摘要
应用常压和高压差热分析技术研究了催化剂对推进剂组分热分解的影响,测定了催化剂共晶和混合加入时相应推进剂的燃速,分析了热分析与推进剂燃烧过程的异同点,引入高氯酸铵(AP)高温分解起始温度(T_(L-H))的概念并以T_(L-H)衡量了催化剂共晶加入时对丁羟推进剂燃速和压力指数的影响.研究表明,AP高温分解过程对复合推进剂燃烧特性影响较大;热分析与燃速相关性和催化剂加入方式有关;共晶催化剂作用下的复合推进剂燃速特性与氧化剂高温分解有密切关系;压强是影响推进剂燃速和热分解相关性的重要因素,高压下AP高温分解过程和变化能更大程度地反映到推进剂燃速中去。本文同时对产生上述现象的原因作了分析。
TGA, DTA and HPDTA methods have been employed to investigate the influence of various combustion catalysts of propellant upon the thermal decomposition properties of the propellant components. The catalyst has been added into the AP/HTPB propellant either by mixing it with the other components or by doping it with the Ammoniun Perchlorate (AP) crystals through recrystallization, and the relevant burning rates of the propellant have been measured. The inner link and the inherent difference between combustion and the thermal analysis environmental condition have been discussed in this paper. The initial HTD temperature (T_(L-H)) of the AP decomposition has reasonably been introduced in and deduced to measuring the effect of catalysts upon the burning rate and the pressure exponent of the AP / HTPB propellant. It was found that the High Temperature Decomposition (HTD) phase of the AP crystal can affect the combustion of the composite propellant much more greatly than that of the Low Temperature Decomposition (LTD) phase. The correlation efficiency is closely related with the way in which the catalyst is added into the propellant. The experimental pressure is also an important factor that affects the correlation. With an equal catalytic alteration to the HTD process of AP (which can be measured by △T_(L-H)), it owns a greater share under higher pressure in altering the burning rate of the propellant. The mechanism resulting the above phenomena has been discussed in the paper.
出处
《固体火箭技术》
EI
CAS
CSCD
1992年第2期53-62,共10页
Journal of Solid Rocket Technology
基金
自然科学基金项目
关键词
复合推进剂
催化剂
燃烧速度
SUBJECT TERMS
Composite propellant
Combustion catalyst of propellant
Burning rate
Propellant pressure exponent
Thermal analysis
