You can not select more than 25 topics
Topics must start with a letter or number, can include dashes ('-') and can be up to 35 characters long.
189 lines
6.8 KiB
189 lines
6.8 KiB
#!/usr/bin/env python3 |
|
""" |
|
Precalculate expected values for test_maneuvers.cpp refactoring. |
|
Uses sim_engine.py for physics propagation. |
|
""" |
|
|
|
import math |
|
import sys |
|
sys.path.insert(0, "/home/agent/dev/claudes_game") |
|
from scripts.sim_engine import * |
|
|
|
|
|
def main(): |
|
dt = 60.0 |
|
sim = Simulator("tests/test_maneuvers.toml", dt=dt) |
|
craft = sim.spacecraft[0] |
|
earth = sim.bodies[1] |
|
|
|
# ========================================================================= |
|
# Test 1: Basic loading |
|
# ========================================================================= |
|
print("// === Test 1: Spacecraft loading from config ===") |
|
print(f"// craft_count = {len(sim.spacecraft)}") |
|
print(f"// craft[0].name = \"{craft.name}\"") |
|
print(f"// craft[0].parent_index = {craft.parent_index}") |
|
print() |
|
|
|
# ========================================================================= |
|
# Test 2: Prograde burn |
|
# ========================================================================= |
|
sim2 = Simulator("tests/test_maneuvers.toml", dt=dt) |
|
craft2 = sim2.spacecraft[0] |
|
v0 = vmag(craft2.local_vel) |
|
r0 = vmag(craft2.local_pos) |
|
|
|
apply_impulsive_burn(craft2, BurnDirection.PROGRADE, 100.0, earth.mass) |
|
v_after = vmag(craft2.local_vel) |
|
|
|
# Simulate 3600s |
|
steps = int(3600.0 / dt) |
|
for _ in range(steps): |
|
sim2._step() |
|
sim2.time += sim2.dt |
|
r_final = vmag(craft2.local_pos) |
|
|
|
print("// === Test 2: Prograde burn ===") |
|
print(f"// initial_velocity = {v0:.4f}") |
|
print(f"// velocity_after_burn = {v_after:.4f}") |
|
print(f"// delta_v = {v_after - v0:.4f}") |
|
print(f"// initial_local_r = {r0:.4f}") |
|
print(f"// final_local_r (t=3600s) = {r_final:.4f}") |
|
print(f"// delta_r = {r_final - r0:.4f}") |
|
print() |
|
|
|
# ========================================================================= |
|
# Test 3: Retrograde burn |
|
# ========================================================================= |
|
sim3 = Simulator("tests/test_maneuvers.toml", dt=dt) |
|
craft3 = sim3.spacecraft[0] |
|
v0r = vmag(craft3.local_vel) |
|
r0r = vmag(craft3.local_pos) |
|
|
|
apply_impulsive_burn(craft3, BurnDirection.RETROGRADE, 100.0, earth.mass) |
|
v_after_r = vmag(craft3.local_vel) |
|
|
|
for _ in range(steps): |
|
sim3._step() |
|
sim3.time += sim3.dt |
|
r_final_r = vmag(craft3.local_pos) |
|
|
|
print("// === Test 3: Retrograde burn ===") |
|
print(f"// initial_velocity = {v0r:.4f}") |
|
print(f"// velocity_after_burn = {v_after_r:.4f}") |
|
print(f"// delta_v = {v_after_r - v0r:.4f}") |
|
print(f"// initial_local_r = {r0r:.4f}") |
|
print(f"// final_local_r (t=3600s) = {r_final_r:.4f}") |
|
print(f"// delta_r = {r_final_r - r0r:.4f}") |
|
print() |
|
|
|
# ========================================================================= |
|
# Test 4: Normal burn |
|
# ========================================================================= |
|
sim4 = Simulator("tests/test_maneuvers.toml", dt=dt) |
|
craft4 = sim4.spacecraft[0] |
|
z0 = craft4.local_pos[2] |
|
|
|
apply_impulsive_burn(craft4, BurnDirection.NORMAL, 500.0, earth.mass) |
|
|
|
for _ in range(steps): |
|
sim4._step() |
|
sim4.time += sim4.dt |
|
z_final = craft4.local_pos[2] |
|
z_change = abs(z_final - z0) |
|
|
|
print("// === Test 4: Normal burn ===") |
|
print(f"// initial_z = {z0:.4f}") |
|
