CAJ | 학술논문

介绍了一种边界层控制方法，阐明了该方法降低喷管喉衬烧蚀的机理，通过降低喷管喉衬的温度和喷管边界层内氧化组分（ H2 O、CO2和OH）的浓度，从而降低喷管的烧蚀率。从理论研究和试验研究两方面阐述了该方法的国内外研究发展现状。在理论方面，介绍了该方法降低喷管喉衬烧蚀的效果，可降低喉衬烧蚀率80％以上；在试验方面，介绍了该方法降低喉衬烧蚀的验证性试验研究，可将喉衬烧蚀率降低到不可测量的程度。最后，总结了该方法目前的发展水平，分析了该方法存在的问题及发展趋势。
개소료일충변계층공제방법，천명료해방법강저분관후츤소식적궤리，통과강저분관후츤적온도화분관변계층내양화조분（ H2 O、CO2화OH）적농도，종이강저분관적소식솔。종이론연구화시험연구량방면천술료해방법적국내외연구발전현상。재이론방면，개소료해방법강저분관후츤소식적효과，가강저후츤소식솔80％이상；재시험방면，개소료해방법강저후츤소식적험증성시험연구，가장후츤소식솔강저도불가측량적정도。최후，총결료해방법목전적발전수평，분석료해방법존재적문제급발전추세。
A nozzle boundary-layer control system was introduced to reduce solid rocket motor nozzle erosion. This design not only reduces the temperature of nozzle throat surface but also reduces the mass fractions of the oxidizing gaseous species such as H2O,CO2 and OH in the combustion products,thus reducing the chemical attack on the nozzle throat surface.This paper gives an re-search status of this method at home and abroad in theoretical and experimental aspects.The effectiveness of this design for mitiga-ting nozzle erosion was introduced in theoretical aspect,which can reduce nozzle erosion by more than 80%.In experimental aspect, the effectiveness of this system was demonstrated,and this method can achieve zero erosion rate.Research status of this method was summarized,and future work was analyzed.