镁铝富燃料推进剂燃烧残渣影响因素理论分析  

Theoretical analysis on combustion residue of magnesium-aluminum fuel-rich propellant

作　　者：胥会祥[1] 赵凤起[1] 

机构地区：[1]西安近代化学研究所,西安710065

出　　处：《固体火箭技术》2006年第3期200-203,共4页Journal of Solid Rocket Technology

摘　　要：用最小自由能法计算了镁铝富燃料推进剂一次燃烧室产物的成分,分析了凝聚相C、Mg和A l产物含量的变化对燃烧残渣的影响;主要探讨了AP含量、Mg/A l比例、HTPB粘合剂含量、燃烧室压强对凝聚相C、Mg、A l燃烧产物含量的影响。计算结果表明,增加AP含量、设计Mg/A l比小于3/5、减小HTPB粘合剂含量、降低燃烧室压强均能减少凝聚相产物含量,有利于降低燃烧残渣。燃气发生器实验结果表明,Mg/A l比例对燃烧残渣影响的实验数据与理论分析一致。The product compositions of magnesium-aluminum fuel-rich propellant in primary chamber were calculated by using minimum free energy method. The effects of condensed phase product content including carbon,magnesium and aluminum on combustion residue were analyzed. The influences of ALP content, Mg/Al ratio, HTPB binder content, pressure of combustion chamber on the content of condensed phase C, Mg, Al in combustion products were discussed mainly. The calculation results show that by using several methods like increasing AP content,determining Mg/Al ratio less than 3/5, reducing HTPB binder content and decreasing pressure of combustion chamber, the molar fraction of condensed phase products can be decreased. All these methods are benefitial to reducing combustion residue. The test results of gas generator indicate that experimental data of the effect of Mg/Al ratio on combustion residue is in accord with theoretical analysis.

关 键 词：镁铝富燃料推进剂 燃烧残渣 凝聚相含量 镁铝比 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]