doi：10.16186/j.cnki.1673-9787.2022030063

Received:2022/03/24

Revised:2022/10/13

Published:2024/01/25

Study on turbocharger matching application for piston engine of high plateau UAV

ZHAO Kaishen1, YANG Guangbin2, HU Chongbo3, GUO Wanshan1, QI Guohai1, ZHAI Lei1

1.Chery Holding Group Co.，Ltd.Ruiqing Automotive Engine Technology Co.，Ltd.，Jiaozuo  454000，Henan，China;2.School of Mechanical and Power Engineering，Henan Polytechnic University，Jiaozuo  454000，Henan，China;3.Research & Design Center，Wuhu Diamond Aeroengine Co.，Ltd.，Wuhu  241000，Anhui，China

Abstract: Objective In order to study the application value of using automobile engine to developing low cost civil aviation UAV piston engine， Methods a development method based on high altitude performance degradation compensation of automobile turbocharged engine was proposed.A certain type of automobile piston turbocharged engine for vehicle was selected to analyze the turbocharger-engine matching conditions under variable altitude environment，and evaluate the performance deterioration degree of automobile turbocharged engine within the boundary of UAV flight envelope.The target boost pressure ratio and engine intake flow of the new turbocharger were obtained through the simulation calculation under the condition of target altitude.With this calculation result as the performance boundary of the target new supercharger，a certain type of turbocharger was selected，and its performance output characteristics could cover the target boost pressure and flow rate of the engine as the UAV power.The UAV flight performance was verified under plain and high plateau conditions，and the pressure ratio，expansion ratio and reduced flow of the compressor and turbine impeller of the newly developed supercharger were checked respectively，and the flight test data of the UAV at different altitudes were analyzed. Results The results showed that the newly matched turbocharger was equipped with the test engine at a high altitude of 4 200 meters，the compressor pressure ratio was 3.2，the converted flow rate was 0.092 kg/s，and the operation interval was within the MAP envelope of the turbocharger impeller，which could make the UAV reach the hovering payload ratio of 28.2%，and the performance could meet the technical requirements of high altitude load flight. Conclusion By using the automobile turbocharged engine，the compressor of the turbocharger was rematched according to the operating condition of the UAV flight envelope，and the turbine operating condition was checked，which could meet the basic requirements of the civil aviation UAV flight performance on high plateau and low altitude.The matching method provided theoretical guidance for the development and application of new products.

Key words:turbocharger;piston engine;high plateau condition;low-altitude UAV