Volume 40 Issue 8
Aug.  2025
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SHEN Xiaochen, DONG Xuefei, ZHAO Zhenfeng, et al. Turbocharging matching and experimental validation for small aviation two-stroke piston engine[J]. Journal of Aerospace Power, 2025, 40（8）：20240332 doi: 10.13224/j.cnki.jasp.20240332
Citation: SHEN Xiaochen, DONG Xuefei, ZHAO Zhenfeng, et al. Turbocharging matching and experimental validation for small aviation two-stroke piston engine[J]. Journal of Aerospace Power, 2025, 40（8）：20240332 doi: 10.13224/j.cnki.jasp.20240332
shu

Turbocharging matching and experimental validation for small aviation two-stroke piston engine

doi: 10.13224/j.cnki.jasp.20240332
  • 1.

    Department of Electrical Engineering，Shanxi Engineering Vocational College，Taiyuan 030027，China

  • 2.

    School of Mechanical Engineering，Beijing Institute of Technology，Beijing 100081，China

  • 3.

    Beijing Aerospace UAV System Engineering Research Institute，Beijing 100094，China

  • Received Date: 2024-05-23
    Available Online: 2024-12-05
    Abstract

  • In order to solve the dramatic power coastdown of short-range unmanned aerial vehicles at high altitudes, a turbocharging two-stroke aviation piston engine was studied. Based on comprehensive analysis of the turbocharging technology application in the unmanned aerial vehicle platform, a technical scheme including an intake pressure stabilizing system, an exhaust resonant system, a self-lubricating turbocharging system and a closed-loop adaptive control system, was proposed. A one-dimensional simulation model was established and calibrated for a turbocharging two-stroke engine. The DOE (design of experiment) test method was used to complete the coupling relationship analysis of the key parameters of the intake and exhaust system, and the best structural parameters of the intake pressure stabilizing system and exhaust resonance system were obtained. And the coupling and matching of the turbocharging system with the engine performance was performed. At an altitude of 8000 m the power-to-mass ratio before and after supercharging increased from 0.59 kW/kg to 0.96 kW/kg; and the proposed technical scheme was estimated through a flight test of a unmanned aerial vehicle platform. The results showed that, the maximum flight height exceeded 8367 m, which was 85% higher than that without this scheme. The two-stroke supercharging technology has obvious advantages in high-altitude power.

     

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