固体火箭喷管烧蚀和传热的基本问题

SOME ESSENTIAL PROBLEMS WITH ABLATION AND HEAT-CONDUCTION IN SOLID ROCKET NOZZLE

关键词:  固体火箭发动机  喷管烧蚀  温度分布

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

摘要:

总结固体火箭复合结构全喷管烧蚀和传热计算中的基本问题:二相跨音速喷管粘流,燃气与喷管壁面的换热,不同材料的热化学烧蚀模型,粒子侵蚀,烧蚀控制机制,移动边界下的瞬时导热,烧蚀与传热的耦合,复合结构全喷管烧蚀和传热的CAD,以及测试等。在解决基本问题的基础上,对复合结构全喷管可获得其烧蚀率和温度分布。

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.