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89 lines
3.2 KiB
89 lines
3.2 KiB
#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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