关键词: 固体火箭发动机;喷管烧蚀;温度分布

Abstract: Some essential problems with ablation and heat-conduction calculations in integral complex-structure nozzle of solid rocket are discussed in the paper: ( 1 ) Calculations of two-phase viscous transonic flow and heat-transfer between gas and wall in nozzle are foundation for ablation and heat-conduction calculations. ( 2 ) The aerodynamic thermochemi-cal ablative models must be presented for various compound materials, (3) Particles’ erosion must be considered (two-phase ablative mechanism). (4 ) It is important to study ablative control mechanism. (5) Moving multi-boundaries should be treated in transient heat-conduction. (6) The couple between ablation and heat-conduction should be taked into account. ( 7 ) Careful test and measurement must be conducted. (8 ) Finally, the software of ablation and heat-transfer CAD may be programed.On the basis of solving essential problems, ablative rate and temperature distributions are obtained for integral complex-structure nozzle.The study on ablative and heat-conductive problems in solid rocket nozzle has been developed more completely and sophisticatedly by Chinese specialists.

Key words: Solid rocket engine;Nozzle;Ablation;Temperature distri- bution