进气道位置对含硼推进剂固体火箭冲压发动机性能的影响

为了提高含硼推进剂固体火箭冲压发动机内硼颗粒的燃烧效率,采用颗粒轨道模型进行了补燃室两相流的数值模拟,其中硼颗粒的点火和燃烧模型采用的是King模型,建立了发动机补然室内简单反应流模型,并在该模型下研究了进气道的位置对非壅塞固体火箭冲压发动机燃烧效率的影响,在此基础上进行直连式试验研究。结果表明:随着前后进气道之间轴向距离增加,燃烧效率先增加后减小,并且试验重复性比较好;前进气道后置长度增加,燃烧效率减小。

Effects of side-inlet location on the performance of boron-based propellant ducted rocket

Theoretical investigation on the behavior of boron particles in the flowfield of a ducted rocket secondary combustor is presented.The study was motivated by the difficulties in achieving good combustion efficiencies of boron particles.The equation describing the gas flowfield and the particle behavior are solved numerically.Assuming that the ignition and combustion of boron particles is controlled by King's model.The solution presents the trajectory and oxide layer thickness of the boron particles due to the interactions with the surrounding gas.And some experimental investigations have been done on a connected-pipe test bed. Increasing the deflector between the two air intakes within proper range can increase the combustion efficiency.Decreasing the dome height increases combustion efficiency.