Overview

P.A.T.A.C.O.N. 1 (Plataforma Avanzada de Tecnología Aeroespacial Con Objetivo No-Orbital 1) was the first high-power rocket developed by the SpaceTech Rocketry team at Universidad de los Andes for the Colombian Collegiate Rocketry Competition (CCCD 2025). The vehicle was designed to satisfy the competition requirements while establishing the engineering processes, manufacturing capabilities, and design methodology that would become the foundation for future vehicles (Doc. 1). And take a look at the launch video Img. 3!

The rocket integrated a composite airframe, custom recovery system, CanSat payload, simulation-driven design workflow, and ground testing campaign. The project also marked the university's return to competitive rocketry after approximately six years without a student-developed launch.

Objectives

  • Design and manufacture a university rocket capable of reaching the 400 m target apogee defined by CCCD 2025.
  • Develop and validate an engineering workflow combining simulation, CAD, composite manufacturing, testing, and flight operations.
  • Integrate a functional CanSat payload while satisfying competition mass, stability, and safety requirements.
  • Establish a reusable technological platform that would serve as the first member of the P.A.T.A.C.O.N. rocket family.

Engineering

Mission Design

Vehicle requirements were derived from the CCCD 2025 competition constraints, including a target apogee of 400 m, a G80-7T motor, a maximum launch mass of 1.2 kg, and the integration of a 250–300 g CanSat payload. These requirements defined the allowable design space throughout the project.

Vehicle Design

Several vehicle configurations were evaluated using iterative CAD and OpenRocket models [1][2]. Alternatives included variable-diameter fuselages, fully composite structures, and multiple fin geometries. The selected configuration adopted a constant-diameter composite airframe with 3D-printed nose cone and couplers, balancing aerodynamic performance, manufacturability, and modularity (Img. 4).

Simulation

OpenRocket and RockSim were used throughout the design process to evaluate apogee, stability margin, rail exit velocity, and recovery timing [1][2]. Environmental conditions at the launch site were incorporated into the simulation workflow, allowing iterative optimization of vehicle geometry and mass distribution before manufacturing.

Additional CFD analyses were conducted in ANSYS Fluent [1] to study pressure distribution and aerodynamic drag (Img. 5). Mesh refinement and boundary-condition validation were used to improve convergence and establish a repeatable CFD workflow for future projects.

Structures & Manufacturing

The project included the complete development of composite manufacturing processes for aerospace structures. Carbon- and glass-fibre laminates were manufactured and mechanically characterized through ASTM D3039 tensile testing before selecting the final structural configuration (Img. 10).

The primary airframe was manufactured as a glass-fibre composite tube using hand layup techniques over an aluminum mandrel (Img. 1). Multiple manufacturing approaches were evaluated before selecting the process that provided the best compromise between dimensional accuracy, surface finish, and repeatability [2].

Recovery System

Several parachute geometries were evaluated through analytical calculations following established parachute recovery methodologies [4]. Circular and cruciform configurations were selected for prototype testing based on packing volume, drag characteristics, manufacturability, and wind sensitivity.

Payload

The rocket carried the S.U.E.R.O. (Sistema Universitario de Ensayo para Recursos Organicos) CanSat payload, which was integrated into the nose section and designed to separate after ejection to complete both the primary competition mission and secondary experimental objectives.

Results

P.A.T.A.C.O.N. 1 completed its maiden flight during CCCD 2025 and successfully validated the majority of the engineering workflow developed throughout the project, including vehicle design, manufacturing, integration, and launch operations. Although the mission did not satisfy all competition objectives, it provided valuable flight data and established the technical foundation for subsequent SpaceTech rocket developments.

  • The recovery system did not deploy due to a motor ejection failure, preventing successful recovery and resulting in an unsuccessful competition flight.
  • The S.U.E.R.O. payload SD card was recovered, allowing partial post-flight analysis despite the loss of the vehicle.
  • Recorded flight data showed that powered ascent and the ballistic coast phase closely matched pre-flight simulations, providing confidence in the vehicle design methodology.
  • The project established the engineering processes, manufacturing techniques, and simulation workflow that became the basis for later P.A.T.A.C.O.N. vehicles.

Documents

References