reorganize test configs: 1:1 mapping with test files

- Move all configs from tests/configs/ to tests/
- Rename configs to match test filenames (test_NAME.toml)
- Remove unused configs (earth_mars_simple, simple_root_transition, interplanetary_transfer)
- Combine earth_circular and mars_circular into test_orbital_period.toml
- Duplicate earth_circular.toml as test_energy.toml
- Remove invalid parent test case from test_invalid_parent_assignment.cpp
- Update all test files to reference new config paths
- Delete tests/configs/ directory

tests/configs/earth_mars_simple.toml

@@ -1,50 +0,0 @@
-[[bodies]]
-name = "Sun"
-mass = 1.989e30
-radius = 6.96e8
-parent_index = -1
-color = { r = 1.0, g = 1.0, b = 0.0 }
-orbit = {
-    semi_major_axis = 0.0,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}
-
-[[bodies]]
-name = "Earth"
-mass = 5.972e24
-radius = 6.371e6
-parent_index = 0
-color = { r = 0.0, g = 0.5, b = 1.0 }
-orbit = {
-    semi_major_axis = 1.496e11,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}
-
-[[bodies]]
-name = "Mars"
-mass = 6.39e23
-radius = 3.3895e6
-parent_index = 0
-color = { r = 0.8, g = 0.3, b = 0.1 }
-orbit = {
-    semi_major_axis = 2.279e11,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}
-
-[[bodies]]
-name = "Spacecraft"
-mass = 1.0
-radius = 1000.0
-# Position at LEO altitude: Earth position + (Earth radius + 200km altitude)
-# Earth: 1.496e11, LEO offset: 6.571e6, Total: 1.49606571e11
-parent_index = 1
-color = { r = 1.0, g = 0.0, b = 0.5 }
-orbit = {
-    # Semi-major axis: Earth radius + 200km LEO altitude
-    semi_major_axis = 6.571e6,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}

tests/configs/interplanetary_transfer.toml

@@ -1,54 +0,0 @@
-# Interplanetary Transfer Test Configuration
-# Sun + Earth + Mars + Probe
-# Probe will transition: Earth -> Sun -> Mars
-
-[[bodies]]
-name = "Sun"
-mass = 1.989e30
-radius = 6.96e8
-parent_index = -1
-color = { r = 1.0, g = 1.0, b = 0.0 }
-orbit = {
-    semi_major_axis = 0.0,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}
-
-[[bodies]]
-name = "Earth"
-mass = 5.972e24
-radius = 6.371e6
-parent_index = 0
-color = { r = 0.0, g = 0.5, b = 1.0 }
-orbit = {
-    semi_major_axis = 1.496e11,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}
-
-[[bodies]]
-name = "Mars"
-mass = 6.39e23
-radius = 3.3895e6
-parent_index = 0
-color = { r = 0.8, g = 0.3, b = 0.1 }
-orbit = {
-    semi_major_axis = 2.279e11,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}
-
-[[bodies]]
-name = "Probe"
-mass = 1.0e3
-radius = 1.0e1
-# Start at Earth's position, moving toward Mars
-# The probe will escape Earth's SOI and transition to Sun, then to Mars
-parent_index = 0  # Start orbiting Sun
-color = { r = 0.0, g = 1.0, b = 0.0 }
-orbit = {
-    # Use elliptical transfer orbit with semi_major_axis halfway between Earth and Mars
-    semi_major_axis = 1.888e11,
-    eccentricity = 0.3,
-    true_anomaly = 0.0
-}

tests/configs/mars_circular.toml

@@ -1,27 +0,0 @@
-# Test Configuration: Sun + Mars (circular orbit)
-# Mars at 1.5 AU with circular orbit
-# Expected orbital period: ~687 days
-
-[[bodies]]
-name = "Sun"
-mass = 1.989e30
-radius = 6.96e8
-parent_index = -1
-color = { r = 1.0, g = 1.0, b = 0.0 }
-orbit = {
-    semi_major_axis = 0.0,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}
-
-[[bodies]]
-name = "Mars"
-mass = 6.39e23
-radius = 3.3895e6
-parent_index = 0
-color = { r = 0.8, g = 0.3, b = 0.1 }
-orbit = {
-    semi_major_axis = 2.244e11,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}

tests/test_energy.cpp

@@ -12,7 +12,7 @@ TEST_CASE("Energy conservation - Earth circular orbit", "[energy][rk4]") {
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/earth_circular.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_energy.toml"));
 
