Aerospace MCP

Instructions

Implementation Reference

• aerospace_mcp/tools/aerodynamics.py:137-157 (handler)

  The primary handler function for the MCP tool 'calculate_stability_derivatives'. It wraps the core implementation from integrations.aero, handles errors, and returns a formatted JSON string response.

  def calculate_stability_derivatives(wing_config: dict, flight_conditions: dict) -> str:
      """Calculate basic longitudinal stability derivatives for a wing.
  
      Args:
          wing_config: Wing configuration parameters
          flight_conditions: Flight conditions
  
      Returns:
          JSON string with stability derivatives
      """
      try:
          from ..integrations.aero import calculate_stability_derivatives as _stability
  
          result = _stability(wing_config, flight_conditions)
          return json.dumps(result, indent=2)
  
      except ImportError:
          return "Stability analysis not available - install aerodynamics packages"
      except Exception as e:
          logger.error(f"Stability analysis error: {str(e)}", exc_info=True)
          return f"Stability analysis error: {str(e)}"

• aerospace_mcp/fastmcp_server.py:102-102 (registration)

  Registration of the 'calculate_stability_derivatives' tool in the FastMCP server.

  mcp.tool(calculate_stability_derivatives)

• aerospace_mcp/integrations/aero.py:435-474 (helper)

  Core implementation of stability derivatives calculation using simplified lifting line theory approximations, including lift curve slope (CL_alpha) and pitching moment slope (CM_alpha). Accepts WingGeometry and flight conditions.

  def calculate_stability_derivatives(
      geometry: WingGeometry, alpha_deg: float = 2.0, mach: float = 0.2
  ) -> StabilityDerivatives:
      """
      Calculate basic longitudinal stability derivatives.
  
      Args:
          geometry: Wing geometry
          alpha_deg: Reference angle of attack
          mach: Mach number
  
      Returns:
          StabilityDerivatives object
      """
      # Calculate wing area and aspect ratio
      S = geometry.span_m * (geometry.chord_root_m + geometry.chord_tip_m) / 2
      AR = geometry.span_m**2 / S
  
      # Get airfoil data
      airfoil_data = AIRFOIL_DATABASE.get(
          geometry.airfoil_root, AIRFOIL_DATABASE["NACA2412"]
      )
  
      # 3D lift curve slope
      e = 0.85  # Oswald efficiency
      beta = math.sqrt(max(0.01, 1 - mach**2))
      CL_alpha_2d = airfoil_data["cl_alpha"]
      CL_alpha = CL_alpha_2d / (1 + CL_alpha_2d / (math.pi * AR * e)) / beta
  
      # Pitching moment slope (simplified)
      # Typically negative for stable aircraft
      CM_alpha = -0.1 * CL_alpha  # Rough approximation
  
      return StabilityDerivatives(
          CL_alpha=CL_alpha,
          CM_alpha=CM_alpha,
          CL_alpha_dot=None,  # Would need unsteady analysis
          CM_alpha_dot=None,
      )

• aerospace_mcp/integrations/aero.py:121-128 (schema)

  Pydantic schema for output stability derivatives (CL_alpha, CM_alpha, etc.).

  class StabilityDerivatives(BaseModel):
      """Longitudinal stability derivatives."""
  
      CL_alpha: float = Field(..., description="Lift curve slope (per radian)")
      CM_alpha: float = Field(..., description="Pitching moment curve slope")
      CL_alpha_dot: float | None = Field(None, description="CL due to alpha rate")
      CM_alpha_dot: float | None = Field(None, description="CM due to alpha rate")

• aerospace_mcp/integrations/aero.py:91-108 (schema)

  Pydantic schema for input wing geometry used in stability derivatives and other aero analyses.

  class WingGeometry(BaseModel):
      """Wing planform geometry definition."""
  
      span_m: float = Field(..., gt=0, description="Wing span in meters")
      chord_root_m: float = Field(..., gt=0, description="Root chord in meters")
      chord_tip_m: float = Field(..., gt=0, description="Tip chord in meters")
      sweep_deg: float = Field(
          0.0, ge=-45, le=45, description="Quarter-chord sweep in degrees"
      )
      dihedral_deg: float = Field(
          0.0, ge=-15, le=15, description="Dihedral angle in degrees"
      )
      twist_deg: float = Field(
          0.0, ge=-10, le=10, description="Geometric twist (tip relative to root)"
      )
      airfoil_root: str = Field("NACA2412", description="Root airfoil name")
      airfoil_tip: str = Field("NACA2412", description="Tip airfoil name")