| 定几何混压式轴对称超声速进气道设计及性能计算 |
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| 引用本文： | 陈兵,徐旭,王元光,蔡国飙. 定几何混压式轴对称超声速进气道设计及性能计算[J]. 航空动力学报, 2005, 20(3): 373-379 |
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| 作者姓名： | 陈兵 徐旭 王元光 蔡国飙 |
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| 作者单位： | 北京航空航天大学宇航学院,北京100083 |
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| 摘 要： | 给出了定几何混压式轴对称超声速进气道型面设计及性能计算方法,进行了算例计算。对亚临界状态下脱体激波的计算进行了研究,给出了进气道临界状态性能参数随飞行马赫数和高度的改变而变化的曲线。分析了进-发匹配过程,以及进气道的自调节能力。计算得到了基于进气道性能最优,即进气道工作在临界状态条件下,碳氢燃料冲压发动机的供油规律,为进气道大范围寻优设计打下了基础。
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| 关 键 词： | 航空、航天推进系统 超声速进气道 性能计算 脱体激波 进-发匹配 供油特性 |
| 文章编号： | 1000-8055(2005)03-0373-07 |
| 收稿时间： | 2004-10-20 |
| 修稿时间： | 2004-10-20 |
Design and Performance Calculation of the Mixed-Compression Fixed-Geometry Axisymmetric Supersonic Inlets |
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| CHEN Bing,XU Xu,WANG Yuan-guang and CAI Guo-biao. Design and Performance Calculation of the Mixed-Compression Fixed-Geometry Axisymmetric Supersonic Inlets[J]. Journal of Aerospace Power, 2005, 20(3): 373-379 |
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| Authors: | CHEN Bing XU Xu WANG Yuan-guang CAI Guo-biao |
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| Affiliation: | School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China |
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| Abstract: | Geometric design method of mixed-compression fixed-geometry axisymmetric supersonic ramjet inlet was presented.Performance calculations of inlet under on-or off-design conditions were carried out with special attention to the detached bow shock calculation during subcritical operations.The influence of flight Mach number and altitude on inlet critical condition performance has been evaluated.The inlet-engine matching mechanism was investigated, and the fuel supply characteristics were obtained to maintain the optimum inlet performance.The successful study provides a good reference to the design of ramjet supersonic inlets. |
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| Keywords: | aerospace propulsion system supersonic inlet performance calculation detached bow shock inlet-engine matching fuel supply characteristics |
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