关键词: 甲基肼/四氧化二氮, 液体火箭发动机, 脉冲工况

Abstract: A numerical and experimental study of pulse mode characteristics in a MMH/NTO rocket Engine is proposed via a reduced chemical kinetic model including 20 reactions and 23 species devoted to the gas phase reaction of monomethyl hydrazine/nitrogen tetroxide (MMH/NTO). The results show that the combustion chamber pressure reaches stability rapidly, related 3.7ms to 8ms. The chamber wall heat flux first increases and then decreases, and the film cooling efficiency is significantly affected by the pulse width. The combustion chamber pressure increases and decreases similarly in different pulse mode, and the engine can deliver a steady thrust or impulse after 2.5 ms~3 ms.

Key words: MMH/NTO, liquid rocket engine, pulse mode