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隔层式多脉冲发动机点火过程较常规发动机有很多不同,为获得端燃型隔层式多脉冲发动机的点火延迟特性及其影响因素,建立物理和数学模型,采用MpCCI耦合器作为FLUENT与ANSYS的数据交换平台,模拟点火燃气填充隔层和隔层变形过程;采用FLUENT计算多脉冲发动机火焰传播过程及填充过程。计算结果表明,与传统固体火箭发动机相比,在相同点火药量的情况下,多脉冲发动机的点火延迟大大增加;推进剂燃速越高,点火延迟越小;燃烧室自由容积越大,点火延迟越大;隔层材料对点火延迟影响较小。可以通过适当加大点火药量和提高燃速来减小点火延迟。
In order to obtain the ignition delay characteristics and its influencing factors of end-fired multi-pulse engine, the physical and mathematical models are established. The MpCCI coupler is used as FLUENT and ANSYS Data exchange platform to simulate the ignition gas filling compartment and the barrier deformation process; FLUENT multi-pulse engine flame propagation process and filling process. The calculation results show that the ignition delay of multi-pulse engine increases greatly with the same ignition dosage compared with the traditional solid rocket motor. The higher the ignition speed of propellant, the smaller the ignition delay. The larger the free volume of the combustion chamber, The greater the delay, the less effect the barrier material has on ignition delay. The ignition delay can be reduced by appropriately increasing the ignition dosage and increasing the burning rate.