| 固体推进剂空气涡轮火箭发动机的非设计点性能研究 |
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| 引用本文： | 陈湘,陈玉春,屠秋野,蔡元虎,张宏.固体推进剂空气涡轮火箭发动机的非设计点性能研究[J].固体火箭技术,2008,31(5). |
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| 作者姓名： | 陈湘 陈玉春 屠秋野 蔡元虎 张宏 |
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| 作者单位： | 西北工业大学,动力与能源学院,西安,710072 |
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| 摘 要： | 为了简化控制系统和节流装置,采用涡轮进口富燃燃气流量为常数的调节计划,建立了固体推进剂空气涡轮火箭发动机(SPATR)的非设计点计算数学模型。分析了不同设计点涡轮进口富燃燃气流量对SPATR性能的影响,确立了设计点富燃燃气流量选择的方法。计算了SPATR的非设计点性能。结果表明,所建数学模型合理、可行,能满足SPATR在不同高度和速度下飞行任务的需要。
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| 关 键 词： | 固体推进剂空气涡轮火箭发动机(SPATR) 非设计点 数学模型 富燃燃气 |
Research on off-design performance of solid propellant air-turbo-rocket |
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| CHEN Xiang,CHEN Yu-chun,TU Qiu-ye,CAI Yuan-hu,ZHANG Hong.Research on off-design performance of solid propellant air-turbo-rocket[J].Journal of Solid Rocket Technology,2008,31(5). |
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| Authors: | CHEN Xiang CHEN Yu-chun TU Qiu-ye CAI Yuan-hu ZHANG Hong |
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| Abstract: | In order to simplify the control system and throttle valve,a numerical model for off-design points of solid propellant air-turbo-rocket(SPATR) was derived by using fuel-rich gas flow in turbine inlet as constant of the regulating plan.The effects of fuel-rich gas flow in different design point turbine inlet on performances of the SPATR were analyzed.The method for selecting design point fuel-rich gas flow was determined.The off-design performance of SPATR was calculated based on this model.The results indicate that the model is rational and feasible,which can meet requirements of SPATR under different altitude and velocity conditions. |
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| Keywords: | solid propellant air-turbo-rocket(SPATR) off-design points mathematical model fuel-rich gases |
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