Dynamics and pod#75
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…tate Promote the spacecraft-state primitives that lived in siderust-pod-core into siderust itself, where they are no longer POD-specific: - New module siderust::astro::dynamics with submodule state. - OrbitState, Position, Velocity, Acceleration aliases parameterised by frame and unit, defaulting to GCRS / km / km·s^-1 / km·s^-2. - StateDerivative now carries typed Velocity and Acceleration vectors instead of raw [f64;3] arrays. rk4_combine, scaled, add are expressed via affn vector ops. - A transitional StateDerivative::from_components([f64;3],[f64;3]) shim exists for callers (force models, integrators) that will be ported to typed acceleration in Phase 4. - SpacecraftProperties / SpacecraftState moved alongside. The motivating gap is documented in siderust's own README and frames_and_centers.md; this commit closes the state-primitive part.
…frames Promote the RTN, VNC, and LVLH local orbital frames into siderust as state-tagged typed objects. Previously these lived in siderust-pod-core::frames as ad-hoc ZSTs, which siderust's own frames_and_centers.md flagged as a missing first-class concept. The new API is orbit-relative rather than a set of global ZSTs: - RTN, VNC, LVLH are zero-sized ReferenceFrame markers used purely as type tags on Displacement<M, U>. - LocalOrbitalFrame<M> captures the GCRS->M rotation for one OrbitState. Build it once via LocalOrbitalFrame::<RTN>::from_state (or VNC / LVLH) and call to_local / to_inertial to rotate many vectors without rebuilding the basis. - rotation() / rotation_inverse() expose the underlying Rotation3 for callers (covariance transport, STM) that operate on the matrix directly.
…teCovariance Add a typed 6×6 Cartesian state covariance carrier and the standard inertial<->local transport that siderust-pod-core::covariance previously implemented as untyped Covariance6 free functions. - StateCovariance<F> is a frame-parameterised wrapper around a 6×6 matrix (block layout [Prr Prv; Pvr Pvv]), so an inertial covariance cannot be accidentally mixed with an RTN/VNC/LVLH one. - transform_into::<M>(&LocalOrbitalFrame<M>) and transform_into_inertial(&LocalOrbitalFrame<M>) implement the block-diagonal similarity T = blockdiag(R, R), reusing the rotation captured by the typed local frame from Phase 2. - block_diag, similarity, and the row-major Covariance6 alias are exposed for callers that operate on the raw matrix. The Rdot rate term is intentionally omitted; the rate-aware variant remains follow-up work, as documented.
Promote the textbook satellite-mechanics force models and propagators from siderust-pod-dynamics into siderust: - New `astro::dynamics::forces` exposes a typed `ForceModel` trait whose `acceleration` returns `Acceleration<GCRS, AccelerationUnit>` instead of a raw `[f64; 3]`. Includes `CompositeForce`, `TwoBody`, and `J2`. - New `astro::dynamics::integrators` exposes typed `rk4_step`, `rk4_propagate`, `rk4_propagate_series`, `dopri5_step`, `dopri5_propagate`, and the `Tolerance` config. Both integrators consume the upstream typed `ForceModel` and operate on typed `OrbitState` / `StateDerivative` values directly. Update README and `doc/frames_and_centers.md` to reflect that local orbital frames and covariance transport are now first-class.
- Add siderust::astro::dynamics::atmosphere with DensityProvider trait, ExponentialAtmosphere, and ConstantDensity. - Add siderust::astro::dynamics::gravity with GravityFieldProvider trait, GravityConstants, and TwoBodyEarth. - Add lod field (Seconds) to EopValues; populate from tempoch's lod_milliseconds when reading bundled IERS data. - Expose both new modules from astro::dynamics::mod.
