摘要
采用推进剂性能评估软件(PEP)模拟计算,并比较了液氧+HTPB固体燃料、液氢+固体推进剂和液氦+固体推进剂3种固-液混合火箭推进剂方案的能量水平,分析了3种混合推进剂方案的燃烧特征。结果表明,液氢+固体推进剂和液氦+固体推进剂2种混合推进剂方案可大幅提高固体推进剂能量水平,且燃烧性能可能更优。液氢+GAP固体推进剂和液氦+GAP固体推进剂方案可获得高于3 000 N·s/kg的比冲,高于液氧+HTPB固体燃料方案。
The energetic performances of three hybrid propulsion systems including liquid oxygen＋curative HTPB fuel,liquid hydrogen＋solid propellants and liquid helium＋solid propellants were studied by means of propellant performance evaluation program （PEP） .The calculation results reveal that liquid hydrogen＋solid propellants and liquid helium＋solid propellants may be able to en- hance the energetic performance of almost all the studied solid propellants systems.In particular, the liquid hydrogen＋GAP solid pro- pellant and liquid helium＋GAP solid propellant hybrid systems can attain specific impulse above 3 000 N · s/kg, higher than that of liquid oxygen＋curative HTPB fuel hybrid system.The analysis of combustion process shows that the liquid hydrogen＋solid propel- lants and liquid helium＋solid propellants may possess better combustion performance than liquid oxygen＋curative HTPB fuel hybrid system.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2016年第3期353-357,368,共6页
Journal of Solid Rocket Technology
关键词
固-液混合推进剂
固体推进剂
新型火箭推进技术
solid-liquid hybrid propellant
solid propellant
novel rocket propulsion technique
