| 远程超低飞行轨道分析 |
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| 引用本文： | 樊菁,蒋建政,孙泉华,黎作武,吴晨曦.远程超低飞行轨道分析[J].力学学报,2009,41(4). |
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| 作者姓名： | 樊菁 蒋建政 孙泉华 黎作武 吴晨曦 |
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| 作者单位： | 1. 中国科学院力学研究所高温气体动力学重点实验室,北京,100190
2. 中国空气动力研究与发展中心国家CFD实验室,北京,100083 |
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| 基金项目： | 国家自然科学基金资助项目(10425211,10621202)~~ |
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| 摘 要： | 研究了一种新的远程导弹飞行轨道的可行性,它的最大飞行高度约100 km.这种超低弹道,借鉴卫星模式,利用离心力抵抗重力.与卫星轨道运行不同的是,超低弹道周围的稀薄空气影响至关重要,必须考虑.计算和分析结果表明,在相同载荷条件和射程条件下,超低弹道和经典的最小能量弹道对于火箭动力的需求大致相当,射程10000km以上基本相同,头部半径为5cm的轴对称外形,沿超低弹道飞行时,其驻点热流在高度26km左右达到最大值50MW/m2,约为最小能量弹道驻点热流最大值的50%.由于超低弹道对升力没有要求,飞行过程中的气动加热问题,沿用成熟方法如烧蚀防热即可解决.总体而言,超低弹道对于火箭动力与外形气动力/热要求,现有技术容易满足,因此利用它增强远程导弹的突防能力是现实可能的.
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| 关 键 词： | 远程导弹 超低飞行轨道 稀薄气体效应 动力需求 驻点热流 |
ANALYSIS OF ULTRA-LOW,LONG-RANGE FLIGHT TRAJECTORY |
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| Fan Jing
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Jiang Jianzheng
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Sun Quanhua
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Li Zuowu
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Wu Chenxi.ANALYSIS OF ULTRA-LOW,LONG-RANGE FLIGHT TRAJECTORY[J].chinese journal of theoretical and applied mechanics,2009,41(4). |
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| Authors: | Fan Jing Jiang Jianzheng Sun Quanhua Li Zuowu Wu Chenxi |
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| Institution: | *;2;Key Laboratory of High Temperature Gas Dynamics;Institute of Mechanics;Chinese Academy of Sciences;Beijing 100190;China;China Aerodynamic Research and Development Center;National Laboratory of Computational Fluid Dynamics;Beijing 100083;China |
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| Abstract: | An ultra-low,long-range flight trajectory with the maximum altitude of about 100 km is investigated. Such an ultra-low trajectory employs the satellite mode against the gravitation by the centrifugal force.Different from a running satellite,the rarefied gas effects on the ultra-low trajectory are essentially important.It is shown that under the same payload and range,the power requirements of the ultra-low trajectory and classic minimum energy trajectory are almost the same.For an axial symmetric configurat... |
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| Keywords: | long-range missile ultra-low trajectory rarefied gas power requirement stagnation heat flux |
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