import os
import logging
from . import core as core
from .core import IAgStkObjectRoot, IAgScenario
from .utils import timed_operation
from .config import get_config
logger = logging.getLogger(__name__)
# Import STK Objects specific to satellite creation if available (Windows Desktop/Engine)
AgESTKObjectType = None
AgEVePropagatorType = None
AgEClassicalLocation = None
satellite_capable = False
if core.stk_available and os.name == 'nt':
try:
from agi.stk12.stkobjects import (
AgESTKObjectType as AgESTKObjectTypeImport,
AgEVePropagatorType as AgEVePropagatorTypeImport,
AgEClassicalLocation as AgEClassicalLocationImport,
)
AgESTKObjectType = AgESTKObjectTypeImport
AgEVePropagatorType = AgEVePropagatorTypeImport
AgEClassicalLocation = AgEClassicalLocationImport
satellite_capable = True
except ImportError:
logger.warning("Could not import STK COM types for satellite creation (Windows only feature).")
except Exception as e:
logger.error("Error importing STK enums: %s", e)
cfg = get_config()
EARTH_RADIUS_KM = cfg.earth_radius_km
@timed_operation
def create_satellite_internal(
stk_root: IAgStkObjectRoot, # Although not directly used, good for context
scenario: IAgScenario,
name: str,
apogee_alt_km: float,
perigee_alt_km: float,
raan_deg: float,
inclination_deg: float,
):
"""
Internal logic to create/configure an STK satellite.
Returns:
tuple: (success_flag, status_message, satellite_object_or_None)
Raises:
ValueError: If input parameters are invalid (e.g., apogee < perigee).
Exception: For COM or other STK errors.
"""
if not core.stk_available or not scenario or not satellite_capable:
raise RuntimeError("STK modules or active scenario not available/initialized.")
if AgESTKObjectType is None or AgEVePropagatorType is None or AgEClassicalLocation is None:
raise RuntimeError("Required STK Object Enums not imported.")
logger.info(" Attempting internal satellite creation/configuration: %s", name)
if apogee_alt_km < perigee_alt_km:
raise ValueError("Apogee altitude cannot be less than Perigee altitude.")
# --- Calculate Semi-Major Axis (a) and Eccentricity (e) ---
radius_apogee_km = apogee_alt_km + EARTH_RADIUS_KM
radius_perigee_km = perigee_alt_km + EARTH_RADIUS_KM
semi_major_axis_km = (radius_apogee_km + radius_perigee_km) / 2.0
denominator = radius_apogee_km + radius_perigee_km
eccentricity = 0.0 if denominator == 0 else (radius_apogee_km - radius_perigee_km) / denominator
logger.debug(" Calculated Semi-Major Axis (a): %.3f km", semi_major_axis_km)
logger.debug(" Calculated Eccentricity (e): %.6f", eccentricity)
# --- Get or Create Satellite Object ---
scenario_children = scenario.Children
satellite = None
if not scenario_children.Contains(AgESTKObjectType.eSatellite, name):
logger.info(" Creating new Satellite object: %s", name)
satellite = scenario_children.New(AgESTKObjectType.eSatellite, name)
else:
logger.info(" Satellite '%s' already exists. Getting reference.", name)
satellite = scenario_children.Item(name)
if satellite is None:
raise Exception(f"Failed to create or retrieve satellite object '{name}'.")
# --- Set Propagator to TwoBody ---
logger.info(" Setting propagator to TwoBody...")
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorTwoBody)
# In the new STK API, interfaces are directly accessible at runtime.
# We do not need to cast 'satellite.Propagator' to 'IAgVePropagatorTwoBody'.
propagator_twobody = satellite.Propagator
# --- Define Orbital Elements ---
argp_deg = 0.0 # Assumed
true_anom_deg = 0.0 # Assumed (starts at perigee)
logger.info(" Assigning Classical Elements (J2000):")
# (Print statements omitted for brevity, add back if desired)
# Similarly, we access the interface directly.
orbit_state = propagator_twobody.InitialState.Representation
classical_elements = orbit_state
if classical_elements:
classical_elements.AssignClassical(
AgEClassicalLocation.eCoordinateSystemJ2000,
semi_major_axis_km, eccentricity, inclination_deg,
argp_deg, raan_deg, true_anom_deg
)
else:
raise Exception("Failed to access orbit state representation.")
# --- Propagate the Orbit ---
logger.info(" Propagating orbit...")
propagator_twobody.Propagate()
logger.info(" Internal satellite configuration for '%s' complete.", name)
# Return success flag, message, and the object
return True, f"Successfully created/configured satellite: '{satellite.InstanceName}'", satellite
