remove old test_omega_debug (refactored to tests/)

old_tests/test_omega_debug.cpp

@@ -1,65 +0,0 @@
-#include <catch2/catch_test_macros.hpp>
-#include <catch2/matchers/catch_matchers_floating_point.hpp>
-#include "../src/physics.h"
-#include "../src/simulation.h"
-#include "../src/orbital_objects.h"
-#include "../src/maneuver.h"
-#include "../src/config_loader.h"
-#include "../src/orbital_mechanics.h"
-#include <cmath>
-
-// Test: Check omega after prograde burn that flips eccentricity vector direction
-TEST_CASE("Omega calculation after prograde burn", "[omega][debug]") {
-    double parent_mass = 5.972e24;  // Earth mass
-
-    // Initial orbit: zero inclination, omega = 0
-    // Start at apoapsis where eccentricity vector points opposite to position
-    OrbitalElements elements = {0};
-    elements.semi_major_axis = 1.0e7;
-    elements.eccentricity = 0.3;
-    elements.true_anomaly = M_PI;  // Start at apoapsis
-    elements.inclination = 1e-12;  // Tiny inclination to trigger atan2 path
-    elements.longitude_of_ascending_node = 0.0;
-    elements.argument_of_periapsis = 0.0;
-
-    // Get initial position and velocity
-    Vec3 pos, vel;
-    orbital_elements_to_cartesian(elements, parent_mass, &pos, &vel);
-
-    // Get initial eccentricity vector
-    Vec3 v = vel;
-    double r = vec3_magnitude(pos);
-    double mu = G * parent_mass;
-    Vec3 e_vec_initial = vec3_scale(vec3_sub(vec3_scale(vel, r), vec3_scale(pos, vec3_magnitude(vel) / mu)), 1.0 / mu);
-    double e_initial = vec3_magnitude(e_vec_initial);
-
-    INFO("Initial state:");
-    INFO("  e = " << e_initial);
-    INFO("  e_vec = (" << e_vec_initial.x << ", " << e_vec_initial.y << ", " << e_vec_initial.z << ")");
-    INFO("  pos = (" << pos.x << ", " << pos.y << ", " << pos.z << ")");
-    INFO("  vel = (" << vel.x << ", " << vel.y << ", " << vel.z << ")");
-
-    // Apply a prograde burn at periapsis
-    Vec3 vel_dir = vec3_normalize(vel);
-    Vec3 delta_v = vec3_scale(vel_dir, 1000.0);  // Large burn to flip e_vec
-    vel = vec3_add(vel, delta_v);
-
-    // Reconstruct orbital elements
-    OrbitalElements new_elements = cartesian_to_orbital_elements(pos, vel, parent_mass);
-
-    INFO("After prograde burn:");
-    INFO("  new omega = " << new_elements.argument_of_periapsis << " rad (" << new_elements.argument_of_periapsis * 180.0 / M_PI << " deg)");
-    INFO("  new e = " << new_elements.eccentricity);
-
-    // Get new eccentricity vector
-    Vec3 e_vec_new = vec3_scale(vec3_sub(vec3_scale(vel, r), vec3_scale(pos, vec3_magnitude(vel) / mu)), 1.0 / mu);
-    INFO("  new e_vec = (" << e_vec_new.x << ", " << e_vec_new.y << ", " << e_vec_new.z << ")");
-
-    // For zero-inclination orbit, omega is computed from the eccentricity vector
-    // (longitude of periapsis since ascending node is undefined)
-    // The key constraint is that omega should be in [0, 2π)
-    bool omega_in_range = (new_elements.argument_of_periapsis >= 0.0) &&
-                         (new_elements.argument_of_periapsis < 2.0 * M_PI);
-
-    REQUIRE(omega_in_range);
-}