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中文摘要：
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26km左右达到最大值50MW／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．
英文摘要：
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.
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