#!/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.global_pos)

    apply_impulsive_burn(craft2, BurnDirection.PROGRADE, 100.0, earth.mass)
    v_after = vmag(craft2.local_vel)

    # Simulate 3600s
    steps = int(3600.0 / dt)
    sim2.run(steps)
    r_final = vmag(craft2.global_pos)

    print("// === Test 2: Prograde burn increases orbital energy ===")
    print(f"// initial_velocity = {v0:.4f}")
    print(f"// velocity_after_burn = {v_after:.4f}")
    print(f"// initial_distance = {r0:.4f}")
    print(f"// final_distance (t=3600s) = {r_final:.4f}")
    print(f"// distance_change = {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.global_pos)

    apply_impulsive_burn(craft3, BurnDirection.RETROGRADE, 100.0, earth.mass)
    v_after_r = vmag(craft3.local_vel)

    sim3.run(steps)
    r_final_r = vmag(craft3.global_pos)

    print("// === Test 3: Retrograde burn decreases orbital energy ===")
    print(f"// initial_velocity = {v0r:.4f}")
    print(f"// velocity_after_burn = {v_after_r:.4f}")
    print(f"// initial_distance = {r0r:.4f}")
    print(f"// final_distance (t=3600s) = {r_final_r:.4f}")
    print(f"// distance_change = {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)

    sim4.run(steps)
    z_final = craft4.local_pos[2]
    z_change = abs(z_final - z0)

    print("// === Test 4: Normal burn changes orbital plane ===")
    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 applies arbitrary delta-v ===")
    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.global_pos)

    total_time = 86400.0
    steps6 = int(total_time / dt)
    sim6.run(steps6)
    r_final_6 = vmag(craft6.global_pos)
    drift_pct = abs(r_final_6 - r0_6) / r0_6 * 100.0

    print("// === Test 6: Propagation stability (1 day) ===")
    print(f"// initial_distance = {r0_6:.4f}")
    print(f"// final_distance (t=86400s) = {r_final_6:.4f}")
    print(f"// distance_drift_pct = {drift_pct:.6f}%")
    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 = 2.0 * math.pi * math.sqrt(orbit_radius**3 / (G * earth.mass))
    quarter_time = period / 4.0
    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()

    # Full rotation check
    final_angle = math.atan2(craft7.local_pos[1], craft7.local_pos[0])
    if final_angle < 0:
        final_angle += 2 * math.pi
    print(f"// total_rotation = {math.degrees(final_angle):.4f}°")
    print()


if __name__ == "__main__":
    main()