Devesh Vyas

Aerospace Engineer (B.Tech Aerospace Eng, 2026) with 1.5 years of applied propulsion experience (3 months full-time, 15 months internships) focused on the end-to-end development of propulsion systems. Strong background in both fluid dynamics simulation and physical hardware testing, combining ISRO-funded resonance ignition system research & testing with hands-on Solid Rocket Motor (SRM) and RATO static fire test campaigns. Currently developing the pyrotechnic fasteners and initiated and leading preliminary micro-missile design while actively upskilling in cryogenic engineering and structural analysis.

Proficient in software ANSYS Fluent, SolidWorks, Autodesk Fusion 360, OpenRocket, and MATLAB.

Propulsion GET at Machfly Aerospace Technologies (2026-07 – Present)

• Micro-Missile: Initiated and currently leading preliminary configuration for a micro-missile project, optimizing aerodynamic stability and CG/CP margins to achieve a target range of 5 km and using OpenRocket and full-body aerodynamic simulations.
• Pyrotechnics Fasteners: Designed and validated a pyrobolt separation mechanism for reliable ejection within 20 milliseconds; performed explosive charge sizing, detonation calculations, and Explicit Dynamics analysis under 6 kN of structural load.
• Hardware Testing: Executed 6 successful Solid Rocket Motor (SRM) static fires and RATO ejection tests generating up to 2 kN of thrust to validate theoretical performance and mechanical separation sequences.
• Composite Manufacturing: Fabricated lightweight carbon fiber composite components for drone applications, including airframes, wing sections, and outer body shells.

Propulsion Intern (2026-01 – 2026-06)

• Performance Analysis: Accelerated a 6-month propellant grain performance analysis, completing the baseline evaluation in 2 weeks to fast-track performance analysis to evaluate the environmental condition on propellant grain and performance.
• Developed Algorithm: Developed MATLAB code to evaluate propellant behavior across extreme upper and lower-bound climatic conditions, accurately modeling variations in thrust, thrust coefficient (C_f), burn rate, and nozzle corrosion.
• System Design: Conceptualized a preliminary Rocket-Assisted Take-Off (RATO) system for a rail-launch mechanism, engineering a reliable separation sequence utilizing a wing pylon system and ensuring structural compatibility with the airframe.

Propulsion Engineer at Wolf Dynamics (2026-01 – 2026-04)

• Combustion System R&D: Conducted end-to-end research and development of an air-propane combustion system engineered to generate targeted infrared (IR) signatures for drone applications.
• Heat Transfer & CFD Simulation: Calculated inlet air preheating over the hot nose cone and executed 2D internal flow and combustion simulations for a propane-air mixture, successfully achieving a target Wien peak emission wavelength of 3.3 micrometers.

Intern - Propulsion Division at CSIR-National Aerospace Laboratories (2025-07 – 2025-11)

• Worked on resonance based ignition phenomena in Hartmann-Sprenger tubes to auto ignite the propellant without external complex system under an ISRO-funded R&D project for liquid engine.
• Executed ANSYS Fluent simulations of underexpanded nozzle flows, defining the drivers of resonance-based ignition by characterizing time-periodic pressure oscillations and complex shock cell structures at different pressure range.
• Conducted multi-pressure test campaigns to analyze fluid flow behavior and gas dynamic shocks in underexpanded nozzles, comparing configurations both with and without Hartmann-Sprenger (HS) tubes. Deployed Schlieren visualization to map transient shock wave dynamics
• Developed MATLAB image processing algorithms to extract quantitative data from Schlieren videos and post-process CFD results, enabling correlation between numerical predictions and experimental measurements.

Intern - Propulsion feed System at Aero2Astro (2024-07 – 2024-10)

• Conducted applied research on pintle injector design and ignition systems for liquid propellant rocket engines, covering literature review, performance hand calculations, and prototype design.
• Evaluated injector performance metrics including atomization efficiency and mixing uniformity for propellant combinations relevant to small launch vehicles.

BTech in Aerospace Engineering – Ajeenkya D Y Patil University, Pune (2022 – 2026)