cinnaboot
/
claudes_game
1
0
Fork 0
Code Issues Pull Requests Projects Releases Wiki Activity
Browse Source

remove extra printf debugging per sim step

main
cinnaboot 6 months ago
parent
b983002997
commit
bf1b8ee0c6
2 changed files with 2 additions and 89 deletions
Whitespace
Show all changes Ignore whitespace when comparing lines Ignore changes in amount of whitespace Ignore changes in whitespace at EOL
Unified View
Diff Options
Show Stats Download Patch File Download Diff File
  1. 1
      src/mission_planning.cpp
  2. 88
      src/simulation.cpp

1
src/mission_planning.cpp
Unescape View File

@ -138,6 +138,7 @@ void apply_transfer_burn(SimulationState* sim, int spacecraft_idx,
int departure_idx, TransferParameters* params) { int departure_idx, TransferParameters* params) {
CelestialBody* spacecraft = &sim->bodies[spacecraft_idx]; CelestialBody* spacecraft = &sim->bodies[spacecraft_idx];
CelestialBody* departure = &sim->bodies[departure_idx]; CelestialBody* departure = &sim->bodies[departure_idx];
CelestialBody* sun = &sim->bodies[0];
Vec3 sun_to_earth = vec3_sub(departure->position, sun->position); Vec3 sun_to_earth = vec3_sub(departure->position, sun->position);
Vec3 sun_to_earth_norm = vec3_normalize(sun_to_earth); Vec3 sun_to_earth_norm = vec3_normalize(sun_to_earth);

