关键词: 固体火箭发动机;喷管;烧蚀性能;控制

Abstract: According to the aerodynamic-thermochemical ablation model, the ablative mass calculation equations are deduced. According to the transient equivalent thermo-capaci-ty heat-conduction equation, its implicit scheme is deduced under the condition of ablative moving boundaries for multi-layer construction of nozzle. Then, these equations are coupled-ly solved.By study, authors find that there are different ablative control mechanisms on different positions of nozzle. kinetics, diffusion or double control mechanism, and following conclusions may be obtained;( 1) It is important to divide ablative mechanisms into diffusion, kinetics or double control mechanisms for ablative calculation in nozzle.(2) When the difference between ablative rate determinded by diffusion and that by ki-netics control mechanisms is equal to or more than 20 times, the ablative rate may be simpli-fiedly calculated according to that control mechanism which brings about lower ablative rate.(3) In solid rocket nozzle, roughly, the ablation is controled by diffusion in convergent portion, but by kinetics in throat and divergent portions.(4) In solid rocket nozzle, the ablative rates in throat and divergent portions may be simplif iedly calculated by the kinetics control mechanism, but the ablative rate in convergent portion must be calculated by double control mechanism.

Key words: Solid rocket engine;nozzle;Ablation property;Control