R2017a | | `dcm2rod` | DCM | Rodrigues vector | R2017a | | `rod2dcm` | Rodrigues vector | DCM | R2017a | | `quat2rod` | Quaternion (1×4) | Rodrigues vector | R2017a | | `rod2quat` | Rodrigues vector | Quaternion (1×4) | R2017a | ### Quaternion Object | Method | Purpose | |--------|---------| | `quaternion(E,'eulerd',RS,PF)` | Create from Euler angles (degrees) | | `quaternion(E,'euler',RS,PF)` | Create from Euler angles (radians) | | `quaternion(RM,'rotmat',PF)` | Create from rotation matrix | | `quaternion(RV,'rotvec')` | Create from rotation vector (radians) | | `compact(q)` | Extract [w x y z] array | | `eulerd(q,RS,PF)` | Convert to Euler angles (degrees) | | `euler(q,RS,PF)` | Convert to Euler angles (radians) | | `rotmat(q,PF)` | Convert to rotation matrix | | `rotvec(q)` / `rotvecd(q)` | Convert to rotation vector (rad/deg) | | `rotatepoint(q,pts)` | Rotate points (active rotation) | | `rotateframe(q,pts)` | Rotate frame (passive rotation) | | `normalize(q)` | Normalize to unit quaternion | | `slerp(q1,q2,t)` | Spherical linear interpolation | | `meanrot(q)` | Mean rotation of array | | `dist(q1,q2)` | Angular distance (radians) | | `angvel(q,dt,PF)` | Angular veloc
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