Model Rocket Performance Analysis Platform
(IEEE Aerospace Conference)

IEEE

Abstract

This research paper presents a comprehensive, web-based computational platform developed for model rocket design and flight dynamics analyses. Designed as an alternative to the accessibility limitations of traditional commercial software, the platform has been developed using the TypeScript language under the Angular 20.x.x framework. The system houses 15 separate analytical modules addressing critical aspects of rocket performance. The platform's computational accuracy has been confirmed with an overall accuracy rate of 87.2% in validation tests against reference MATLAB simulations. This system provides a robust and accessible analysis infrastructure that serves a wide range of applications from engineering education to R&D projects.

1. System Architecture and Technological Foundations

Model rocket analyses require information from multiple engineering disciplines such as aerodynamics, structural mechanics, and control systems. The platform's architecture has been designed to present these complex calculations in a secure and modular structure.

1.1 Technology Stack

The platform's software stack focuses on creating high-performance web applications:

  • Frontend and Development Language: Angular has been used for a modular and scalable structure, and TypeScript's static type checking feature has been utilized for the reliability of mathematical algorithms.
  • Computational Standard: All mathematical operations are performed in the internationally valid MKS (SI) unit system, eliminating potential errors from unit conversion.
  • Data Visualization and Reporting: The Chart.js library has been integrated for real-time graphical outputs; automatic reporting capability with jsPDF has been provided for professional documentation of analysis results.

2. Multidisciplinary Analysis Capability

The platform provides a comprehensive solution with 15 modules of rocket design divided into two main categories: Trajectory Analyses (8 modules) and Structural Analyses (7 modules).

2.1 Trajectory and Performance Analyses

These modules examine flight dynamics and performance optimization:

  • Trajectory Analysis: The time integration of the flight profile is performed using the Forward Euler Numerical Integration method based on Newton's Second Law. The International Standard Atmosphere (ISA) model is applied for atmospheric parameters.
  • Static Stability Analysis: The rocket's aerodynamic stability is analyzed using the Barrowman Methodology along with Mach number-dependent coefficient corrections, and the Static Margin value is determined.
  • Monte Carlo Landing Analysis: Monte Carlo Simulation is applied to evaluate the effects of uncertainties in the landing area (wind speed, parachute performance, etc.). This calculates the Probability Distribution and Confidence Ellipse of the landing point, providing critical data for risk management.
  • Six Degrees of Freedom (6-DOF) Analysis: Models the rocket's complete 3D motion in space, examining pitch, yaw, and roll dynamics.

2.2 Structural Integrity Analyses

These modules guarantee the rocket's strength and integrity:

  • Composite Material Analysis: Classical Lamination Theory (CLT) is used in the analysis of multi-layered laminate structures. Effective material properties ($E_{eff}, G_{eff}$) of layers and failure criteria (Tsai-Hill, Tsai-Wu) are calculated.
  • Buckling Analysis: The structural stability of the rocket body under axial pressure is analyzed based on classical shell theory, and critical buckling loads are calculated.
  • Optimization Analysis: Using the Nelder-Mead algorithm, the rocket's mass distribution and aerodynamic ratios are optimized according to multi-objective design criteria such as reaching a specific altitude target.

3. Validation and Computational Reliability

All analytical algorithms in the platform have been developed and validated primarily in the MATLAB environment, which is a high-reliability reference application.

  • Validation Methodology: The platform's computational results have been tested against MATLAB reference results using Mean Absolute Percentage Error (MAPE) metrics.
  • Accuracy Result: The overall computational accuracy rate obtained has been determined as 87.2%. This rate indicates an acceptable performance level for academic and industrial modeling applications.

4. Conclusion and Future Perspectives

The Model Rocket Performance Analysis Platform is a significant advancement that democratizes complex engineering analyses and makes them accessible through web technologies. Thanks to its high modularity and proven computational reliability, it provides an indispensable decision support system, especially for teams participating in university rocket competitions and academic research groups.
Future development work will focus on upgrading numerical integration methods to the Runge-Kutta method and integrating machine learning-supported optimization algorithms to increase computational speed.