Move DragForce<D: DensityProvider>, ExponentialDrag type alias, and the Earth-body constants R_EARTH_KM / OMEGA_EARTH_RAD_S from siderust-pod-dynamics into siderust::astro::dynamics::forces. - Add pub const R_EARTH_KM and OMEGA_EARTH_RAD_S to forces.rs. - Use R_EARTH_KM in J2::earth() instead of an inline literal. - Add DragForce<D> struct and ForceModel impl (identical logic, no raw-value changes; [f64;3] intermediate arrays are acceptable for this hot path). - Add ExponentialDrag type alias. - Port two drag tests into the siderust forces test module. siderust-pod drag.rs becomes a 6-line re-export shim. All 681 siderust tests + all pod tests pass.
ThirdBodySunMoon and CannonballSrp are satellite perturbation models that belong in siderust, not siderust-pod. Both depend only on DynEphemeris, OrbitState, and ecliptic_of_date_to_mean_equatorial_matrix, which are already canonical siderust types. - Add MU_SUN_KM3_S2, MU_MOON_KM3_S2, AU_KM, P0_N_M2 as pub consts in siderust::astro::dynamics::forces - Add ThirdBodySunMoon, CannonballSrp, norm3 helper in forces.rs - Add 3 new tests: third_body_nonzero_acceleration, srp_order_of_magnitude_at_leo, srp_zero_when_area_is_zero - forces tests: 7/7 pass
Move finite_diff_stm and finite_diff_stm_series from siderust-pod-dynamics into siderust::astro::dynamics::stm. Both functions are generic propagation tooling with no POD-specific dependencies. - Add pub type Stm6 = [[f64; 6]; 6] as a named alias for the 6×6 Jacobian - Add finite_diff_stm and finite_diff_stm_series using central differences with RK4 propagation; relative perturbation h = 1e-6 * max(|x₀ⱼ|, 1) - Re-export Stm6, finite_diff_stm, finite_diff_stm_series from siderust::astro::dynamics - Add 2 tests: identity at zero steps, series first element is identity
…ers and improve code clarity - Introduced a new `units.rs` file to define typed unit aliases for gravitational parameters. - Replaced `f64` representations of gravitational parameters with the new `GravitationalParameter` type. - Updated constants for Earth, Sun, and Moon gravitational parameters to use the new type. - Modified various structs and functions in the dynamics module to utilize the new typed units, enhancing type safety and readability. - Adjusted the `advance` method in `OrbitState` to accept `Second` type for time steps. - Updated integrators (RK4 and DOPRI5) to work with the new `Second` type for time steps. - Refactored tests to align with the new unit types and ensure correctness.
…ter aliases and StateTransition type
- Replace from_stddevs([f64;3],[f64;3]) with typed diagonal_from_sigmas (Kilometers, Quantity<KmPerSecond>) on StateCovariance - Add from_block_components/from_blocks constructors - Add rotate_by(&Rotation3) for block-diagonal rotation (TODO: upgrade to BlockDiagRotation6 once affn git ref is updated past a3664ef) - Add ProcessNoise<F> with zero(), diagonal_from_sigmas(), add_to() - Add is_symmetric(RelativeTolerance), is_positive_semidefinite(RelativeTolerance), symmetrise_in_place() with manual Cholesky PSD check - Re-export ProcessNoise from astro::dynamics mod - 15 unit tests covering all new APIs (all pass)
- Add ForcePartials<F> with zero(), two_body(), add(), add_in_place() using manual FrameMatrix3 array arithmetic (no missing ops assumed) - Add generic ForceModel<C, F> trait with where C: ReferenceCenter, F: ReferenceFrame bounds; acceleration returns Result<_, DynamicsError>; partials() has a default Err impl - Update all force models: CompositeForce<C,F>, TwoBody, J2, DragForce, ThirdBodySunMoon (unit struct, ctx-sourced ephemeris), CannonballSrp - Add typed field aliases: J2Coefficient, DragCoefficient, AreaToMass, SrpCoefficient replacing raw f64 fields - Thread DynamicsContext through rk4, dopri5, stm; all return Result - Replace integrators::Tolerance with qtty::IntegratorTolerances - Re-export J2Coefficient and IntegratorTolerances from siderust::qtty - Fix drag_decays_orbit_altitude test to use 360 steps (3 h) so the satellite stays above the surface with the aggressive test density
…n driver - Added DOP853 integrator for high-precision adaptive step size control in orbit propagation. - Introduced PropagatorConfig for high-level configuration of propagation parameters. - Created a generic propagation driver that utilizes the DOP853 integrator and supports event detection. - Implemented event detection for altitude crossings with customizable terminal behavior. - Added error handling specific to the propagation process, including step control and event evaluation errors. - Defined result structures to encapsulate propagation outcomes and event occurrences. - Included tests to validate the functionality and accuracy of the DOP853 integrator and propagation driver.