88
src/simulation.cpp
Unescape View File

@ -90,25 +90,12 @@ int find_dominant_body(SimulationState* sim, int body_index) {
int new_parent = 0; int new_parent = 0;
double min_distance = INFINITY; double min_distance = INFINITY;
// Debug: Print SOI check details for spacecraft
bool is_spacecraft = (strncmp(body->name, "Spacecraft", 10) == 0);
if (is_spacecraft) {
printf("DEBUG [find_dominant_body for %s]:\n", body->name);
printf(" Current parent: %d (root)\n", parent_idx);
printf(" Body pos: (%.2e, %.2e, %.2e)\n", body->position.x, body->position.y, body->position.z);
}
for (int i = 0; i < sim->body_count; i++) { for (int i = 0; i < sim->body_count; i++) {
if (i == body_index) continue; if (i == body_index) continue;
CelestialBody* potential = &sim->bodies[i]; CelestialBody* potential = &sim->bodies[i];
double distance = vec3_distance(body->position, potential->position); double distance = vec3_distance(body->position, potential->position);
if (is_spacecraft) {
printf(" Checking body %d (%s): distance=%.2e, SOI=%.2e, within=%d\n",
i, potential->name, distance, potential->soi_radius, distance < potential->soi_radius);
}
// If within SOI and closer than current, switch to this body // If within SOI and closer than current, switch to this body
if (distance < potential->soi_radius && distance < min_distance) { if (distance < potential->soi_radius && distance < min_distance) {
min_distance = distance; min_distance = distance;
@ -116,10 +103,6 @@ int find_dominant_body(SimulationState* sim, int body_index) {
} }
} }
if (is_spacecraft) {
printf(" Selected new parent: %d (%s)\n", new_parent, sim->bodies[new_parent].name);
}
return new_parent; return new_parent;
} }
// Update sphere of influence radius using Hill sphere approximation // Update sphere of influence radius using Hill sphere approximation
@ -145,18 +128,6 @@ void update_simulation(SimulationState* sim) {
int new_parent = find_dominant_body(sim, i); int new_parent = find_dominant_body(sim, i);
// Debug: Print spacecraft state before parent switch
if (strncmp(body->name, "Spacecraft", 10) == 0) {
printf("DEBUG [Before find_dominant_body]:\n");
printf(" Body: %s (idx %d)\n", body->name, i);
printf(" Current parent: %d\n", body->parent_index);
printf(" Global pos: (%.2e, %.2e, %.2e)\n", body->position.x, body->position.y, body->position.z);
printf(" Local pos: (%.2e, %.2e, %.2e)\n", body->local_position.x, body->local_position.y, body->local_position.z);
printf(" Global vel: (%.2e, %.2e, %.2e)\n", body->velocity.x, body->velocity.y, body->velocity.z);
printf(" Local vel: (%.2e, %.2e, %.2e)\n", body->local_velocity.x, body->local_velocity.y, body->local_velocity.z);
printf(" New parent from find_dominant_body: %d\n", new_parent);
}
if (new_parent != body->parent_index) { if (new_parent != body->parent_index) {
// Convert current local coordinates to global coordinates using old parent // Convert current local coordinates to global coordinates using old parent
if (body->parent_index >= 0 && body->parent_index < sim->body_count) { if (body->parent_index >= 0 && body->parent_index < sim->body_count) {
@ -172,14 +143,6 @@ void update_simulation(SimulationState* sim) {
// Update parent index // Update parent index
body->parent_index = new_parent; body->parent_index = new_parent;
// Debug: Print after parent index change, before new local coord calculation
if (strncmp(body->name, "Spacecraft", 10) == 0) {
printf("DEBUG [Parent switch detected]:\n");
printf(" Old parent: %d -> New parent: %d\n", i, new_parent);
printf(" Global pos after old->global transform: (%.2e, %.2e, %.2e)\n", body->position.x, body->position.y, body->position.z);
printf(" Global vel after old->global transform: (%.2e, %.2e, %.2e)\n", body->velocity.x, body->velocity.y, body->velocity.z);
}
// Convert global coordinates to local coordinates using new parent // Convert global coordinates to local coordinates using new parent
if (body->parent_index >= 0 && body->parent_index < sim->body_count) { if (body->parent_index >= 0 && body->parent_index < sim->body_count) {
CelestialBody* new_parent_body = &sim->bodies[body->parent_index]; CelestialBody* new_parent_body = &sim->bodies[body->parent_index];
@ -190,67 +153,16 @@ void update_simulation(SimulationState* sim) {
body->local_position = body->position; body->local_position = body->position;
body->local_velocity = body->velocity; body->local_velocity = body->velocity;
} }
// Debug: Print after new local coord calculation
if (strncmp(body->name, "Spacecraft", 10) == 0) {
printf("DEBUG [After new local coords]:\n");
printf(" Local pos: (%.2e, %.2e, %.2e)\n", body->local_position.x, body->local_position.y, body->local_position.z);
printf(" Local vel: (%.2e, %.2e, %.2e)\n", body->local_velocity.x, body->local_velocity.y, body->local_velocity.z);
if (new_parent >= 0 && new_parent < sim->body_count) {
CelestialBody* parent = &sim->bodies[new_parent];
printf(" New parent pos: (%.2e, %.2e, %.2e)\n", parent->position.x, parent->position.y, parent->position.z);
printf(" New parent vel: (%.2e, %.2e, %.2e)\n", parent->velocity.x, parent->velocity.y, parent->velocity.z);
}
}
} }
if (body->parent_index >= 0 && body->parent_index < sim->body_count) { if (body->parent_index >= 0 && body->parent_index < sim->body_count) {
CelestialBody* parent = &sim->bodies[body->parent_index]; CelestialBody* parent = &sim->bodies[body->parent_index];
// Debug: Print before RK4 integration
if (strncmp(body->name, "Spacecraft", 10) == 0) {
printf("DEBUG [Before RK4 integration]:\n");
printf(" Parent: %s (idx %d)\n", parent->name, body->parent_index);
printf(" Parent mass: %.2e kg\n", parent->mass);
printf(" Local pos: (%.2e, %.2e, %.2e)\n", body->local_position.x, body->local_position.y, body->local_position.z);
printf(" Local vel: (%.2e, %.2e, %.2e)\n", body->local_velocity.x, body->local_velocity.y, body->local_velocity.z);
}
rk4_step(&body->local_position, &body->local_velocity, rk4_step(&body->local_position, &body->local_velocity,
sim->dt, body->mass, parent->mass); sim->dt, body->mass, parent->mass);
// Debug: Print after RK4 integration
if (strncmp(body->name, "Spacecraft", 10) == 0) {
printf("DEBUG [After RK4 integration]:\n");
printf(" Local pos: (%.2e, %.2e, %.2e)\n", body->local_position.x, body->local_position.y, body->local_position.z);
printf(" Local vel: (%.2e, %.2e, %.2e)\n", body->local_velocity.x, body->local_velocity.y, body->local_velocity.z);
}
}
}
// Debug: Print before compute_global_coordinates for spacecraft
for (int i = 0; i < sim->body_count; i++) {
if (strncmp(sim->bodies[i].name, "Spacecraft", 10) == 0) {
CelestialBody* body = &sim->bodies[i];
printf("DEBUG [Before compute_global_coordinates]:\n");
printf(" Parent: %d\n", body->parent_index);
printf(" Local pos: (%.2e, %.2e, %.2e)\n", body->local_position.x, body->local_position.y, body->local_position.z);
printf(" Local vel: (%.2e, %.2e, %.2e)\n", body->local_velocity.x, body->local_velocity.y, body->local_velocity.z);
} }
} }
compute_global_coordinates(sim); compute_global_coordinates(sim);
// Debug: Print after compute_global_coordinates for spacecraft
for (int i = 0; i < sim->body_count; i++) {
if (strncmp(sim->bodies[i].name, "Spacecraft", 10) == 0) {
CelestialBody* body = &sim->bodies[i];
printf("DEBUG [After compute_global_coordinates]:\n");
printf(" Global pos: (%.2e, %.2e, %.2e)\n", body->position.x, body->position.y, body->position.z);
printf(" Global vel: (%.2e, %.2e, %.2e)\n", body->velocity.x, body->velocity.y, body->velocity.z);
}
}
sim->time += sim->dt; sim->time += sim->dt;
} }

Write Preview
Loading…
Cancel
Save