     double initial_energy = calculate_system_total_energy(sim);
 

tests/test_hyperbolic_orbit.cpp

@@ -14,7 +14,7 @@ TEST_CASE("Hyperbolic orbit - energy and escape trajectory", "[hyperbolic][energ
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/hyperbolic_comet.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_hyperbolic_orbit.toml"));
 
     const int COMET_INDEX = 1;
     const int SUN_INDEX = 0;
@@ -113,7 +113,7 @@ TEST_CASE("Hyperbolic orbit initial conditions", "[hyperbolic][initial]") {
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/hyperbolic_comet.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_hyperbolic_orbit.toml"));
 
     const int COMET_INDEX = 1;
     const int SUN_INDEX = 0;
@@ -176,7 +176,7 @@ TEST_CASE("Hyperbolic orbit asymptotic velocity", "[hyperbolic][asymptotic]") {
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/hyperbolic_comet.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_hyperbolic_orbit.toml"));
 
     const int COMET_INDEX = 1;
     const int SUN_INDEX = 0;

tests/test_invalid_parent_assignment.cpp

@@ -4,59 +4,12 @@
 #include "../src/config_loader.h"
 #include <cmath>
 
-TEST_CASE("Invalid parent: massive bodies never become children of small bodies",
-          "[init][parent][hierarchy]") {
-    const double TIME_STEP = 60.0;
-    const double MASS_THRESHOLD_RATIO = 1000.0;
-
-    SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
-    REQUIRE(load_system_config(sim, "tests/configs/earth_mars_simple.toml"));
-
-    for (int i = 0; i < sim->body_count; i++) {
-        if (sim->bodies[i].parent_index >= 0) {
-            int parent_idx = sim->bodies[i].parent_index;
-            double parent_mass = sim->bodies[parent_idx].mass;
-            double child_mass = sim->bodies[i].mass;
-            double mass_ratio = parent_mass / child_mass;
-
-            INFO("Body " << i << " (" << sim->bodies[i].name
-                 << ") parent " << parent_idx << " (" << sim->bodies[parent_idx].name
-                 << "): mass ratio = " << mass_ratio);
-
-            REQUIRE(mass_ratio >= 1.0);
-
-            if (strcmp(sim->bodies[parent_idx].name, "Spacecraft") != 0 &&
-                strcmp(sim->bodies[i].name, "Spacecraft") != 0) {
-                REQUIRE(mass_ratio >= MASS_THRESHOLD_RATIO);
-            }
-        }
-    }
-
-    for (int step = 0; step < 100; step++) {
-        update_simulation(sim);
-
-        for (int i = 0; i < sim->body_count; i++) {
-            if (sim->bodies[i].parent_index >= 0) {
-                int parent_idx = sim->bodies[i].parent_index;
-                double parent_mass = sim->bodies[parent_idx].mass;
-                double child_mass = sim->bodies[i].mass;
-
-                if (child_mass > 1e20) {
-                    REQUIRE(parent_mass > child_mass);
-                }
-            }
-        }
-    }
-
-    destroy_simulation(sim);
-}
-
 TEST_CASE("Mutual SOI: similar mass planets within SOI boundary",
           "[init][soi][mutual][edge_case]") {
     const double TIME_STEP = 60.0;
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
-    REQUIRE_FALSE(load_system_config(sim, "tests/configs/mutual_soi_close.toml"));
+    REQUIRE_FALSE(load_system_config(sim, "tests/test_invalid_parent_assignment.toml"));
 
     destroy_simulation(sim);
 }

tests/test_maneuver_planning.cpp

@@ -11,7 +11,7 @@ TEST_CASE("Maneuver loading from config", "[maneuver][config]") {
 
     SimulationState* sim = create_simulation(10, 10, 100, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/maneuver_sequence.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_maneuver_planning.toml"));
 
     REQUIRE(sim->maneuver_count == 2);
     REQUIRE(std::string(sim->maneuvers[0].name) == "orbit_raise_1");
@@ -28,7 +28,7 @@ TEST_CASE("Time-based trigger executes at correct time", "[maneuver][trigger][ti
 
     SimulationState* sim = create_simulation(10, 10, 100, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/maneuver_sequence.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_maneuver_planning.toml"));
 
     REQUIRE(sim->maneuver_count == 2);
     REQUIRE(!sim->maneuvers[0].executed);
@@ -55,7 +55,7 @@ TEST_CASE("True anomaly trigger executes at correct angle", "[maneuver][trigger]
 