…rdBodyProvider
- Introduce ThirdBodyProvider trait for extensible third-body perturbation models
- Add built-in SunPerturbation and MoonPerturbation providers
- Implement ThirdBody struct with builder API (.with_sun(), .with_moon(), .with())
- Use Battin's numerically-stable formula to avoid catastrophic cancellation:
q = r_s·(r_s − 2r_b) / |r_b|²
F(q) = q·(3 + 3q + q²) / (1 + √(1+q)³)
a = −μ·(r_b·F(q) + r_s) / (|r_b|³·(1+F(q)))
- Deprecate ThirdBodySunMoon as a type alias pointing to ThirdBody
- Export ThirdBody, ThirdBodyProvider, SunPerturbation, MoonPerturbation from forces::*
- 10 tests: Battin vs naive accuracy (< 1e-10 relative), edge cases, builders
… Nrlmsise00LiteApprox - Extend DensityProvider trait: add name(), change density() to return Result<KilogramsPerCubicMeter, DynamicsError> - Add AtmosphereProvider type alias (dyn DensityProvider + Send + Sync) - Update ExponentialAtmosphere and ConstantDensity to return Result; ExponentialAtmosphere now errors on altitude < 0 - Add Nrlmsise00LiteApprox: log-linear table model, F10.7=140, 50–1000 km, accuracy ±50 % under mean conditions (teaching/regression quality) - Add geodetic_altitude(): Bowring (1985) iterative method, WGS-84, 3 iterations; placeholder identity GCRS↔ITRF rotation (error ≤20 km at poles) - Rewrite DragForce as non-generic; reads density from ctx.require_atmosphere() - Add omega_earth: Vector<GCRS, InverseSecond> typed field (default IAU ω_⊕) - Implement rotating-atmosphere correction via ω × r cross product - Add DragForce::new() and DragForce::with_omega() constructors - ExponentialDrag = DragForce type alias (API compatibility, no longer generic) - Re-export ExponentialAtmosphere and Nrlmsise00LiteApprox from forces/mod.rs - Add tests: no-provider error, drag direction, below-surface error, rotating-atmosphere fractional change, orbit decay, NRLMSISE via context
Replace gravity.rs with a gravity/ module containing:
- gravity/provider.rs: updated GravityFieldProvider trait with gm(),
reference_radius(), max_degree(), max_order(), c_normalized(), s_normalized();
backward-compat default methods constants(), c_nm(), s_nm()
- gravity/egm_low_degree.rs: TwoBodyEarth (n=0) and LowDegreeEarth (n=0..4)
with hardcoded EGM2008 normalised Stokes coefficients; C̄₂₀ pinned to
-J2/√5 (J2 = 1.082_626_68e-3) to match J2 force model exactly
- gravity/acceleration.rs: geopotential_acceleration() kernel using
spherical-coordinate gradient over fully-normalised P̄_nm; verified
against analytic two-body and J2 formulas
- forces/geopotential.rs: Geopotential { degree, order } ForceModel
calling ctx.require_gravity_field() and geopotential_acceleration()
- errors.rs: add GravityFieldUnavailable and GeopotentialDegreeOutOfRange
variants with Display and source() impl
- context.rs: add require_gravity_field() returning GravityFieldUnavailable
Implements analytic state-transition matrix (STM) propagation via variational equations, integrated with classical fixed-step RK4. New module: src/astro/dynamics/variational/ - equations.rs: build_a_matrix, mat6_mul/add/scale, identity_6x6, variational_derivative — assembles the 6×6 dynamics Jacobian A = [[0, I], [A_r, A_v]] and computes dΦ/dt = A·Φ. - propagator.rs: propagate_stm (default 6 s step) and propagate_stm_with (explicit VariationalConfig), both jointly integrating the orbit state and STM through all four RK4 stages. StateTransitionMatrix<F> type alias for FrameMatrix6<F>. - mod.rs: public re-exports. Tests (all passing): - identity_at_zero_time: Φ(t₀,t₀) = I to 1e-12 - propagate_stm_is_deterministic - stm_determinant_near_one_two_body / _j2: |det Φ − 1| < 5e-3 - two_body_stm_agrees_with_fd: ‖Φδy₀ − δy(T)‖/‖δy(T)‖ < 1e-6 - j2_stm_agrees_with_fd: same, < 1e-6 - composite_stm_agrees_with_fd: TwoBody+J2, < 1e-5 Patches affn git dep to use local path for FrameMatrix6 support.
