BACKGROUND
Precise thrust control in turbojet UAS (unmanned aerial systems) platforms and traditional propulsion applications are becoming increasingly critical as military missions such as loitering munition and Intelligence, Surveillance, Reconnaissance (ISR) are developing more demanding criteria. UAS platforms responsible for high-speed reconnaissance and prolonged loitering require precise control over thrust output. The craft ultimately needs adaptable propulsion solutions. Innovations that can meet thrust control performance targets, such as thrust range and maximum thrust, while minimizing weight and size constraints are necessary for continued successful UAS missions.
SUMMARY OF TECHNOLOGY
Researchers at Oklahoma State University have developed a variable area nozzle for small turbojet engines (e.g. mass flow rate less than 5 pounds per second). The novel nozzle optimizes thrust performance and enables rapid thrust modulation without engine spooling delays, providing precise thrust control. Thrust performance targets, such as thrust range and maximum thrust, are met while minimizing weight incorporated and fitting within size constraints. The performance of the micro turbojet engine was characterized by On-Design Parametric Cycle Analysis and Off-Design Engine Performance Analysis, ensuring optimal nozzle exit areas with the mass flow parameter. Incorporation of the novel variable area nozzle in UAS platforms will improve overall maneuverability and operational efficiency of UAS platforms by implementing precise thrust control with minimal engine spooling delays.
POTENTIAL AREAS OF APPLICATION
MAIN ADVANTAGES
STAGE OF DEVELOPMENT
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