1) Burning rate pressure exponent
燃速压强指数
1.
Analysis and discrimination of the burning rate pressure exponent of AP-CMDB propellants;
AP-CMDB推进剂燃速压强指数的变化分析与辨识
2) burning rate pressure exponent
燃速压力指数
1.
In order to study combustion characteristics of RDX nitramine propellant furtherly,the burning rate pressure exponents for three RDX nitramine propellants were investigated by closed bomb test and data-treatment in the different range of pressure,and were compared with that of the single base propellant.
为深入研究含黑索今(RDX)类硝胺发射药的燃烧性能,采用密闭爆发器燃烧实验和分段数据处理分析方法,研究了3种含RDX硝胺发射药的燃速压力指数变化规律,并与传统的单基发射药进行了对比分析。
2.
The test results showed that burning rate pressure exponent values of the JMZ propellant are large at low pressure,as those of RDX nitramine propellants,but the burning rate pressure exponent values gradually diminish along wi.
结果表明,JM Z发射药在低压下的燃速压力指数较大,具有高含量RDX硝胺发射药的共同特征,但在高压下的燃速压力指数逐渐变小,与制式发射药相当,在燃速压力指数的变化过程中不存在明显的转折现象。
3.
In order to study the interior ballistic behavior of new type high-energy propellant,influence of burning rate pressure exponent of propellant on gun interior ballistic behavior was theoretically simulated by classical interior ballistic mathematical model.
为研究新型高能发射药的内弹道性能,采用经典内弹道数学模型理论模拟了发射药的燃速压力指数对火炮内弹道性能的影响。
3) negative exponent gas generating propellant
负压强指数燃气发生剂
4) pressure exponent
压强指数
1.
Effects of AP content and granularity gradation on pressure exponent of boron-based fuel-rich propellant;
AP含量及粒度级配对含硼富燃推进剂压强指数的影响
2.
By means of coupled DSC-TG and burning rate measurement methods,some burning rate modifiers such as nano-PbO,QC,C,SEA,Fe2O3 and Co3O4 were selected to reduce the pressure exponent of CMDB propellant and AP composite propellant,moreover their effects on combustion properties of NEPE propellant were discussed.
利用DSC-TG联用和燃速测试等方法,从降低CMDB推进剂和AP类复合推进剂压强指数的燃速调节剂中,筛选出了纳米PbO、QC、C及SEA、Fe2O3、Co3O4等燃速调节剂,并考察了这些燃速调节剂对NEPE推进剂燃烧性能的影响。
3.
In order to obtain the main factors affecting the pressure exponent of boron-based fuel-rich propellant,propellant samples were prepared via mix of the compositions in mixing machine,pouring in vacuum and curing at constant temperature.
为获得含硼推进剂压强指数的主要影响因素,采用捏合机混合物料,真空浇注、恒温固化的方法制备推进剂试样,靶线法测试推进剂(0。
5) Pressure index
压强指数
1.
Based on the research into the influence of the grain sizes and grain size stage matches of high energy solid propellants upon the burning rate and the pressure indexes, some suitable grain size stage match methods are given.
研究了高能推进剂固体组份粒度及粒度级配对燃速和压强指数的影响。
6) negative pressure exponant
负压强指数
1.
This paper indicates that the doping of Ca+ + can make the pressure exponant decline in the pressure preseeure of solid solid rocket, and even the negative pressure exponant appears in some pressure range(7-8.
５ＭＰａ）压强指数出现负值，这为进一步完善“统一模型”提供了依据，为负压强指数推进剂的研制和进一步降低硝胺／ＡＰ复合推进剂的压强指数提供了新的途径。
补充资料：压强指数
分子式：
CAS号：
性质：推进剂线性燃速随燃烧室压强的变化率，可表达为n=。火箭发动机正常工作状态，要求推进剂n值必须小于1，n值小，发动机燃烧室的压强波动小，有利于壳体质量的减轻，提高质量比。
CAS号：
性质：推进剂线性燃速随燃烧室压强的变化率，可表达为n=。火箭发动机正常工作状态，要求推进剂n值必须小于1，n值小，发动机燃烧室的压强波动小，有利于壳体质量的减轻，提高质量比。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条