OpenEngineering Toolkit 📐🚀

Transparent, verified computational engineering mechanics, aerospace sizing, fluid dynamics, and rocket propulsion library for Python.

Includes Command-Line Interface (openeng), REST API (FastAPI), and Model Context Protocol (MCP) server for seamless integration with AI coding agents (Claude Desktop, Cursor, Antigravity).

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🛠️ Architecture Overview

flowchart TD
    User([Engineer / AI Agent]) --> Interface{Interface}
    Interface -->|CLI| CLI[openeng CLI]
    Interface -->|JSON-RPC| MCP[MCP Server stdio]
    Interface -->|HTTP/REST| API[FastAPI Endpoints]
    Interface -->|Python Import| PythonLib[Core Library API]

    CLI --> Core
    MCP --> Core
    API --> Core
    PythonLib --> Core

    subgraph Core[OpenEngineering Core Engine]
        prop[Propulsion Module<br/>Tsiolkovsky Delta-v, c*, Thrust Coeff, Nozzle F]
        fluids[Fluids Module<br/>Reynolds No, Dynamic Pressure q, Mach, Haaland Friction]
        aero[Aerospace Module<br/>Wing Loading W/S, Aspect Ratio, T/W Ratio]
        beam[Solid Mechanics Module<br/>Euler-Bernoulli Deflection, Bending Stress, FoS]
        units[Dimensional Analysis<br/>Length, Force, Pressure Conversions]
    end

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🚀 Key Modules & Analytical Capabilities

1. Rocket Propulsion (openengineering.propulsion)

• Tsiolkovsky Delta-V: $\Delta v = I_{sp} g_0 \ln\left(rac{m_0}{m_f} ight)$ with strict propellant fraction validation.
• Characteristic Exhaust Velocity ($c^*$): Theoretical chamber speed from gas heat ratio $\gamma$, molecular weight, and chamber temperature $T_c$.
• Nozzle Thrust Coefficient ($C_F$): Evaluates momentum expansion and pressure mismatch terms $(p_e - p_a)/p_c \cdot \epsilon$.
• Total Thrust Force: $F = \dot{m} v_e + (p_e - p_a) A_e$.

2. Fluid Dynamics & Aerodynamics (openengineering.fluids & aerospace)

• Reynolds Number: $Re = rac{ ho v L}{\mu}$ for boundary layer regime identification (laminar vs turbulent).
• Dynamic Pressure: $q = rac{1}{2} ho v^2$.
• Compressible Flow Mach Number: $M = rac{v}{\sqrt{\gamma R T}}$ and total-to-static pressure ratio $P_0/P$.
• Haaland Turbulent Pipe Friction: Explicit Darcy friction factor $f$.
• Aircraft Preliminary Sizing: Wing loading $W/S$, geometric aspect ratio $b^2/S$, and thrust-to-weight $T/W$.

3. Compressible Gas Dynamics & Shock Waves (openengineering.compressible)

• Isentropic Ratios: Total-to-static temperature ($T_0/T$), total-to-static density ($\rho_0/\rho$), and sonic throat area ratio ($A/A^*$) for nozzle expansion.
• 1D Normal Shock Mechanics (Rankine-Hugoniot): Downstream Mach $M_2$, static pressure jump $P_2/P_1$, and total pressure loss $P_{02}/P_{01}$.
• Prandtl-Meyer Supersonic Expansion: Exact expansion angle $\nu(M)$ in degrees for supersonic flow around convex corners.
• API & MCP: Exposed at /fluids/compressible/ and via openeng_compressible_isentropic & openeng_normal_shock tools.

4. Structural Mechanics & Beams (openengineering.beam & mechanics)

• Euler-Bernoulli Simply-Supported Deflection: $\delta_{\max} = \frac{P L^3}{48 E I}$.
• Maximum Bending Stress: $\sigma = \frac{|M| c}{I}$.
• Factor of Safety: $FoS = \frac{\sigma_{\text{allowable}}}{\sigma_{\text{actual}}}$.

5. Verified Dimensional Analysis (openengineering.units)

• Robust SI, Imperial, and US Customary unit conversions for Length (m, mm, ft, in), Force (N, kN, lbf), and Pressure (Pa, kPa, MPa, bar, psi, atm).

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⚡ Quick Start

Installation

# Clone and install in editable mode with all dev & API tools
git clone https://github.com/perfectalone375/openengineering-toolkit.git
cd openengineering-toolkit
pip install -e ".[api,dev]"

Python API Example

from openengineering import (
    tsiolkovsky_delta_v,
    reynolds_number,
    simply_supported_center_load_max_deflection,
    convert_pressure,
)

# 1. Rocket stage delta-v
dv = tsiolkovsky_delta_v(isp_s=320, initial_mass_kg=5000, dry_mass_kg=1200)
print(f"Stage Delta-V: {dv:.1f} m/s")

# 2. Aerodynamic Reynolds number for 1.5m wing chord at 60 m/s
re = reynolds_number(density_kg_m3=1.225, velocity_m_s=60.0, characteristic_length_m=1.5, dynamic_viscosity_pa_s=1.789e-5)
print(f"Reynolds Number: {re:.2e}")

# 3. Steel I-beam mid-span deflection under 5 kN load across 4 m span
defl = simply_supported_center_load_max_deflection(
    load_n=5000, span_m=4.0, elastic_modulus_pa=210e9, second_moment_m4=8.5e-6
)
print(f"Mid-span deflection: {defl * 1000:.3f} mm")

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💻 Command Line Interface (openeng)

# Rocket delta-v
openeng deltav --isp 311 --m0 12500 --mf 2100

# Beam deflection
openeng beam-deflection --load 2500 --span 3.5 --modulus 200e9 --inertia 2.5e-6

# Reynolds number
openeng reynolds --density 1.225 --velocity 85 --length 2.1

# Dynamic pressure
openeng q --density 1.225 --velocity 120

# Unit conversions
openeng convert --type pressure --value 35 --from-unit psi --to-unit bar

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🤖 Model Context Protocol (MCP) Integration

The toolkit includes a native stdio MCP server enabling AI coding assistants to invoke deterministic engineering formulas without hallucinations:

Claude Desktop / Cursor Config (mcp.json)

{
  "mcpServers": {
    "openengineering": {
      "command": "openeng-mcp",
      "args": []
    }
  }
}

Available MCP Tools

Tool Name	Parameters	Description
openeng_deltav	isp_s, initial_mass_kg, dry_mass_kg	Computes rocket Delta-V (m/s and km/s)
openeng_beam_deflection	load_n, span_m, elastic_modulus_pa, second_moment_m4	Computes mid-span beam deflection
openeng_reynolds	density_kg_m3, velocity_m_s, length_m, viscosity_pa_s	Computes Reynolds number and regime
openeng_unit_convert	category, value, from_unit, to_unit	Converts engineering dimensions safely

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🧪 Testing & Verification

The suite enforces 100% passing tests and strict Ruff linting across Python 3.10, 3.11, and 3.12:

# Run pytest test suite
pytest

# Run Ruff code analysis
ruff check .

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📄 License

This project is licensed under the MIT License - see the LICENSE file for details.

Developed with precision by Gopi Naga Vignesh Thirupati.