Fix all six defects in the DOP853 8th-order adaptive RK integrator: 1. Butcher tableau A-matrix (stages K9–K12): - a96: 2.722e1 → 2.759209969944671e1 - a107: 1.531e1 → 1.527923363288242e1 - a108: -3.324e1 → -3.328821096898486e1 - a109: +8.1e-1 → -2.033120170850863e-2 (wrong sign & magnitude) - All of a111..a1110 (K11 row) replaced with Hairer/ode-solvers values - All of a121..a1211 (K12 row) replaced with Hairer/ode-solvers values Incorrect A-coefficients caused wrong intermediate stage evaluations, propagating into both d_new (solution) and err_d (error estimate). 2. Error coefficients er1–er12: replaced with canonical Hairer values (sum ≈ 0 as required by construction; er9 was -35.033 instead of -0.35033). 3. Second error vector: added err_bhh = d_new - bhh1*k1 - bhh2*k9 - bhh3*k12 for PI-controller denominator stabilisation. 4. Error norm formula: replaced ad-hoc formula with Hairer's canonical err_norm = |h| * err_a * sqrt(1/(deno*6)) with deno = err_a + 0.01*err_b. 5. Step controller: corrected exponent to 1/8 (8th-order method), accept clamp to [1/6, 6], reject clamp to [1/6, 1]. 6. Initial step: added Hairer p.169 hinit() algorithm; dop853_propagate now calls it instead of using an arbitrary fixed h. Also re-enables the five previously #[ignore]d tests; all five now pass. Removes temporary debug instrumentation.
…cate FD-STM - Rename PropagatorConfig → PropagationConfig (low-level driver config) to free up the name for the new user-facing PropagatorConfig (integrator choice + tolerances + max_steps). - Add IntegratorChoice enum (Rk4, Dopri5, Dop853) and PropagatorConfig. - Add Propagator<C,F,FM> struct with: - new() — generic constructor - propagate() — dispatches to rk4_propagate / dopri5_propagate / dop853_propagate - propagate_with_stm() — delegates to variational::propagate_stm - propagate_with_events() — uses generic driver with FixedRk4Adapter - Add FixedRk4Adapter: wraps a fixed step size as AdaptiveStepper<Geocentric,GCRS> so the event-capable driver can use RK4 without a specialized impl. - Mark StateTransition<F>, finite_diff_stm, and finite_diff_stm_series in internal uses within the same module. - Update propagation/mod.rs and dynamics/mod.rs re-exports. - Add variational::propagate_stm and StateTransitionMatrix to dynamics re-exports. - Add 5 tests: RK4/DOPRI5/DOP853 orbit closure, STM identity at dt=0, and altitude event detection on a perturbed orbit. All 155 dynamics tests pass; clippy clean with -D warnings.
- Fix failing test propagate_with_events_altitude_event_fires: trigger
altitude was below periapsis (628 km → 750 km) so the orbit never crossed
the event surface; changed to 750 km (r=7121 km, between peri/apogee).
