摘要：A new pressurized feed system of the dual-thrust hybrid rocket motor for flight is presented in this *** feed system supplies 90% hydrogen peroxide (90%H 2 O 2) with two different flows of 4.5 and 2 kg s *** oxidizer flow is changed through regulating the mass flow of the high-pressure gas and switching the performance modes of the unique oxidizer flow control valve *** models of the gas storage container,pressure regulator valve,control orifice,propellant tank,oxidizer flow control valve and cavitating venturi are generated and used to compute the instantaneous pressure,temperature and mass flow *** is a good agreement between the simulated and experimental *** sensitivity analysis is also *** is found that the throat diameter of the cavitating venturi in feed line 1 is the main factor affecting the mass flow in both boost and sustaining *** parameters have limited effects on the mass flow rate and the transition time of the system.

摘要：以数值仿真的结果作为参考,开展了基于PLIF(平面激光诱导荧光)技术、高速摄影技术等非接触光学燃烧诊断技术的气氧/气甲烷同轴剪切喷嘴试验研究。通过联合光学诊断对不同设计工况的燃烧流场进行诊断测量,获得燃烧室内OH分布,燃烧流场发展演化过程、火焰的结构等信息,对燃烧流场进行详细的分析。研究结果表明:气氧/气甲烷剪切燃烧火焰存在明显的剪切燃烧层,且随着轴向距离的增加,火焰逐渐失稳;随燃氧速度比的增加,流场涡旋作用明显加强,火焰根部稳定段变短,瞬时火焰结构卷曲和褶皱增多;仿真计算的OH分布与试验测得的OH分布相似,仿真模型能够合理预测气氧/气甲烷同轴剪切喷嘴的燃烧流场。

摘要：利用太阳引力摄动与月球绕飞设计的地月转移轨道 (飞月轨道 ) ,与霍曼转移相比 ,虽然飞行时间较长 (约三、四个月 ) ,但可显著节省速度增量 (可达 15 0米 /秒 ) ,对无人月球探测器尤为适合。应用平面圆型限制性四体问题动力学模型 ,选择从月球出发的初始条件。借助“地心距 时间曲线” ,从平面圆型限制性四体问题转换为一般的限制性四体问题。通过典型模拟计算 ,分析负向积分 (从月球轨道出发 )初始轨道参数及太阳方位对月球探测器轨迹的影响 。