Development of a Microjet Engine Including Conceptual Design, Prototype Fabrication, an‎d Transient Performance Analysis

3/13/2026 12:00:00 AM

Today, microjet engines are recognized as one of the advanced technologies in the aerospace, military, an‎d industrial fields due to their small size, low weight, an‎d high power output. These engines have gained a special place in modern industries because of their high power-to-weight ratio, simpler structure compared to larger engines, an‎d their applicability in small flight systems. Microjet engines typically feature a centrifugal compressor, a single-stage axial turbine, an‎d a one-piece annular combustion chamber. Such engines are widely used in drones, jet packs, combined heat an‎d power generation systems, an‎d other lightweight an‎d portable equipment. In this research, initially, using aerodynamic an‎d thermodynamic relations, an algorithm was developed for the conceptual design of a laboratory microjet engine with the goal of achieving a specified static thrust. In this algorithm, considering manufacturing constraints, alloy temperature tolerances, an‎d maximum allowable velocity in the exhaust nozzle, the design parameters of the main engine components were determined step-by-step. After completing the design stages, a prototype engine was manufactured, an‎d the production process including selec‎tion of durable alloys, machining of parts, final assembly, an‎d initial startup was documented. Next, to investigate the dynamic behavior of the system, the engine’s open-loop equations were derived, an‎d using physical an‎d empirical assumptions, a nonlinear mathematical model of the engine was developed. This model was implemented in the MATLAB environment, an‎d various control scenarios such as constant fueling, step increase, sudden decrease, an‎d linear increase of fuel were examined. The simulation results, including engine speed response, exhaust gas temperature, an‎d thrust force, were compared with experimental data obtained from engine testing. Additionally, using the acquired data, the reliability of engine performance under sudden fuel changes an‎d the stability of transient states were eva‎luated. The final analysis showed that the presented mathematical model corresponds well with the actual engine behavior an‎d can be utilized in the development of precise an‎d indigenous control systems. The findings of this study demonstrate that relying on domestic knowledge can lead to the design an‎d manufacture of efficient microjet engines with acceptable costs, paving the way for the localization of this strategic technology.

موتور ميكروجت , الگوريتم طراحي , ساخت وتوليد

Microjet engine , design algorithm , manufacturing an‎d production

Danial nori

Dr seyed mostafa Hoseinalipor