     SimulationState* sim = create_simulation(10, 10, 100, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/maneuver_sequence.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_maneuver_planning.toml"));
 
     REQUIRE(sim->maneuver_count == 2);
     REQUIRE(!sim->maneuvers[1].executed);
@@ -98,7 +98,7 @@ TEST_CASE("Maneuvers only execute once", "[maneuver][execution]") {
 
     SimulationState* sim = create_simulation(10, 10, 100, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/maneuver_sequence.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_maneuver_planning.toml"));
 
     const double MAX_TIME = 10000.0;
     while (sim->time < MAX_TIME) {
@@ -125,7 +125,7 @@ TEST_CASE("Duplicate maneuver names fail config load", "[maneuver][config][error
 
     SimulationState* sim = create_simulation(10, 10, 100, TIME_STEP);
 
-    bool result = load_system_config(sim, "tests/configs/maneuver_sequence.toml");
+    bool result = load_system_config(sim, "tests/test_maneuver_planning.toml");
     REQUIRE(result);
 
     REQUIRE(sim->maneuver_count == 2);

tests/test_maneuvers.cpp

@@ -12,7 +12,7 @@ TEST_CASE("Spacecraft loading from config", "[spacecraft][config]") {
 
     SimulationState* sim = create_simulation(10, 10, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/spacecraft_test.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_maneuvers.toml"));
 
     REQUIRE(sim->craft_count == 1);
     REQUIRE(std::string(sim->spacecraft[0].name) == "LEO_Satellite");
@@ -26,7 +26,7 @@ TEST_CASE("Prograde burn increases orbital energy", "[spacecraft][burn][prograde
 
     SimulationState* sim = create_simulation(10, 10, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/spacecraft_test.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_maneuvers.toml"));
 
     Spacecraft* craft = &sim->spacecraft[0];
     CelestialBody* earth = &sim->bodies[1];
@@ -56,7 +56,7 @@ TEST_CASE("Retrograde burn decreases orbital energy", "[spacecraft][burn][retrog
 
     SimulationState* sim = create_simulation(10, 10, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/spacecraft_test.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_maneuvers.toml"));
 
     Spacecraft* craft = &sim->spacecraft[0];
     CelestialBody* earth = &sim->bodies[1];
@@ -86,7 +86,7 @@ TEST_CASE("Normal burn changes orbital plane", "[spacecraft][burn][normal]") {
 
     SimulationState* sim = create_simulation(10, 10, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/spacecraft_test.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_maneuvers.toml"));
 
     Spacecraft* craft = &sim->spacecraft[0];
 
@@ -111,7 +111,7 @@ TEST_CASE("Custom burn applies arbitrary delta-v", "[spacecraft][burn][custom]")
 
     SimulationState* sim = create_simulation(10, 10, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/spacecraft_test.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_maneuvers.toml"));
 
     Spacecraft* craft = &sim->spacecraft[0];
 
@@ -134,7 +134,7 @@ TEST_CASE("Spacecraft propagation maintains stability", "[spacecraft][propagatio
 
     SimulationState* sim = create_simulation(10, 10, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/spacecraft_test.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_maneuvers.toml"));
 
     Spacecraft* craft = &sim->spacecraft[0];
     CelestialBody* earth = &sim->bodies[1];

tests/test_moon_orbits.cpp

@@ -15,7 +15,7 @@ TEST_CASE("Moon orbital stability around Earth", "[moon][earth]") {
 
     SimulationState* sim = create_simulation(20, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/solar_system.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_moon_orbits.toml"));
 
     const int EARTH_INDEX = 2;
     const int MOON_INDEX = 8;
@@ -100,7 +100,7 @@ TEST_CASE("Galilean moons orbital stability around Jupiter", "[moon][jupiter]")
 
     SimulationState* sim = create_simulation(20, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/solar_system.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_moon_orbits.toml"));
 
     const int JUPITER_INDEX = 4;
     const int IO_INDEX = 9;
@@ -164,7 +164,7 @@ TEST_CASE("Titan orbital stability around Saturn", "[moon][saturn]") {
 
     SimulationState* sim = create_simulation(20, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/solar_system.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_moon_orbits.toml"));
 
     const int SATURN_INDEX = 5;
     const int TITAN_INDEX = 13;
@@ -218,7 +218,7 @@ TEST_CASE("Combined solar system with all moons - parent stability", "[moon][int
 
