#!/usr/bin/env python3
"""Precalculate expected values for test_extreme_orientation_mixed."""

import sys
import os
import math

sys.path.insert(0, os.path.dirname(os.path.abspath(__file__)))
import sim_engine
from sim_engine import Simulator

# Load config via sim_engine (TOML 1.0 parsing + spacecraft initialization)
sim = Simulator("tests/test_extreme_orientation_mixed.toml", dt=60.0)

mu = 6.67430e-11 * 5.972e24  # Earth's gravitational parameter

print(f"# mu = {mu:.6f} m^3/s^2")
print()

for i, craft in enumerate(sim.spacecraft):
    a = craft.orbit.a
    e = craft.orbit.e
    name = craft.name

    print(f"# Spacecraft {i}: {name} (a={a}, e={e})")

    # Periapsis (nu=0)
    r_peri = a * (1.0 - e)
    v_peri = math.sqrt(mu * (2.0/r_peri - 1.0/a))
    print(f"#  nu=0: r={r_peri:.6e} m, v={v_peri:.6f} m/s")

    # Apoapsis (nu=pi)
    if e < 1.0:
        r_apo = a * (1.0 + e)
        v_apo = math.sqrt(mu * (2.0/r_apo - 1.0/a))
        print(f"#  nu=pi: r={r_apo:.6e} m, v={v_apo:.6f} m/s")

    # nu=pi/2
    r_nu90 = a * (1.0 - e*e) / (1.0 + e * math.cos(math.pi/2))
    v_nu90 = math.sqrt(mu * (2.0/r_nu90 - 1.0/a))
    print(f"#  nu=pi/2: r={r_nu90:.6e} m, v={v_nu90:.6f} m/s")

    # nu=3pi/2
    r_nu270 = a * (1.0 - e*e) / (1.0 + e * math.cos(3*math.pi/2))
    v_nu270 = math.sqrt(mu * (2.0/r_nu270 - 1.0/a))
    print(f"#  nu=3pi/2: r={r_nu270:.6e} m, v={v_nu270:.6f} m/s")

    # Round-trip check: convert to cartesian and back
    parent_mass = mu / 6.67430e-11
    pos, vel = sim_engine.orbital_to_cartesian(craft.orbit, parent_mass)
    recovered = sim_engine.cartesian_to_orbital_elements(pos, vel, parent_mass)
    print(f"#  round-trip: e_err={abs(recovered.e - e):.2e}, "
          f"i_err={abs(recovered.inc - craft.orbit.inc):.2e}, "
          f"O_err={abs(recovered.Omega - craft.orbit.Omega):.2e}, "
          f"w_err={abs(recovered.omega - craft.orbit.omega):.2e}")
    print()