| 引用本文: | 吴继平,谭建国,陈健,等.火箭-双燃烧室冲压组合循环发动机概念研究.[J].国防科技大学学报,2019,41(5):8-15.[点击复制] |
| WU Jiping,TAN Jianguo,CHEN Jian,et al.Conceptual analysis of rocket dual combustion ramjet combined-cycle engine[J].Journal of National University of Defense Technology,2019,41(5):8-15[点击复制] |
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| 火箭-双燃烧室冲压组合循环发动机概念研究 |
| 吴继平1,2, 谭建国1,2, 陈健1,2, 张紫豪1,2 |
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(1.国防科技大学 空天科学学院， 湖南 长沙 410073;2.国防科技大学 高超声速冲压发动机技术重点实验室， 湖南 长沙 410073)
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| 摘要: |
| 临近空间高超声速飞行器近年来获得了广泛关注，本文提出一种以基于火箭发动机和双燃烧室冲压发动机的多模态火箭-双燃烧室冲压组合循环发动机作为飞行器的动力系统，并进行了性能分析研究。该飞行器在海拔10 km左右高度以0.8马赫的速度投放，在重力和发动机推力的联合作用下，能够在海拔5~8 km 处加速到2马赫；然后加速爬升进入临近空间，发动机工作在引射亚燃或者双燃烧室亚燃模态下。可以根据实际选择高推重比、较低推进剂比冲效率的引射亚燃模态，或是较低推重比、高推进剂比冲效率的双燃烧室亚燃模态。最终飞行器加速到6马赫（26 km），进入双燃室超燃模态。针对空中发射模式和地面发射模式进行了轨道优化，仿真结果表明：在加速爬升到6马赫（26 km）的过程中，空中发射模式相比较地面发射模式可以节省37%的推进剂；空中发射模式存在一个负的最优初始飞行角度使得剩余质量与初始质量的比值达到最大。 |
| 关键词: 空天推进系统 高超声速飞行器 组合循环发动机 轨道优化 |
| DOI：10.11887/j.cn.201905002 |
| 投稿日期：2018-05-02 |
| 基金项目:国家自然科学基金资助项目（11172324） |
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| Conceptual analysis of rocket dual combustion ramjet combined-cycle engine |
| WU Jiping1,2, TAN Jianguo1,2, CHEN Jian1,2, ZHANG Zihao1,2 |
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(1.College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China;2.Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China)
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| Abstract: |
| Increasing attention has been paid to near space plane in recent years. In the present study, a multi-module RDCRC (rocket dual combustion ramjet combined cycle) engine was proposed to power the near space plane and its performance was analyzed. The plane was designed to drop at about Mach 0.8 and 10 km above sea level. Under the gravity and the combination thrust of the engine, the plane accelerates to about Mach 2 at 5~8 km above sea level. Then, it climbs up and accelerates the near space under the ejector-ramjet mode or DCR ramjet mode. The ejector-ramjet mode provides higher acceleration with less efficiency, while the DCR ramjet mode provides more efficiency and lower acceleration, thus the mode can be transformed according to the actual situation. Finally, the plane climbs up to about 26 km above sea level, accelerates to Mach 6, and starts to cruise in DCR scramjet mode. A trajectory optimization was carried out for air launch and surface launch, and the obtained results show that the air launch can save about 37% propellant with Mach 6 and 26 km above sea level, and there lies a negative optimal initial flight angle that leads to an optimum ratio between the residual mass and the initial mass. |
| Keywords: aerospace propulsion system hypersonic vehicle combine-cycle engine trajectory optimization |
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