火箭推进

针对空气涡轮火箭(ATR)发动机展开研究,在建立发动机全系统数学模型仿真系统的基础上,研究不同推进剂组合对发动机性能影响,并采用发动机组件关键参数对推力比冲影响分析方法,确定发动机关键参数范围,结果表明:推力方面液氧甲烷(LOX/CH4)推进剂更具优势,比冲方面液氢液氧(LOX/LH2)推进剂具有很大优势。发现涡轮效率提高对发动机比冲增益最为显著,每提高1%涡轮效率比冲平均增加9.1 s; 压气机效率的影响次之,比冲平均增加8.0 s。随着涡轮和压气机效率的增加,发动机比冲增加而推力下降; 随着燃烧效率的增加,发动机推力和比冲均增加。

Based on the whole system mathematical model of Air Turbo Rocket,this paper focuses on Air Turbo Rocket engine research and the influence of different propellants on the engine.And based on the analysis the influence of key parameters of engine components on thrust and specific impulse,the range of key engine parameters was determined.The result shows: the liquid oxygen and methane propellant have relative advantage in thrust,and the liquid hydrogen and oxygen propellant have great advantage in specific impulse.The increase in turbine efficiency has the most significant impact on the engine specific impulse,for every 1% increase in turbine efficiency,the specific impulse increases by an average of 9.1 s.The effect of compressor efficiency is second,the specific impulse increases by an average of 8.0 s.As the efficiency of turbine and compressor efficiency increases,engine specific impulse increases and thrust decreases.As combustion efficiency increases,engine specific impulse and thrust increase.

引言
1 工作原理及参数选择
2 推进剂影响分析
3 敏感参数分析
4 结论

图1 ATR发动机系统原理示意图<br/>Fig.1 System schematic of ATR engine

图1 ATR发动机系统原理示意图
Fig.1 System schematic of ATR engine

表1 ATR发动机地面点主要系统参数<br/>Tab.1 Main system parameters of ATR engine design point

表1 ATR发动机地面点主要系统参数
Tab.1 Main system parameters of ATR engine design point

图2 不同推进剂推力随马赫数高度变化<br/>Fig.2 Thrust of different propellants varies with height and Mach number

图2 不同推进剂推力随马赫数高度变化
Fig.2 Thrust of different propellants varies with height and Mach number

图3 不同推进剂比冲随马赫数高度变化<br/>Fig.3 Specific impulse of different propellants varies with height and Mach number

图3 不同推进剂比冲随马赫数高度变化
Fig.3 Specific impulse of different propellants varies with height and Mach number

图4 不同推进剂余气系数随马赫数高度变化<br/>Fig.4 Residual gas coefficient of different propellants varies with height and Mach number

图4 不同推进剂余气系数随马赫数高度变化
Fig.4 Residual gas coefficient of different propellants varies with height and Mach number

图5 不同推进剂体积流量随马赫数高度变化<br/>Fig.5 Volume flow of different propellants varies with height and Mach number

图5 不同推进剂体积流量随马赫数高度变化
Fig.5 Volume flow of different propellants varies with height and Mach number

图6 组件效率对发动机比冲的影响<br/>Fig.6 Effect of component efficiency on engine specific impulse

图6 组件效率对发动机比冲的影响
Fig.6 Effect of component efficiency on engine specific impulse

图7 组件效率对发动机推力的影响<br/>Fig.7 Effect of component efficiency on engine thrust

图7 组件效率对发动机推力的影响
Fig.7 Effect of component efficiency on engine thrust

图8 涡轮落压比对发动机比冲的影响<br/>Fig.8 Effect of turbine drop pressure ratio on engine specific impulse

图8 涡轮落压比对发动机比冲的影响
Fig.8 Effect of turbine drop pressure ratio on engine specific impulse

图9 涡轮入口温度对发动机比冲的影响<br/>Fig.9 Effect of turbine inlet temperature on engine specific impulse

图9 涡轮入口温度对发动机比冲的影响
Fig.9 Effect of turbine inlet temperature on engine specific impulse

图10 压气机压比对发动机比冲的影响<br/>Fig.10 Effect of compressor pressure ratio on engine specific impulse

图10 压气机压比对发动机比冲的影响
Fig.10 Effect of compressor pressure ratio on engine specific impulse

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备注

引言

1 工作原理及参数选择

2 推进剂影响分析

3 敏感参数分析

4 结论

期刊信息