Aerospace MCP

"""Propeller and UAV energy analysis tools for the Aerospace MCP server.""" import json import logging logger = logging.getLogger(__name__) def propeller_bemt_analysis( propeller_geometry: dict, operating_conditions: dict, analysis_options: dict | None = None, ) -> str: """Analyze propeller performance using Blade Element Momentum Theory. Args: propeller_geometry: Propeller geometry (diameter_m, pitch_m, num_blades, etc.) operating_conditions: Operating conditions (rpm_list, velocity_ms, altitude_m) analysis_options: Optional analysis settings Returns: Formatted string with propeller performance analysis """ try: from ..integrations.propellers import ( PropellerGeometry, ) from ..integrations.propellers import ( propeller_bemt_analysis as _propeller_analysis, ) # Create geometry object geometry = PropellerGeometry(**propeller_geometry) rpm_list = operating_conditions.get("rpm_list", [2000, 2500, 3000]) velocity_ms = operating_conditions.get("velocity_ms", 20.0) altitude_m = operating_conditions.get("altitude_m", 0.0) # Run analysis results = _propeller_analysis(geometry, rpm_list, velocity_ms, altitude_m) # Format response result_lines = [ "Propeller BEMT Analysis", "=" * 60, f"Propeller: {geometry.diameter_m:.2f}m dia, {geometry.pitch_m:.2f}m pitch, {geometry.num_blades} blades", f"Conditions: {velocity_ms:.1f} m/s @ {altitude_m:.0f}m altitude", "", f"{'RPM':>6} {'Thrust (N)':>10} {'Power (W)':>9} {'Efficiency':>10} {'Adv Ratio':>10}", ] result_lines.append("-" * 60) for result in results: result_lines.append( f"{result.rpm:6.0f} {result.thrust_n:10.1f} {result.power_w:9.0f} " f"{result.efficiency:10.3f} {result.advance_ratio:10.3f}" ) # Add JSON data json_data = json.dumps( [ { "rpm": r.rpm, "thrust_n": r.thrust_n, "torque_nm": r.torque_nm, "power_w": r.power_w, "efficiency": r.efficiency, "advance_ratio": r.advance_ratio, "thrust_coefficient": r.thrust_coefficient, "power_coefficient": r.power_coefficient, } for r in results ], indent=2, ) result_lines.extend(["", "JSON Data:", json_data]) return "\n".join(result_lines) except ImportError: return "Propeller analysis not available - install propulsion packages" except Exception as e: logger.error(f"Propeller analysis error: {str(e)}", exc_info=True) return f"Propeller analysis error: {str(e)}" def uav_energy_estimate( uav_config: dict, battery_config: dict, mission_profile: dict | None = None ) -> str: """Estimate UAV flight time and energy consumption for mission planning. Args: uav_config: UAV configuration parameters battery_config: Battery configuration parameters mission_profile: Optional mission profile parameters Returns: Formatted string with energy analysis results """ try: from ..integrations.propellers import ( BatteryConfiguration, UAVConfiguration, ) from ..integrations.propellers import ( uav_energy_estimate as _energy_estimate, ) # Create configuration objects uav = UAVConfiguration(**uav_config) battery = BatteryConfiguration(**battery_config) mission = mission_profile or {} # Run analysis result = _energy_estimate(uav, battery, mission) # Determine aircraft type aircraft_type = "Fixed-Wing" if uav.wing_area_m2 else "Multirotor" # Format response result_lines = [ f"UAV Energy Analysis ({aircraft_type})", "=" * 45, f"Aircraft Mass: {uav.mass_kg:.1f} kg", f"Battery: {battery.capacity_ah:.1f} Ah @ {battery.voltage_nominal_v:.1f}V ({battery.mass_kg:.2f} kg)", ] if uav.wing_area_m2: result_lines.extend( [ f"Wing Area: {uav.wing_area_m2:.2f} m²", f"Wing Loading: {uav.mass_kg * 9.81 / uav.wing_area_m2:.1f} N/m²", ] ) elif uav.disk_area_m2: result_lines.extend( [ f"Rotor Disk Area: {uav.disk_area_m2:.2f} m²", f"Disk Loading: {uav.mass_kg * 9.81 / uav.disk_area_m2:.1f} N/m²", ] ) result_lines.extend( [ "", "Energy Analysis:", f" Battery Energy: {result.battery_energy_wh:.0f} Wh", f" Usable Energy: {result.energy_consumed_wh:.0f} Wh", f" Power Required: {result.power_required_w:.0f} W", f" System Efficiency: {result.efficiency_overall:.1%}", "", "Mission Performance:", f" Flight Time: {result.flight_time_min:.1f} minutes ({result.flight_time_min / 60:.1f} hours)", ] ) if result.range_km: result_lines.append(f" Range: {result.range_km:.1f} km") if result.hover_time_min: result_lines.append(f" Hover Time: {result.hover_time_min:.1f} minutes") # Add recommendations result_lines.extend(["", "Recommendations:"]) if result.flight_time_min < 10: result_lines.append( " ⚠ Very short flight time - consider larger battery or lighter aircraft" ) elif result.flight_time_min < 20: result_lines.append( " ⚠ Short flight time - optimize for efficiency or add battery capacity" ) elif result.flight_time_min > 120: result_lines.append( " ✓ Excellent endurance - well optimized configuration" ) else: result_lines.append(" ✓ Good flight time for mission requirements") if result.efficiency_overall < 0.7: result_lines.append(" ⚠ Low system efficiency - check motor/ESC selection") else: result_lines.append(" ✓ Good system efficiency") # Add JSON data json_data = json.dumps( { "flight_time_min": result.flight_time_min, "range_km": result.range_km, "hover_time_min": result.hover_time_min, "power_required_w": result.power_required_w, "energy_consumed_wh": result.energy_consumed_wh, "battery_energy_wh": result.battery_energy_wh, "efficiency_overall": result.efficiency_overall, }, indent=2, ) result_lines.extend(["", "JSON Data:", json_data]) return "\n".join(result_lines) except ImportError: return "UAV energy analysis not available - install propulsion packages" except Exception as e: logger.error(f"UAV energy analysis error: {str(e)}", exc_info=True) return f"UAV energy analysis error: {str(e)}" def get_propeller_database() -> str: """Get available propeller database with geometric and performance data. Returns: JSON string with propeller database """ try: from ..integrations.propellers import PROPELLER_DATABASE return json.dumps(PROPELLER_DATABASE, indent=2) except ImportError: return "Propeller database not available" except Exception as e: logger.error(f"Propeller database error: {str(e)}", exc_info=True) return f"Propeller database error: {str(e)}"