进气道角度对含硼推进剂固冲发动机性能的影响

Effects of Side-inlet Angle on the Performance of Boron-based Propellant Ducted Rocket

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,建立了发动机补燃室内简单反应流模型,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,并在此基础上进行直连式试验研究。结果表明,后进气道角度为60°时的燃烧效率比90°时高。

Theoretical investigation on the behavior of boron particles in the flow field 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 flow field and the particle behavior were solved numerically.It is presumed that the ignition and combustion of boron particles can be controlled by King s model.The solution presents the trajectory and oxide layer thickness of the boron partic...