Refactor two-body state vector representation and expose from Python (#…

…46)

* Prototype exposing two-body states

* Refactor two body state vector representations

* Move time field into state

* Refactor some more

* Add Python type hints

* Use explicit methods

* Add Python example

* More tests

* Re-add TwoBody trait

* Add Python smoke tests and PyO3 unit test

* Test Python time wrapper

* Test Python frames wrapper

* Test Sun and barycenters

* Test planets

* Test all bodies

* Test PyBody

* Re-introduce `two_body` module and more tests

* Add anomaly tests

.github/workflows/rust.yml

@@ -16,6 +16,29 @@ jobs:
       - name: Run tests
         run: cargo test
 
+  python:
+    name: Python smoke tests
+    runs-on: ubuntu-latest
+    steps:
+      - uses: actions/checkout@v3
+      - uses: dtolnay/rust-toolchain@stable
+      - uses: Swatinem/rust-cache@v2
+      - uses: actions/setup-python@v5
+        with:
+          python-version: '3.11'
+      - name: Generate virtual environment
+        run: python -m venv .venv
+      - name: Build Python wrapper
+        uses: PyO3/maturin-action@v1
+        with:
+          command: develop
+          working-directory: ./crates/lox_py
+          args: --extras dev
+      - name: Run test
+        run: |
+          source .venv/bin/activate
+          pytest crates/lox_py/tests
+
   fmt:
     name: Rustfmt
     runs-on: ubuntu-latest

Cargo.toml

@@ -15,5 +15,8 @@ authors = ["Helge Eichhorn and the lox-space contributors"]
 
 [workspace.dependencies]
 lox_core = { path = "./crates/lox_core" }
+float_eq = "1.0.1"
+proptest = "1.4.0"
+rstest = "0.18.2"
 thiserror = "1.0"
 

crates/lox-space/examples/iss.rs

@@ -14,20 +14,21 @@ fn main() {
     let epoch = Epoch::from_date_and_time(TimeScale::TDB, date, time);
     let position = DVec3::new(6068279.27, -1692843.94, -2516619.18) * 1e-3;
     let velocity = DVec3::new(-660.415582, 5495.938726, -5303.093233) * 1e-3;
-    let iss = Cartesian::new(epoch, Earth, position, velocity);
+    let iss_cartesian = Cartesian::new(epoch, Earth, Icrf, position, velocity);
+    let iss = Keplerian::from(iss_cartesian);
 
-    println!(
-        "ISS Orbit for Julian Day {}",
-        iss.epoch().days_since_j2000(),
-    );
+    println!("ISS Orbit for Julian Day {}", iss.time().days_since_j2000(),);
     println!("=============================");
-    println!("Semi-major axis: {:.3} km", iss.semi_major());
+    println!("Semi-major axis: {:.3} km", iss.semi_major_axis());
     println!("Eccentricity: {:.6}", iss.eccentricity());
     println!("Inclination: {:.3}°", iss.inclination().to_degrees());
     println!(
         "Longitude of ascending node: {:.3}°",
         iss.ascending_node().to_degrees()
     );
-    println!("Argument of perigee: {}°", iss.periapsis_arg().to_degrees());
+    println!(
+        "Argument of perigee: {}°",
+        iss.periapsis_argument().to_degrees()
+    );
     println!("True anomaly: {:.3}°", iss.true_anomaly().to_degrees());
 }

crates/lox-space/src/prelude.rs

@@ -7,8 +7,8 @@
  */
 
 pub use lox_core::bodies::*;
-
+pub use lox_core::coords::two_body::{Cartesian, Keplerian};
+pub use lox_core::coords::DVec3;
+pub use lox_core::frames::*;
 pub use lox_core::time::dates::*;
 pub use lox_core::time::epochs::*;
-
-pub use lox_core::two_body::{Cartesian, DVec3, Keplerian, TwoBody};

crates/lox_core/Cargo.toml

@@ -4,17 +4,18 @@ version = "0.1.0"
 edition = "2021"
 
 [dependencies]
-float_eq = "1.0.1"
-glam = "0.24.2"
-num = "0.4.0"
+float_eq.workspace = true
 thiserror.workspace = true
+glam = "0.25.0"
+num = "0.4.1"
 nom = "7.1.3"
 fast_polynomial = "0.1.0"
+dyn-clone = "1.0.16"
 
 [dev-dependencies]
-proptest = "1.1.0"
-rstest = "0.18.2"
-divan = "0.1.2"
+proptest.workspace = true
+rstest.workspace = true
+divan = "0.1.11"
 
 [[bench]]
 name = "iau_frames"