| RBCC引射/亚燃模态过渡点选择 |
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| 引用本文： | 刘洋,何国强,刘佩进,吕翔.RBCC引射/亚燃模态过渡点选择[J].固体火箭技术,2009,32(5). |
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| 作者姓名： | 刘洋 何国强 刘佩进 吕翔 |
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| 作者单位： | 西北工业大学,燃烧、流动和热结构国家级重点实验室,西安,710072 |
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| 摘 要： | 以RBCC推进系统为动力的飞行器设计流程出发,建立了考虑发动机工作的限制条件的引射和亚燃模态性能评估方法,研究了不同燃料条件下发动机引射和亚燃模态下比冲和推力系数随飞行弹道的变化规律,提出了基于比冲最优、推力变化最小的模态过渡点选择方法;结合某一具体飞行任务的典型弹道,获得了在飞行马赫数为2.6±0.1、飞行高度为11.7～12.9 km范围内进行引射/亚燃模态过渡最佳的结论.
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| 关 键 词： | 火箭基组合循环(RBCC) 引射模态 亚燃模态 模态过渡 |
Selection of ejector-ramjet mode transition interval on RBCC |
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| LIU Yang,HE Guo-qiang,LIU Pei-jin,LV Xiang.Selection of ejector-ramjet mode transition interval on RBCC[J].Journal of Solid Rocket Technology,2009,32(5). |
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| Authors: | LIU Yang HE Guo-qiang LIU Pei-jin LV Xiang |
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| Institution: | LIU Yang,HE Guo-qiang,LIU Pei-jin,LV Xiang(National Key Laboratory of Combustion,Flow and Thermo-Structure,Northwestern Polytechnical University,Xi'an 710072,China) |
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| Abstract: | The performance evaluating method that takes into account the RBCC restrictive real operation condition of ejector and ramjet mode was set up based on aircraft design flow chart.The change of specific impulse and thrust coefficient of motor using different fuels with flight trajectory were discussed.The selection method based on optimum specific impulse and minimum thrust fluctuation of ejector/ramjet mode transition interval was put forward.In considering the reference flight trajectory of a certain missio... |
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| Keywords: | rocket based combined cycle(RBCC) ejector mode ramjet mode mode transition |
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