Feasibility of a Helium Closed-Cycle Gas Turbine for UAV Propulsion
Source abstract
Abstract
When selecting a design for an unmanned aerial vehicle, the choice of the propulsion system is vital in terms of mission requirements, sustainability, usability, noise, controllability, reliability and technology readiness level (TRL). This study analyses the various propulsion systems used in unmanned aerial vehicles (UAVs), paying particular focus on the closed-cycle propulsion systems. The study also investigates the feasibility of using helium closed-cycle gas turbines for UAV propulsion, highlighting the merits and demerits of helium closed-cycle gas turbines. Some of the advantages mentioned include high payload, low noise and high altitude mission ability; while the major drawbacks include a heat sink, nuclear hazard radiation and the shield weight. A preliminary assessment of the cycle showed that a pressure ratio of 4, turbine entry temperature (TET) of 800 °C and mass flow of 50 kg/s could be used to achieve a lightweight helium closed-cycle gas turbine design for UAV mission considering component design constraints.
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Research context
OpenAlex topics: Advanced Aircraft Design and Technologies · Advanced Thermodynamic Systems and Engines · Thermodynamic and Exergetic Analyses of Power and Cooling Systems
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
EGB Engineering, Southwell NG25 0BB, UK
Centre for Propulsion Engineering, School of Aerospace Transport and Manufacturing (SATM), Cranfield University, Cranfield MK43 0AL, UK
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