Aerospace MCP

"""Rocket trajectory and performance analysis tools for the Aerospace MCP server.""" import json import logging from typing import Literal logger = logging.getLogger(__name__) def rocket_3dof_trajectory( rocket_geometry: dict, launch_conditions: dict, simulation_options: dict | None = None, ) -> str: """Calculate 3DOF rocket trajectory using numerical integration. Args: rocket_geometry: Rocket geometry parameters launch_conditions: Launch conditions (launch_angle_deg, launch_site, etc.) simulation_options: Optional simulation settings Returns: Formatted string with trajectory analysis results """ try: from ..integrations.rockets import ( RocketGeometry, ) from ..integrations.rockets import ( rocket_3dof_trajectory as _trajectory_analysis, ) # Create geometry object geometry = RocketGeometry(**rocket_geometry) # Run trajectory analysis result = _trajectory_analysis(geometry, launch_conditions, simulation_options) # Format response result_lines = [ "3DOF Rocket Trajectory Analysis", "=" * 50, f"Rocket: {geometry.length_m:.1f}m long, {geometry.diameter_m:.2f}m dia", f"Mass: {geometry.dry_mass_kg:.1f} kg dry + {geometry.propellant_mass_kg:.1f} kg prop", f"Launch Angle: {launch_conditions.get('launch_angle_deg', 90):.1f}°", "", "Performance Summary:", f" Max Altitude: {result.performance.max_altitude_m:.0f} m ({result.performance.max_altitude_m / 1000:.2f} km)", f" Max Velocity: {result.performance.max_velocity_ms:.1f} m/s (Mach {result.performance.max_mach:.2f})", f" Apogee Time: {result.performance.apogee_time_s:.1f} s", f" Burnout Time: {result.performance.burnout_time_s:.1f} s", f" Max Q: {result.performance.max_q_pa / 1000:.1f} kPa", f" Total Impulse: {result.performance.total_impulse_ns:.0f} N⋅s", f" Specific Impulse: {result.performance.specific_impulse_s:.1f} s", ] # Add trajectory points summary if hasattr(result, "trajectory") and result.trajectory: result_lines.extend( [ "", "Key Trajectory Points:", f"{'Time (s)':>8} {'Alt (m)':>8} {'Vel (m/s)':>10} {'Accel (m/s²)':>12}", ] ) result_lines.append("-" * 45) # Sample key points trajectory = result.trajectory sample_indices = [ 0, len(trajectory) // 4, len(trajectory) // 2, 3 * len(trajectory) // 4, -1, ] for i in sample_indices: if i < len(trajectory): point = trajectory[i] result_lines.append( f"{point.time_s:8.1f} {point.altitude_m:8.0f} {point.velocity_ms:10.1f} " f"{point.acceleration_ms2:12.1f}" ) # Add JSON data json_data = json.dumps( { "performance": { "max_altitude_m": result.performance.max_altitude_m, "max_velocity_ms": result.performance.max_velocity_ms, "apogee_time_s": result.performance.apogee_time_s, "burnout_time_s": result.performance.burnout_time_s, "max_q_pa": result.performance.max_q_pa, "total_impulse_ns": result.performance.total_impulse_ns, "specific_impulse_s": result.performance.specific_impulse_s, } }, indent=2, ) result_lines.extend(["", "JSON Performance Data:", json_data]) return "\n".join(result_lines) except ImportError: return "Rocket trajectory analysis not available - install rocketry packages" except Exception as e: logger.error(f"Rocket trajectory error: {str(e)}", exc_info=True) return f"Rocket trajectory error: {str(e)}" def estimate_rocket_sizing( target_altitude_m: float, payload_mass_kg: float, propellant_type: Literal["solid", "liquid"] = "solid", design_margin: float = 1.2, ) -> str: """Estimate rocket sizing requirements for target altitude and payload. Args: target_altitude_m: Target altitude in meters payload_mass_kg: Payload mass in kg propellant_type: Propellant type ('solid' or 'liquid') design_margin: Design margin factor Returns: JSON string with sizing estimates """ try: from ..integrations.rockets import estimate_rocket_sizing as _sizing result = _sizing( target_altitude_m, payload_mass_kg, propellant_type, design_margin ) return json.dumps(result, indent=2) except ImportError: return "Rocket sizing not available - install rocketry packages" except Exception as e: logger.error(f"Rocket sizing error: {str(e)}", exc_info=True) return f"Rocket sizing error: {str(e)}" def optimize_launch_angle( rocket_geometry: dict, target_range_m: float | None = None, optimize_for: Literal["altitude", "range"] = "altitude", angle_bounds_deg: tuple[float, float] = (45.0, 90.0), ) -> str: """Optimize rocket launch angle for maximum altitude or range. Args: rocket_geometry: Rocket geometry parameters target_range_m: Optional target range in meters optimize_for: Optimization objective ('altitude' or 'range') angle_bounds_deg: Launch angle bounds in degrees Returns: JSON string with optimization results """ try: from ..integrations.rockets import ( RocketGeometry, ) from ..integrations.rockets import ( optimize_launch_angle as _optimize, ) geometry = RocketGeometry(**rocket_geometry) result = _optimize(geometry, target_range_m, optimize_for, angle_bounds_deg) return json.dumps(result, indent=2) except ImportError: return "Launch optimization not available - install optimization packages" except Exception as e: logger.error(f"Launch optimization error: {str(e)}", exc_info=True) return f"Launch optimization error: {str(e)}"