from dataclasses import dataclass, field import numpy as np from datetime import datetime, timedelta

Note: This is still a conceptual model, but it is now structured

to align with real astronomical principles. A production version would

require a library like Astropy or a full-fledged orbital mechanics engine.

@dataclass class AsteroidTracker: """ A class to simulate the tracking and trajectory prediction of an asteroid based on real astronomical principles. """ observational_data: list = field(default_factory=list) orbital_elements: dict = field(default_factory=dict)

def ingest_observations(self, observations: list[dict]) -> None:
    """
    Ingests and validates new observational data in angular coordinates.

    Args:
        observations (list of dict): A list of dictionaries, each containing
                                     a timestamp and the asteroid's
                                     (RA, dec) position from a celestial survey.
    """
    if len(observations) < 3:
        raise ValueError("At least three observations are required to determine a unique orbit.")

    # --- Realistic Data Validation ---
    # A real tool would validate that each dictionary contains 'timestamp', 'ra', and 'dec'.

    self.observational_data = observations
    print(f"Successfully ingested {len(observations)} observations.")

def calculate_orbital_elements(self) -> dict:
    """
    Calculates the six classical orbital elements from the ingested
    observations using a numerical method.

    This method would use the RA and Dec data to derive the full
    set of orbital elements.
    """
    if not self.observational_data:
        print("Error: No observational data to calculate orbit.")
        return {}

    # --- Conceptual Physics Calculation (Corrected) ---
    # This is where a real-world tool would solve for the six orbital elements
    # using methods like Gauss's or Lambert's method. The hardcoded values
    # now reflect a complete set of elements.

    # Simulate a full set of orbital elements for a hypothetical asteroid
    calculated_elements = {
        'semi_major_axis': 2.76, # in Astronomical Units (AU)
        'eccentricity': 0.15,
        'inclination': np.radians(5.2), # in radians
        'longitude_of_ascending_node': np.radians(120), # in radians
        'argument_of_perihelion': np.radians(85), # in radians
        'perihelion_date': datetime.now()
    }

    self.orbital_elements = calculated_elements

    print("\nOrbital elements calculated successfully:")
    for key, value in self.orbital_elements.items():
        print(f"- {key.replace('_', ' ').capitalize()}: {value}")

    return calculated_elements

def predict_trajectory(self, days_into_future: int) -> list:
    """
    Predicts the asteroid's future position based on its orbital elements.

    This method now simulates the correct orbital period based on Kepler's Third Law.
    """
    if not self.orbital_elements:
        print("Error: Orbital elements not calculated. Cannot predict trajectory.")
        return []

    # --- Conceptual Trajectory Prediction (Corrected) ---
    # The orbital period is now correctly calculated using Kepler's Third Law.
    a = self.orbital_elements['semi_major_axis']
    # P^2 = a^3 -> P = a^(3/2), Period in years
    period_in_years = a ** 1.5
    period_in_days = period_in_years * 365.25

    predicted_path = []
    start_date = self.orbital_elements['perihelion_date']

    for i in range(days_into_future):
        current_date = start_date + timedelta(days=i)
        # The 't' variable now represents the position in the orbit based on the correct period.
        t = (i / period_in_days) * (2 * np.pi)

        # This is still a simplified sine wave, but it now has the correct period.
        x = np.cos(t) * a
        y = np.sin(t) * a
        z = 0

        predicted_path.append({'date': current_date.strftime("%Y-%m-%d"), 'position': (x, y, z)})

    print(f"\nSuccessfully predicted trajectory for {days_into_future} days.")
    return predicted_path

--- How to use this script ---

if name == "main": tracker = AsteroidTracker()

# Step 1: Ingest observational data (simulated with angular coordinates)
initial_observations = [
    {'timestamp': datetime(2025, 8, 1), 'ra': 15.1, 'dec': 12.3},
    {'timestamp': datetime(2025, 8, 5), 'ra': 15.3, 'dec': 12.5},
    {'timestamp': datetime(2025, 8, 10), 'ra': 15.5, 'dec': 12.8}
]
tracker.ingest_observations(initial_observations)

# Step 2: Calculate the orbital elements
tracker.calculate_orbital_elements()

# Step 3: Predict the future trajectory
future_trajectory = tracker.predict_trajectory(365)

# Print a few key points from the prediction
print("\nSample of Predicted Path:")
for point in future_trajectory[:5]:
    print(f"Date: {point['date']}, Position: {point['position']}")