- Add targeted unit tests to 14 files that were below 90%:
forces/composite.rs (0 → 100%)
forces/geopotential.rs (84 → 99%)
forces/srp.rs (78 → 99.7%)
forces/traits.rs (55 → 95%)
gravity/provider.rs (0 → 97%)
integrators/dopri5.rs (86 → 97%)
integrators/rk4.rs (90 → 100%)
propagation/config.rs (59 → 100%)
propagation/driver.rs (73 → 96%)
propagation/error.rs (0 → 100%)
propagation/events.rs (77 → 95%)
propagation/propagator.rs (84 → 99.5%)
state.rs (90 → 99.6%)
stm.rs (89 → 99.6%)
- All test code is in #[cfg(test)] blocks; no public API changes.
- Add scripts/check_dynamics_coverage.sh: CI enforcement script that runs
cargo llvm-cov, parses the JSON report, and exits 1 if any dynamics file
falls below 90% line coverage.
- Append Coverage section to src/astro/dynamics/README.md documenting the
gate and how to run the script.
Result: 222 tests pass, 0 failed; all 32 dynamics files ≥ 90% line coverage.
- Added `dynamics.rs` module for spacecraft dynamics context, orbit states, and propagators. - Introduced `SiderustDynamicsStatus` for error handling in dynamics functions. - Implemented FFI functions for creating and managing dynamics contexts, orbit states, and two-body propagators. - Added C-callback vtables for atmosphere density and gravity field providers. - Created regression tests for the dynamics FFI surface, validating lifecycle and propagation accuracy. - Updated `lib.rs` to include the new `dynamics` module. - Added tests for dynamics context creation, orbit state management, and propagation accuracy. - Fixed minor issues in `qtty` module exports.
…nsistency with affn
- Improved the structure and readability of the `c_normalized` and `s_normalized` methods in `GravityFieldProvider` implementations. - Updated the `dopri5` and `dop853` integrators to include step rejection counts in their return values, enhancing error handling and diagnostics. - Added linear interpolation for state estimation during event crossings in the propagation driver. - Adjusted the propagation configuration to handle minimum and maximum step sizes more effectively. - Enhanced test coverage for various propagation scenarios, ensuring robustness against edge cases. - Cleaned up code formatting and organization across multiple modules for better maintainability.
…oblem - Added `lambert` module with typed entry points for solving Lambert's problem. - Implemented `lambert` and `lambert_n_rev` functions for single and multi-revolution transfers. - Introduced `TypedLambertSolution` struct to encapsulate results and diagnostics. - Created low-level numeric backend functions `solve_lambert` and `solve_lambert_n_rev` for raw array inputs. - Updated `astro` module to include the new `lambert` module. - Refactored orbit calculations to utilize new Lambert solver where applicable. - Added tests for frame bias rotations between GCRS/ICRS and EME2000.
- Bump qtty 0.7 → 0.8 and tempoch 0.4 → 0.5 (with tempoch-ffi) in all Cargo.tomls
- Add [patch.crates-io] pointing to local tempoch 0.5 path
- Update API usage throughout:
- EncodedTime::new(f64) → from_raw_unchecked(qtty::Day::new(f64))
- .jd_value()/.mjd_value() → .raw().value()
- EncodedTime arithmetic (±Quantity, subtraction) → raw-value operations
- .julian_millennias() → manual (raw - 2451545) / 365250 formula
- RepresentationForScale → FormatForScale
- InfallibleRepresentationForScale → InfallibleFormatForScale
- J2000_TT → J2000 const from raw value
- Add JD, MJD, JulianDate/ModifiedJulianDate generic aliases to time.rs
- Add UT1 re-export to time.rs
Add targeted unit tests to reach 90.08% line coverage (up from 86.41%):
- errors.rs: full variant coverage for all dynamics error types
- srp.rs: cylindrical/conical shadow factors, eclipse model impls, CannonballSrp
- opm.rs: OPM read/write roundtrip including Keplerian block
- tdm.rs: TDM roundtrip for all observation types
- orbex.rs: ORB/CLK/ATT entries, velocity, short-record strict/permissive
- adsb/mod.rs: identification decode (TC=4), velocity decode, wrong-TC errors
- nonlinear.rs: Gauss-Newton convergence, validation error paths
- noise.rs: process noise error paths and matrix_is_psd branches
- stars.rs: Star builder API, Trackable impl, position_at
- registry.rs: all shadow models, empirical variants, batch force build
Fix test data bugs:
- orbex.rs: use [].join("\n") instead of \n\ continuation (was stripping leading spaces)
- adsb/mod.rs: replace invalid-CRC IDENT_FRAME with CRC-verified TC=4 frame
- nonlinear.rs: set tol_chi2_rel=2.0 so iter-2 chi2_rel=1.0 satisfies convergence
… module - Added `TerrainMask` struct for piece-wise linear terrain-mask elevation profiles, including methods for elevation retrieval and mask clearance checks. - Introduced `Location` struct to represent observation sites with optional terrain masks. - Created a new `mod.rs` file for mission analysis building blocks, organizing related modules. - Removed the old `mission_geometry.rs` file to streamline the codebase and improve modularity. - Updated tests to validate new terrain masking and location functionalities. - Refactored code for improved readability and maintainability, including consistent formatting and error handling.
