| 引用本文: | 马松,林鹏,左林玄,等.并联TBCC动力对高超声速飞行器性能的影响.[J].国防科技大学学报,2019,41(2):1-7.[点击复制] |
| MA Song,LIN Peng,ZUO Linxuan,et al.Influence of over-under TBCC on the performance of hypersonic aircraft[J].Journal of National University of Defense Technology,2019,41(2):1-7[点击复制] |
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| 并联TBCC动力对高超声速飞行器性能的影响 |
| 马松1,2, 林鹏2, 左林玄2, 王霄1,2, 谭建国1 |
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(1.国防科技大学 空天科学学院， 湖南 长沙 410073;2.沈阳飞机设计研究所， 辽宁 沈阳 110035)
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| 摘要: |
| 针对马赫数为6的一级高超声速巡航飞行器的动力需求，提出涡轮/亚燃冲压/双模态超燃冲压组合动力（T/RJ/DMSJ）和射流预冷涡轮/亚燃冲压/双模态超燃冲压组合动力(PCT/RJ/DMSJ)两种方案。在给定的飞行任务下，分析起飞推重比分别为0.8和1.0时，飞行器完成任务时的航程和飞行时间，并对比了PCT/RJ/DMSJ在两种工作模态下的性能。研究结果表明：在相同的起飞推重比下，两种组合动力方案的航程和飞行时间相差不大。当起飞推重比为0.8时，采用PCT/RJ/DMSJ组合动力方案比T/RJ/DMSJ组合动力方案的航程高出3.6%，飞行时间高出3.8%；当起飞推重比为1.0时，PCT/RJ/DMSJ的航程和飞行时间比T/RJ/DMSJ的分别高出4.6%和4.8%。在小推重比下，跨声速段的燃料消耗和飞行时间占整个加速爬升段的比例较大，随着推重比的增加，这个比例减小，巡航可用的燃料比例增大，巡航距离增加，提高起飞推重比可以提高超声速飞行器的航程并缩短飞行时间。 |
| 关键词: 高超声速 组合动力 推重比 航程 飞行时间 |
| DOI：10.11887/j.cn.201902001 |
| 投稿日期：2018-01-09 |
| 基金项目:国家自然科学基金资助项目（91441121） |
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| Influence of over-under TBCC on the performance of hypersonic aircraft |
| MA Song1,2, LIN Peng2, ZUO Linxuan2, WANG Xiao1,2, TAN Jianguo1 |
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(1. College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China;2. Shenyang Aircraft Design & Research Institute, Shenyang 110035, China)
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| Abstract: |
| Two kinds of combined-cycle propulsions were studied to meet the requirement of a hypersonic vehicle that cruises at Mach number 6. One consists of T/RJ/DMSJ (turbine engine, ramjet and dual mode scramjet), while the other consists of PCT/RJ/DMSJ (pre-cooled turbine engine, ramjet and dual mode scramjet). The ranges and the flying time of the hypersonic vehicle which uses T/RJ/DMSJ and PCT/RJ/DMSJ were obtained under thrust weight ratio of 0.8 and 1.0 with a given mission. The performances of two operating mode of PCT/RJ/DMSJ were compared. Results show that the range and the flying time of the two combined-cycle propulsions are almost close. The range of PCT/RJ/DMSJ is 3.6% higher than T/RJ/DMSJ and the flying time of PCT/RJ/DMSJ is 3.8% more than T/RJ/DMSJ under thrust weight ratio of 0.8. When the thrust weight ratio is 1.0, the range and the flying time of PCT/RJ/DMSJ are 4.6% and 4.8% higher than T/RJ/DMSJ, respectively. Under the lower thrust weight ratio, the fuel consumption of the transonic flying phase is the largest part during the acceleration and climbing process. The fuel consumption of the transonic flying phase decreases as the increase of thrust weight ratio and then more fuel can be used in the hypersonic cruise and the cruise distance increases. The range increases and the flying time decreases as the increase of thrust weight ratio. |
| Keywords: hypersonic combined-cycle propulsion thrust weight ratio range flying time |
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