     SimulationState* sim = create_simulation(20, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/solar_system.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_moon_orbits.toml"));
 
     struct ParentChange {
         double time_days;

tests/test_orbital_period.cpp

@@ -13,7 +13,7 @@ TEST_CASE("Orbital period - Earth (RK4)", "[period][rk4]") {
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/earth_circular.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_orbital_period.toml"));
 
     OrbitTracker* tracker = create_orbit_tracker(1);
 
@@ -46,14 +46,14 @@ TEST_CASE("Orbital period - Mars (RK4)", "[period][rk4]") {
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/mars_circular.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_orbital_period.toml"));
 
-    OrbitTracker* tracker = create_orbit_tracker(1);
+    OrbitTracker* tracker = create_orbit_tracker(2);
 
     double max_time = MAX_SIMULATION_DAYS * SECONDS_PER_DAY;
     while (sim->time < max_time && !tracker->orbit_completed) {
         update_simulation(sim);
-        update_orbit_tracker(tracker, &sim->bodies[1], &sim->bodies[0], sim->time);
+        update_orbit_tracker(tracker, &sim->bodies[2], &sim->bodies[0], sim->time);
     }
 
     REQUIRE(tracker->orbit_completed);

tests/test_orbital_period.toml

@@ -1,6 +1,6 @@
-# Simple Root Body Transition Test
+# Test Configuration: Sun + Earth + Mars (circular orbits)
-# Sun + Earth + Mars + Probe
+# Earth at 1 AU, Mars at 1.5 AU with circular orbits
-# Probe positioned to force transitions: Earth -> Sun -> Mars
+# Expected orbital periods: Earth ~365 days, Mars ~687 days
 
 [[bodies]]
 name = "Sun"
@@ -33,20 +33,7 @@ radius = 3.3895e6
 parent_index = 0
 color = { r = 0.8, g = 0.3, b = 0.1 }
 orbit = {
-    semi_major_axis = 2.279e11,
+    semi_major_axis = 2.244e11,
     eccentricity = 0.0,
     true_anomaly = 0.0
 }
-
-# Probe starts near Earth, in Earth's SOI
-[[bodies]]
-name = "Probe"
-mass = 1.0e3
-radius = 1.0e1
-parent_index = 1
-color = { r = 1.0, g = 0.0, b = 1.0 }
-orbit = {
-    semi_major_axis = 5.0e8,
-    eccentricity = 0.2,
-    true_anomaly = 0.0
-}

tests/test_parabolic_orbit.cpp

@@ -14,7 +14,7 @@ TEST_CASE("Parabolic orbit - energy and escape trajectory", "[parabolic][energy]
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/parabolic_comet.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_parabolic_orbit.toml"));
 
     const int COMET_INDEX = 1;
     const int SUN_INDEX = 0;
@@ -106,7 +106,7 @@ TEST_CASE("Parabolic orbit initial conditions", "[parabolic][initial]") {
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/parabolic_comet.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_parabolic_orbit.toml"));
 
     const int COMET_INDEX = 1;
     const int SUN_INDEX = 0;

tests/test_root_body_transitions.cpp

@@ -25,7 +25,7 @@ TEST_CASE("Root body transition - Earth to Sun", "[root][transition]") {
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/manual_root_transition.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_root_body_transitions.toml"));
 
     const int PROBE_INDEX = 3;
     const int SUN_INDEX = 0;
@@ -99,7 +99,7 @@ TEST_CASE("Root body round-trip - Earth -> Sun -> Mars -> Sun", "[root][round-tr
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/manual_root_transition.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_root_body_transitions.toml"));
 
     const int PROBE_INDEX = 3;
     const int SUN_INDEX = 0;

tests/test_soi_transition.cpp

@@ -24,7 +24,7 @@ TEST_CASE("SOI transition - Sun to Mars", "[soi][transition]") {
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/soi_transition.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_soi_transition.toml"));
 
     const int SMALL_BODY_INDEX = 2;
     const int MARS_INDEX = 1;
@@ -102,7 +102,7 @@ TEST_CASE("SOI transition - verify SOI radii", "[soi][radii]") {
 
     SimulationState* sim = create_simulation(10, 0, 0, TIME_STEP);
 
-    REQUIRE(load_system_config(sim, "tests/configs/soi_transition.toml"));
+    REQUIRE(load_system_config(sim, "tests/test_soi_transition.toml"));
 
     const int MARS_INDEX = 1;