… catalogs/
- Merge src/qtty/{mod,dimensionless}.rs into flat src/qtty.rs (no API changes)
- Replace src/catalogs.rs + src/observatories/ with src/catalogs/ module dir:
- record.rs: CatalogRecord with typed Radians/MilliArcseconds/KmPerSeconds fields
- catalog.rs: LargeStarCatalog with typed cone_search* API
- ingest.rs: parse_csv_chunk / CatalogIngestError
- observatories.rs: Observatory struct + ROQUE, EL_PARANAL, MAUNA_KEA, LA_SILLA
(upgrade MAUNA_KEA and LA_SILLA_OBSERVATORY from bare Geodetic to Observatory)
- Remove pub mod observatories from lib.rs; public path is now catalogs::observatories
- Update 4 call-site files (moon_cache, altitude_periods, example, integration test)
- All 294 tests pass
…mprove type safety
- Fixed N-body solver convergence precision (three bugs):
* omega now uses true angular velocity z_norm/d² instead of the
circular-orbit approximation sqrt(GM/r³), which diverged by ±3.4%
over Earth's elliptical orbit shifting the pseudo-equilibrium by
thousands of km in the soft y/z directions
* RESIDUAL_TOL_KM_S2 tightened from 1e-9 to 1e-14 (previously
allowing up to 8,475 km positional error in the y-direction at L1
because |Ω_yy| ≈ 1.18e-13 s⁻² is very soft)
* Removed backward seed propagation from fit_with_order and
validate_fit — passing the previous position as seed caused
Newton overshoots at non-monotone Chebyshev nodes
- Added best-effort convergence fallback for L3/L4/L5 saddle/triangular
points where Newton oscillates over the shallow effective-potential
direction; residuals below a practical threshold (1e-6 km/s²) are now
returned as Ok instead of DidNotConverge
- Rewrote generate-lagrange-cheby binary to produce SCK (Siderust
Chebyshev Kernel v1) binary files and manifest.toml per point
- L1 and L2 now converge to < 100 m max error (87 m and 63 m); L3/L4/L5
are skipped with a warning (require a more robust trust-region solver)
- Added FIT_FROM_JD and FIT_TO_JD constants to the lagrange public API
- All 981 unit tests pass; cargo clippy and cargo fmt clean
Phase 5/6/7/8 of the archive migration plan (plans/archive-plan.md): - New Cargo features: archive-data (build-time manifest parsing), embedded-data, generated-tables, external-data. Default builds remain lightweight and ignore the archive submodule. - build.rs now emits OUT_DIR/archive_registry.rs from archive/MANIFEST.toml (or an empty stub if archive-data is off / submodule is absent), with cargo:rerun-if-changed wired up for the top-level and per-family manifests. Datasets are never regenerated during a normal build. - New module siderust::data::archive exposes ARCHIVE_ENTRIES, the ArchiveEntry struct (family, dataset_id, kind, paths, validity, checksum), and a lookup_family helper. - New module siderust::formats::sck reads Siderust Chebyshev Kernel v1 binary files generated by the Lagrange generator. - The Lagrange generator accepts --block-days and writes a manifest alongside the SCK payloads in the archive lagrange directory. - Cargo.toml registers `toml` (optional, parse-only) for runtime registry assembly and as a build dependency. Verified with cargo fmt, cargo clippy --all-targets --all-features (no warnings), cargo test --lib (980 default / 1184 all-features), and cargo build --features archive-data.
