Browse Source
- Consolidate 5 TEST_CASEs into 1 SCENARIO with 6 SECTIONs - Add tolerance constants (A_TOL, E_TOL, ANG_TOL, R_TOL, V_TOL) - Convert TOML to inline table syntax - Add precalc script for expected values - Update continue.md with tolerance reference table and strict widen policytest-refactor
4 changed files with 204 additions and 5 deletions
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#!/usr/bin/env python3 |
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""" |
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Precalculate expected values for test_cartesian_to_elements_basic.cpp. |
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Usage: |
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python3 scripts/precalc_cartesian_to_elements_basic.py |
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Outputs C++-style comments with precalculated values for embedding in the test. |
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""" |
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import sys, math |
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sys.path.insert(0, 'scripts') |
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from sim_engine import orbital_to_cartesian, cartesian_to_orbital_elements, vmag, OrbitalElements, G |
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# ============================================================================= |
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# Test configuration: moderate eccentricity, zero inclination |
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# ============================================================================= |
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mu = G * 5.972e24 |
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a = 1.5e7 |
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e = 0.5 |
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nu = 0.0 |
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inc = 0.0 |
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Omega = 0.0 |
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omega = 0.0 |
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elements = OrbitalElements(a=a, e=e, nu=nu, inc=inc, Omega=Omega, omega=omega) |
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pos, vel = orbital_to_cartesian(elements, 5.972e24) |
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r = vmag(pos) |
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v = vmag(vel) |
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# Round-trip: convert back |
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elements_rt = cartesian_to_orbital_elements(pos, vel, 5.972e24) |
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print("# Test: test_cartesian_to_elements_basic") |
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print(f"#") |
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print(f"# Original elements:") |
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print(f"# a = {a:.6f}") |
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print(f"# e = {e:.6f}") |
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print(f"# nu = {nu:.6f}") |
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print(f"# inc = {inc:.6f}") |
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print(f"# Omega = {Omega:.6f}") |
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print(f"# omega = {omega:.6f}") |
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print(f"#") |
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print(f"# State vectors from elements:") |
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print(f"# pos = ({pos[0]:.6f}, {pos[1]:.6f}, {pos[2]:.6f}) m") |
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print(f"# vel = ({vel[0]:.6f}, {vel[1]:.6f}, {vel[2]:.6f}) m/s") |
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print(f"# r = {r:.6f} m") |
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print(f"# v = {v:.6f} m/s") |
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print(f"#") |
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print(f"# Round-trip recovered elements:") |
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print(f"# a = {elements_rt.a:.15f}") |
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print(f"# e = {elements_rt.e:.15f}") |
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print(f"# nu = {elements_rt.nu:.15f}") |
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print(f"# inc = {elements_rt.inc:.15f}") |
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print(f"# Omega = {elements_rt.Omega:.15f}") |
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print(f"# omega = {elements_rt.omega:.15f}") |
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print(f"#") |
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print(f"# Errors:") |
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print(f"# da = {abs(elements_rt.a - a):.2e}") |
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print(f"# de = {abs(elements_rt.e - e):.2e}") |
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print(f"# dnu = {abs(elements_rt.nu - nu):.2e}") |
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print(f"# dinc = {abs(elements_rt.inc - inc):.2e}") |
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print(f"# dOmega = {abs(elements_rt.Omega - Omega):.2e}") |
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print(f"# domega = {abs(elements_rt.omega - omega):.2e}") |
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print(f"# dr = {abs(r - r):.2e} (trivial)") |
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print(f"# dv = {abs(v - v):.2e} (trivial)") |
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# Re-convert recovered elements back to state vectors |
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pos2, vel2 = orbital_to_cartesian(elements_rt, 5.972e24) |
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r2 = vmag(pos2) |
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v2 = vmag(vel2) |
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print(f"#") |
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print(f"# Reconstructed from recovered elements:") |
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print(f"# pos = ({pos2[0]:.6f}, {pos2[1]:.6f}, {pos2[2]:.6f}) m") |
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print(f"# vel = ({vel2[0]:.6f}, {vel2[1]:.6f}, {vel2[2]:.6f}) m/s") |
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print(f"# r = {r2:.6f} m") |
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print(f"# v = {v2:.6f} m/s") |
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print(f"# dr = {abs(r2 - r):.2e} m") |
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print(f"# dv = {abs(v2 - v):.2e} m/s") |
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#include <catch2/catch_test_macros.hpp> |
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#include <catch2/matchers/catch_matchers_floating_point.hpp> |
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#include "../src/physics.h" |
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#include "../src/orbital_mechanics.h" |
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#include "../src/simulation.h" |
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#include "../src/config_loader.h" |
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#include <cmath> |
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using Catch::Matchers::WithinAbs; |
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SCENARIO("Cartesian ↔ orbital elements round-trip conversion", |
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"[cartesian][elements][roundtrip]") { |
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const double TIME_STEP = 60.0; |
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const double parent_mass = 5.972e24; |
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const double A_TOL = 1e-6; |
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const double E_TOL = 1e-12; |
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const double ANG_TOL = 1e-12; |
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const double R_TOL = 1e-6; |
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const double V_TOL = 1e-6; |
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SimulationState* sim = create_simulation(10, 1, 0, TIME_STEP); |
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REQUIRE(load_system_config(sim, "tests/test_cartesian_to_elements_basic.toml")); |
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Spacecraft* craft = &sim->spacecraft[0]; |
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const OrbitalElements& orig = craft->orbit; |
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// Convert elements → state vectors
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Vec3 pos, vel; |
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orbital_elements_to_cartesian(orig, parent_mass, &pos, &vel); |
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const double expected_r = vec3_magnitude(pos); // 7500000.0
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const double expected_v = vec3_magnitude(vel); // 8928.484709...
