基于压力隐式算子分割(PISO)算法,通过求解Navier-Stokes方程,对煤油/气氧/气氢三组元火箭发动机两相燃烧进行了数值仿真,得到了燃烧自激振荡的仿真结果;根据燃烧室压力变化,通过实时调节推进剂流量,对液体火箭发动机燃烧不稳定进行主动控制.仿真结果表明:对液体火箭发动机不稳定燃烧进行主动控制是可行的;通过调节推进剂流量的3%就可以抑制燃烧不稳定.
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