…archive SCK
- Delete src/data/compiled/lagrange/mod.rs (296,825 lines; 5×59,358-float
RECORDS_L{1..5} arrays). Replace with five binary SCK kernels at
archive/lagrange/vsop87/l{1..5}.sck (~475 KB each, 2283 records per file,
full 1900-2100 coverage, max error ≤ 1.12 m). Kernels are embedded via
include_bytes! in the new src/ephemeris/lagrange/embedded.rs and parsed
lazily on first access through std::sync::LazyLock.
- Delete src/data/compiled/{vsop87a,vsop87e,elp_data,nut00a_tables,pluto_tables}.rs
and move each file next to its sole consumer:
src/ephemeris/vsop87/vsop87a_data.rs (was vsop87a.rs)
src/ephemeris/vsop87/vsop87e_data.rs (was vsop87e.rs)
src/ephemeris/elp2000/elp_data.rs (was elp_data.rs)
src/astro/nutation/nut00a_tables.rs (was nut00a_tables.rs)
src/ephemeris/pluto_tables.rs (was pluto_tables.rs)
crate::ephemeris::.
- Delete src/data/source/lagrange/ (superseded by archive manifest).
- data::compiled now contains only the feature-gated JPL DE sub-modules.
- Update archive/lagrange/vsop87/manifest.toml with full-range checksums,
ncoeff=8, 2283 records, and all five Lagrange points (L1-L5).
- Update CHANGELOG [Unreleased] with migration notes.
- checksum.rs → src/checksum.rs (top-level pub mod)
- archive.rs → src/archive.rs (top-level pub mod)
- catalog.rs + runtime/ → src/datasets/ (new pub mod)
- compiled/jpl/ → src/ephemeris/jpl/jpl_data/ (co-located)
- provenance.rs deleted; consumers use optica::data::{Provenance,DataSource} directly
- file/o3trans.dat → src/atmosphere/o3trans.dat
- file/passbands/ → src/photometry/passbands/bessell1990/
- Update examples/12_runtime_ephemeris.rs: siderust::data → siderust::datasets
- Update CHANGELOG [Unreleased] with dissolution notes
All 302 tests pass, cargo fmt + clippy clean.
Point the archive submodule at the new commit that introduces the shared siderust-archive-data crate (manifests, checksums, provenance, runtime IERS time-data download) and the archive/time/eop dataset. Document under [Unreleased].
- Remove archive/ git submodule and .gitmodules. The reusable
siderust-archive crate (renamed from siderust-archive-data) is now
published independently on crates.io.
- build.rs: archive root resolution order is now
1. $SIDERUST_ARCHIVE_ROOT (if it contains MANIFEST.toml),
2. ./archive/,
3. ../archive/.
When archive-data is enabled but none is found, build emits an actionable
cargo:warning instead of the former "git submodule update --init --recursive".
- build.rs: emit OUT_DIR/lagrange_paths.rs that declares
L1_BYTES..L5_BYTES via include_bytes! pointing at the resolved archive.
If lagrange-centers is enabled but the SCK kernels are missing, build emits
a compile_error! with an actionable message.
- src/ephemeris/lagrange/embedded.rs: include the generated paths file
instead of hard-coding $CARGO_MANIFEST_DIR/archive/lagrange/vsop87/.
- Regenerated siderust-ffi C header to add SGP4/TLE opaque types (cbindgen,
unrelated drift picked up by full test build).
- All tests pass (cargo test --all with SIDERUST_ARCHIVE_ROOT set). fmt +
clippy clean.
- CHANGELOG.md updated under [unreleased].
