远程超低飞行轨道分析  

ANALYSIS OF ULTRA-LOW,LONG-RANGE FLIGHT TRAJECTORY

作　　者：樊菁[1] 蒋建政[1] 孙泉华[1] 黎作武[2] 吴晨曦[1] 

机构地区：[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

出　　处：《力学学报》2009年第4期449-454,共6页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金资助项目(10425211;10621202)~~

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100km.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26 km左右达到最大值50 MW/m^2,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。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 configuration with the nose radius of 5 cm, its stagnation heat flux along an ultra-low trajectory arrives at a maximum value of 50 MW/m^2 around altitude 25 km, which is about half of the maximum stagnation heat flux along a minimum energy trajectory. The aerodynamic heating along an ultra-low trajectory can be solved using conventional mature techniques such as ablation, because it does not require lift. In general, the power and aerodynamic requirements of ultra-low flight trajectories can be satisfied based on existing technologies, and therefore it is realistic to promote the anti-defense ability of long-range missiles by taking the ultra-low flight trajectory.

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 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]