摘要
对潜入和非潜入式喷管的翼柱形药柱发动机点火瞬态过程进行了数值仿真研究,采用修改源项法模拟推进剂燃烧加质,并分析了不同深度、不同宽度的翼槽结构对翼槽区域火焰传播的影响。发现潜入喷管的存在、不同深度、不同宽度的翼槽结构影响火焰传播方式;潜入喷管的存在导致火焰峰连续向翼槽底部及尾部区域传播;尾部翼槽较深时,尾部翼槽尾部尖角处首先点燃,然后火焰峰自尾部翼槽前部与翼槽尖角处同时向翼槽底部传播。尾部翼槽宽度较宽,火焰峰传播速度越快;尾部翼槽深度越深,火焰峰传播速度越慢。
Flame propagation process of the ignition transient process of solid rocket motor with finocyl grain and submerged or non-submerged nozzle were simulated.The source change method was used to simulate the mass addition from burning surface and the effect of fin-slots with different width and depth on the flame-spreading was analysed.The result indicates submerged nozzle,different width and depth of fin-slots affect the form of the flame-spreading;the presence of the submerged nozzle leads the flame propagation to the bottom and tail regions of the fin-slots continuously;the propellant in tail fin-slots was ignited first as the tail fin-slot is more deep,then the flame spreads to the the bottom of the fin-slots from the front of the fin-slots and the tail fin-slots.The more wide fin-slots,the more rapid the flame spreads;the more deep fin-slots,the more slower the flame spreads.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第6期626-630,共5页
Journal of Solid Rocket Technology