print(f"// final_z (t=3600s) = {z_final:.4f}") |
|
print(f"// |z_change| = {z_change:.4f}") |
|
print() |
|
|
|
# ========================================================================= |
|
# Test 5: Custom burn |
|
# ========================================================================= |
|
sim5 = Simulator("tests/test_maneuvers.toml", dt=dt) |
|
craft5 = sim5.spacecraft[0] |
|
iv5 = craft5.local_vel |
|
|
|
apply_custom_burn(craft5, (10.0, 20.0, 30.0)) |
|
|
|
print("// === Test 5: Custom burn ===") |
|
print(f"// initial_vel = ({iv5[0]:.4f}, {iv5[1]:.4f}, {iv5[2]:.4f})") |
|
print(f"// final_vel = ({craft5.local_vel[0]:.4f}, {craft5.local_vel[1]:.4f}, {craft5.local_vel[2]:.4f})") |
|
print(f"// dx = {craft5.local_vel[0] - iv5[0]:.4f}") |
|
print(f"// dy = {craft5.local_vel[1] - iv5[1]:.4f}") |
|
print(f"// dz = {craft5.local_vel[2] - iv5[2]:.4f}") |
|
print() |
|
|
|
# ========================================================================= |
|
# Test 6: Propagation stability (1 day) |
|
# ========================================================================= |
|
sim6 = Simulator("tests/test_maneuvers.toml", dt=dt) |
|
craft6 = sim6.spacecraft[0] |
|
r0_6 = vmag(craft6.local_pos) |
|
a0_6 = craft6.orbit.a |
|
e0_6 = craft6.orbit.e |
|
|
|
total_time = 86400.0 |
|
steps6 = int(total_time / dt) |
|
for _ in range(steps6): |
|
sim6._step() |
|
sim6.time += sim6.dt |
|
r_final_6 = vmag(craft6.local_pos) |
|
a_final_6 = craft6.orbit.a |
|
e_final_6 = craft6.orbit.e |
|
drift_pct = abs(r_final_6 - r0_6) / r0_6 * 100.0 |
|
a_drift_pct = abs(a_final_6 - a0_6) / a0_6 * 100.0 |
|
|
|
print("// === Test 6: Propagation stability (1 day) ===") |
|
print(f"// initial_local_r = {r0_6:.4f}") |
|
print(f"// final_local_r (t=86400s) = {r_final_6:.4f}") |
|
print(f"// distance_drift_pct = {drift_pct:.10f}%") |
|
print(f"// initial_a = {a0_6:.4f}") |
|
print(f"// final_a = {a_final_6:.4f}") |
|
print(f"// a_drift_pct = {a_drift_pct:.10f}%") |
|
print(f"// initial_e = {e0_6:.10f}") |
|
print(f"// final_e = {e_final_6:.10f}") |
|
print() |
|
|
|
# ========================================================================= |
|
# Test 7: State vectors at orbital quarters |
|
# ========================================================================= |
|
sim7 = Simulator("tests/test_maneuvers.toml", dt=dt) |
|
craft7 = sim7.spacecraft[0] |
|
|
|
orbit_radius = vmag(craft7.local_pos) |
|
period = 2 * math.pi * math.sqrt(orbit_radius**3 / (G * earth.mass)) |
|
quarter_time = period / 4 |
|
steps_per_quarter = int(quarter_time / dt) |
|
|
|
print("// === Test 7: State vectors at orbital quarters ===") |
|
print(f"// orbit_radius = {orbit_radius:.4f}") |
|
print(f"// orbital_period = {period:.4f} s ({period/3600:.4f} hours)") |
|
print(f"// steps_per_quarter = {steps_per_quarter}") |
|
|
|
for q in range(5): |
|
angle = math.atan2(craft7.local_pos[1], craft7.local_pos[0]) |
|
if angle < 0: |
|
angle += 2 * math.pi |
|
r_q = vmag(craft7.local_pos) |
|
v_q = vmag(craft7.local_vel) |
|
print(f"// Q{q}: angle={math.degrees(angle):.4f}°, r={r_q:.4f}, v={v_q:.4f}") |
|
|
|
if q < 4: |
|
for _ in range(steps_per_quarter): |
|
sim7._step() |
|
sim7.time += sim7.dt |
|
|
|
# Full rotation check |
|
final_angle = math.atan2(craft7.local_pos[1], craft7.local_pos[0]) |
|
if final_angle < 0: |
|
final_angle += 2 * math.pi |
|
total_deg = math.degrees(final_angle) |
|
print(f"// total_rotation = {total_deg:.4f}° = {final_angle:.6f} rad") |
|
print(f"// angle_change_per_quarter = {(total_deg / 4):.4f}°") |
|
print() |
|
|
|
|
|
if __name__ == "__main__": |
|
main()
|
|
|