摘要
在无人机燃用航空煤油燃料效能问题的研究中,以小型二冲程汽油发动机为动力装置的无人机燃用航空煤油燃料具有重要的军事意义。煤油在内燃机中的研究和应用相对较少,所以研究煤油发动机性能参数的变化规律及爆震特性,为煤油发动机的参数优化匹配提供依据。通过建立航空二冲程发动机工作循环数值模型及爆震模型,改变模型中的压缩比、空燃比、点火提前角及反映高空特性变化的进气压力和进气温度等参数,分析主要结构参数和调整参数对煤油发动机性能的影响情况。研究结果表明,在相同的条件下,二冲程发动机燃用航空煤油燃料时性能差别不大,爆震倾向加大。可为小型二冲程汽油发动机燃用航空煤油燃料时爆震特性的研究提供参考。
Burning aviation kerosene for unmanned Aerial Vehicle which takes the miniature two - stroke gasoline engine as motive force has important military significance, and study on knock characteristics of two - stroke kerosene aero - engine is one of key technologies. The working cycle numeric model and knock model of kerosene engine were built in the paper. Through changing the compression ratio, air - fuel ratio, advance angle of ignition, intake pressure and temperature, knock characteristics of aviation kerosene fuel replaced gasoline fuel before and after were researched. The paper analyzed knock characteristics of the kerosene engine in the different configurations and parameters. The basis for the kerosene was proposed in the parameters optimizing match. The results show that two - stroke engine burning gasoline fuel generates more knock than burning kerosene fuel in the same conditions.
出处
《计算机仿真》
CSCD
北大核心
2014年第6期54-59,共6页
Computer Simulation
基金
总装某国防预研项目
关键词
航空
二冲程发动机
小型无人机
煤油
爆震特性
数值计算
Aviation
Two - stroke engine
Unmanned aerial vehicle
Kerosene
Knock characteristics
Numerical calculation