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// Round-trip: state vectors → elements
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const OrbitalElements recovered = cartesian_to_orbital_elements(pos, vel, parent_mass); |
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// Re-convert recovered elements → state vectors
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Vec3 pos2, vel2; |
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orbital_elements_to_cartesian(recovered, parent_mass, &pos2, &vel2); |
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const double recovered_r = vec3_magnitude(pos2); |
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const double recovered_v = vec3_magnitude(vel2); |
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SECTION("elements round-trip: semi-major axis") { |
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const double da = fabs(recovered.semi_major_axis - orig.semi_major_axis); |
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INFO("Original a: " << orig.semi_major_axis); |
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INFO("Recovered a: " << recovered.semi_major_axis); |
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INFO("Error: " << da << " m"); |
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REQUIRE_THAT(da, WithinAbs(0.0, A_TOL)); |
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} |
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SECTION("elements round-trip: eccentricity") { |
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const double de = fabs(recovered.eccentricity - orig.eccentricity); |
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INFO("Original e: " << orig.eccentricity); |
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INFO("Recovered e: " << recovered.eccentricity); |
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INFO("Error: " << de); |
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REQUIRE_THAT(de, WithinAbs(0.0, E_TOL)); |
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} |
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SECTION("elements round-trip: true anomaly") { |
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const double dnu = fabs(recovered.true_anomaly - orig.true_anomaly); |
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INFO("Original nu: " << orig.true_anomaly); |
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INFO("Recovered nu: " << recovered.true_anomaly); |
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INFO("Error: " << dnu); |
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REQUIRE_THAT(dnu, WithinAbs(0.0, ANG_TOL)); |
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} |
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SECTION("elements round-trip: inclination") { |
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const double dinc = fabs(recovered.inclination - orig.inclination); |
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INFO("Original inc: " << orig.inclination); |
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INFO("Recovered inc: " << recovered.inclination); |
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INFO("Error: " << dinc); |
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REQUIRE_THAT(dinc, WithinAbs(0.0, ANG_TOL)); |
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} |
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SECTION("radius preservation") { |
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INFO("Original r: " << expected_r); |
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INFO("Recovered r: " << recovered_r); |
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REQUIRE_THAT(recovered_r, WithinAbs(expected_r, R_TOL)); |
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} |
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SECTION("velocity magnitude preservation") { |
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INFO("Original v: " << expected_v); |
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INFO("Recovered v: " << recovered_v); |
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REQUIRE_THAT(recovered_v, WithinAbs(expected_v, V_TOL)); |
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} |
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destroy_simulation(sim); |
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} |
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@ -0,0 +1,15 @@
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# Basic elliptical orbit: a=15000km, e=0.5, zero inclination |
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[[bodies]] |
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name = "Earth" |
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mass = 5.972e24 |
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radius = 6.371e6 |
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parent_index = -1 |
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color = { r = 0.0, g = 0.5, b = 1.0 } |
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orbit = { semi_major_axis = 0.0, eccentricity = 0.0, true_anomaly = 0.0 } |
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[[spacecraft]] |
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name = "Test_Spacecraft" |
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mass = 1000.0 |
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parent_index = 0 |
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orbit = { semi_major_axis = 1.5e7, eccentricity = 0.5, true_anomaly = 0.0, inclination = 0.0, longitude_of_ascending_node = 0.0, argument_of_periapsis = 0.0 } |
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