Abstract
Extensive application of small and medium-sized unmanned aerial vehicles (UAVs) have already made the development of corresponding power system a research hotspot nowadays. Two-stroke heavy fuel light aeroengine (2SHFLA) is selected as the research focus in this paper. The working principle of 2SHFLA with different fuel injection systems is elaborated systematically. By dividing the initial prototype engine into several subsystems, the simulation platform is set up with its key model parameters accurately calibrated against the test data. Simulation platforms of the other two types of engines are subsequently constructed based on the pre-calibrated simulation platform of the initial prototype engine. Afterwards, comparative simulation is performed and the corresponding simulation results include: (1) comparison of performance characteristics of the initial prototype engine fueled with regular gasoline/heavy fuel; (2) comprehensive comparison of the performance characteristics of all the three types of engine.
Highlights
In recent years, with the great progress of wireless communication technology, flight control technology, and information processing technology, the field of general aviation power has seen great strides in development [1,2]
As a new form of propulsion, 2-stroke heavy fuel light Aeroengine (2SHFLA) is selected as our research focus for its superiority in fulfilling the above-mentioned demands of power systems of small and medium unmanned aerial vehicles (UAVs)
The comparison of performance characteristics of the initial prototype engine supplied with regular gasoline/heavy fuel is conducted
Summary
With the great progress of wireless communication technology, flight control technology, and information processing technology, the field of general aviation power has seen great strides in development [1,2]. With respect to small and medium-sized UAVs, its main functions generally include battlefield surveillance and reconnaissance, real-time relay communication, and continual border patrol. Taking into account these function features, take-off weight and loitering time are often considered as the core indicators for evaluating the performance of small and medium-sized UAVs [3]. Crucial requirements including high power density, light weight, and compact structure have been met when designing the power systems for small and medium-sized UAVs [4,5]. As a new form of propulsion, 2-stroke heavy fuel light Aeroengine (2SHFLA) is selected as our research focus for its superiority in fulfilling the above-mentioned demands of power systems of small and medium UAVs
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