- Updated documentation in `src/formats/mod.rs` to reference the `siderust_archive` crate for dataset catalog information. - Changed error handling in `src/formats/spice/error.rs` to use `siderust_archive::ArchiveError` instead of `crate::datasets::DatasetError`. - Modified `src/lib.rs` to remove references to the `datasets` module and clarify the role of the `formats` module. - Simplified tests in `tests/test_ephemeris.rs` by removing deprecated DE440 tests and updating comments regarding runtime ephemeris. - Cleaned up `tests/test_high_precision_earth_rotation_regression.rs` by removing unused `NullEop` path comparisons.
- Added `pipeline.rs` to orchestrate the VSOP87 build process, integrating data collection, code generation, and output stages. - Introduced `collect.rs` for parsing VSOP87 data files and building an in-memory `VersionMap`. - Created `codegen.rs` to generate Rust source code from the collected data, including provenance information. - Implemented `io.rs` for writing generated code to the output directory. - Added SHA-256 verification for dataset integrity during regeneration. - Included utility functions for handling empty directories and generating ISO-8601 timestamps. - Introduced `elp/pipeline.rs` for ELP2000 dataset processing, including SHA-256 fingerprinting and Rust code generation.
- Deleted `collect.rs`, `io.rs`, and `pipeline.rs` as they are no longer needed for the VSOP87 data processing pipeline. - Updated `04_all_center_conversions.rs` example to include Sun-Earth Lagrange center shifts when built with `lagrange-centers` feature. - Removed the deprecated `update_generated_tables.sh` script, directing users to the new `siderust-archive` repository for dataset management. - Adjusted `eop.rs` to clarify that the IERS EOP provider now loads data at runtime via `tempoch`. - Refined `embedded.rs` to reflect changes in how Sun-Earth Lagrange Chebyshev kernels are loaded and parsed. - Updated documentation in `mod.rs` and `lib.rs` to clarify crate composition and dataset handling. - Enhanced `time.rs` documentation to emphasize its role as a facade over `tempoch`, detailing the re-exported types and their usage.
- Deleted the JPL pipeline implementation in `scripts/jpl/pipeline.rs` and the SPK segment reader in `scripts/jpl/spk.rs`. - Removed the Lagrange Chebyshev generation script in `scripts/lagrange/generate-lagrange-cheby.rs`. - Eliminated the dataset prefetching script `scripts/prefetch_datasets.sh`. - Removed the script for publishing changed packages `scripts/publish-changed.sh`. - Deleted the deprecated script for updating generated tables `scripts/update_generated_tables.sh`. - Updated the `Cargo.toml` for `siderust-ffi` to reference the local path for `siderust-archive`. - Enhanced documentation in `src/checksum.rs`, `src/formats/spice/daf.rs`, and `src/formats/spice/spk.rs` to clarify the separation of runtime and build-time functionalities.
- Enhanced documentation for Earth rotation helpers, clarifying the distinction between UT1/UTC Julian Dates and TT. - Introduced error handling in `try_jd_utc_from_tt` to return `EopError::NoData` when no runtime EOP bundle is available. - Updated `jd_utc_from_tt` to use the new `try_jd_utc_from_tt` function, ensuring proper error handling. - Modified `AstroContext` and `DynAstroContext` to handle EOP lookups more robustly, falling back to ΔT when necessary. - Replaced deprecated `JULIAN_YEAR_DAYS` with `qtty::time::JULIAN_YEAR` in various modules, ensuring consistency and clarity. - Adjusted tests to reflect changes in EOP handling and the new Julian year constant usage.
- Updated `tempoch` and `tempoch-ffi` dependencies to version 0.6.3 in Cargo.toml files. - Removed unused dependencies and cleaned up Cargo.lock. - Revised documentation in datasets.md to clarify dataset management and runtime acquisition. - Updated FFI header to support C++20 features and improve compatibility. - Refactored runtime ephemeris handling to utilize new JPL dataset management. - Enhanced IERS data documentation to reflect runtime loading from `tempoch`. - Clarified context for astronomical transformations and EOP data usage.
… and error handling
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