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65 lines
2.8 KiB
65 lines
2.8 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/simulation.h" |
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#include "../src/orbital_objects.h" |
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#include "../src/maneuver.h" |
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#include "../src/config_loader.h" |
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#include "../src/orbital_mechanics.h" |
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#include <cmath> |
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// Test: Check omega after prograde burn that flips eccentricity vector direction |
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TEST_CASE("Omega calculation after prograde burn", "[omega][debug]") { |
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double parent_mass = 5.972e24; // Earth mass |
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// Initial orbit: zero inclination, omega = 0 |
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// Start at apoapsis where eccentricity vector points opposite to position |
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OrbitalElements elements = {0}; |
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elements.semi_major_axis = 1.0e7; |
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elements.eccentricity = 0.3; |
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elements.true_anomaly = M_PI; // Start at apoapsis |
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elements.inclination = 1e-12; // Tiny inclination to trigger atan2 path |
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elements.longitude_of_ascending_node = 0.0; |
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elements.argument_of_periapsis = 0.0; |
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// Get initial position and velocity |
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Vec3 pos, vel; |
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orbital_elements_to_cartesian(elements, parent_mass, &pos, &vel); |
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// Get initial eccentricity vector |
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Vec3 v = vel; |
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double r = vec3_magnitude(pos); |
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double mu = G * parent_mass; |
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Vec3 e_vec_initial = vec3_scale(vec3_sub(vec3_scale(vel, r), vec3_scale(pos, vec3_magnitude(vel) / mu)), 1.0 / mu); |
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double e_initial = vec3_magnitude(e_vec_initial); |
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INFO("Initial state:"); |
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INFO(" e = " << e_initial); |
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INFO(" e_vec = (" << e_vec_initial.x << ", " << e_vec_initial.y << ", " << e_vec_initial.z << ")"); |
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INFO(" pos = (" << pos.x << ", " << pos.y << ", " << pos.z << ")"); |
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INFO(" vel = (" << vel.x << ", " << vel.y << ", " << vel.z << ")"); |
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// Apply a prograde burn at periapsis |
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Vec3 vel_dir = vec3_normalize(vel); |
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Vec3 delta_v = vec3_scale(vel_dir, 1000.0); // Large burn to flip e_vec |
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vel = vec3_add(vel, delta_v); |
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// Reconstruct orbital elements |
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OrbitalElements new_elements = cartesian_to_orbital_elements(pos, vel, parent_mass); |
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INFO("After prograde burn:"); |
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INFO(" new omega = " << new_elements.argument_of_periapsis << " rad (" << new_elements.argument_of_periapsis * 180.0 / M_PI << " deg)"); |
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INFO(" new e = " << new_elements.eccentricity); |
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// Get new eccentricity vector |
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Vec3 e_vec_new = vec3_scale(vec3_sub(vec3_scale(vel, r), vec3_scale(pos, vec3_magnitude(vel) / mu)), 1.0 / mu); |
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INFO(" new e_vec = (" << e_vec_new.x << ", " << e_vec_new.y << ", " << e_vec_new.z << ")"); |
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// For zero-inclination orbit, omega is computed from the eccentricity vector |
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// (longitude of periapsis since ascending node is undefined) |
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// The key constraint is that omega should be in [0, 2π) |
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bool omega_in_range = (new_elements.argument_of_periapsis >= 0.0) && |
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(new_elements.argument_of_periapsis < 2.0 * M_PI); |
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REQUIRE(omega_in_range); |
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}
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