Currently fielded electric-powered small unmanned aircraft systems (UAS) lack the endurance desired by warfighters, while their internal combustion engine driven counterparts generate mission compromising acoustic and thermal signatures. Parallel hybrid-electric propulsion systems would meet the military's needs by combining the advantages of hydrocarbon and electric power systems. Three distinct parallel hybrid-electric system designs, each with three unique battery discharging profiles, were analyzed and compared using a constrained static optimization formulation based upon traditional aircraft design equations. Each system combined an internal combustion engine sized for cruise speed with an electric motor sized for endurance speed. The nine variations were compared using a typical intelligence, surveillance and reconnaissance (ISR) mission profile. The analysis determined the most suitable design for the baseline ISR mission and provided recommended missions for the remaining designs.
Analysis of Hybrid-Electric Propulsion System Designs for Small Unmanned Aircraft Systems
2010
148 pages
Report
Keine Angabe
Englisch
Aircraft , Electric & Ion Propulsion , Hybrid systems , Electric power , Hybrid propulsion , Theses , Coding , Hydrocarbons , Unmanned , Acoustic signatures , Military planning , Surveillance , Reconnaissance , Folding , Internal combustion engines , Experimental design , Mission profiles , Mathematical models , Optimization , Dual propeller design
Hybrid-electric propulsion systems for small unmanned aircraft
TIBKAT | 2014
|Hybrid-electric propulsion systems for small unmanned aircraft
TIBKAT | 2014
|Hybrid-Electric, Heavy-Fuel Propulsion System for Small Unmanned Aircraft
SAE Technical Papers | 2014
|Hybrid-Electric, Heavy-Fuel Propulsion System for Small Unmanned Aircraft
British Library Conference Proceedings | 2014
|