含锆或氢化锆推进剂的能量特性分析
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摘要
通过CEA软件,研究了Zr粉和Zr H2粉含量、压强及HTPB含量等对含锆或氢化锆推进剂的比冲、密度比冲和燃烧室温度等能量特性的影响。计算结果表明,随着Zr粉、Zr H2粉和Zr/Zr H2混合物含量增加,推进剂比冲下降,但密度比冲呈现先增后减的趋势,含Zr推进剂燃烧室温度先增后减,而含Zr H2推进剂燃烧室温度持续下降;相比于含Al推进剂,密度比冲是含锆或氢化锆推进剂一个显著优势;随着压强增大,能量特性参数均呈现增大趋势;随着HTPB含量减小,推进剂能量特性参数均增大。
CEA software was used to study and analyze the effects of Zr or ZrH_2 powder contents,chamber pressure,and HTPB content on the energy characteristics of the corresponding solid propellants.The energy characteristics include specific impulse,density specific impulse and combustion chamber temperature.The results show that with the increase of Zr(or ZrH_2) powder content,the specific impulse decreases,but the density specific impulse shows a trend of increase first and then decrease.Moreover,the combustion chamber temperature of the Zr-containing propellant was increased first and then decreased,whereas the combustion chamber temperature decreases constantly.Compared to the Al-containing propellants,the density specific impulse of the propellants containing zirconium or its hydride is a significantly advantage.As the pressure increases,the energy characteristic parameters increase.As the HTPB content decreases,the energy characteristics has been improved.
CEA software was used to study and analyze the effects of Zr or ZrH_2 powder contents,chamber pressure,and HTPB content on the energy characteristics of the corresponding solid propellants.The energy characteristics include specific impulse,density specific impulse and combustion chamber temperature.The results show that with the increase of Zr(or ZrH_2) powder content,the specific impulse decreases,but the density specific impulse shows a trend of increase first and then decrease.Moreover,the combustion chamber temperature of the Zr-containing propellant was increased first and then decreased,whereas the combustion chamber temperature decreases constantly.Compared to the Al-containing propellants,the density specific impulse of the propellants containing zirconium or its hydride is a significantly advantage.As the pressure increases,the energy characteristic parameters increase.As the HTPB content decreases,the energy characteristics has been improved.
引文
[1]庞爱民.固体火箭推进剂理论与工程[M].北京:中国宇航出版社,2014.PANG Aimin.Solid rocket propellant theory and engineering[M].Beijing:China Astronautic Publishing House,2014.
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[5]Lempert D B,Brambilla M,Deluca L T.Ballistic effectiveness of Zr-containing composite solid propellants as a function of binder nature and mass fraction[J].Progress in Propulsion Physics,2013(4):15-32.
[6]Alekseev A P,Lempert D B,Nemtsev G G,et al.Combustion of zirconium-containing model compositions of solid propellant[J].Russian Journal of Physical Chemistry B,2012,5(6):997-999.
[7]Min B S,Hyun H S.Study on combustion characteristics and performance of HTPB/AP propellants containing zirconium[J].Journal of Propulsion&Power,2015,28(1):211-213.
[8]Oshima H,Tanabe M,Kuwahara T.Ignition characteristics of Zr with micro ducted rockets[R].AIAA 2006-5248.
[9]李猛,赵凤起,徐司雨,等.含金属氢化物的复合推进剂能量特性[J].固体火箭技术,2014,37(1):86-90.LI Meng,ZHAO Fengqi,XU Siyu,et al.Energetic characteristics of composite propellant containing different metal hydride[J].Journal of Solid Rocket Technology,2014,37(1):86-90.
[10]YANG Yanjing,ZHAO Fengqi,YUAN Zhifeng,et al.On the combustion mechanisms of Zr H2in double-base propellant[J].Physical Chemistry Chemical Physics,2017,48(19):32597-32604.
[2]陈林泉,毛根旺,陈军涛.采用高低燃温组合装药降低喷管内表面温度和烧蚀研究[J].固体火箭技术,2008,31(6):599-601.CHEN Linquan,MAO Genwang,CHEN Juntao.Research on reducing inner surface temperature and ablation rate of nozzle by means of high and low temperature combined propellant[J].Journal of Solid Rocket Technology,2008,31(6):599-601.
[3]赵生国,宋明纲.高固体NEPE高能推进剂研究[C]//中国宇航学会固体火箭推进24届年会文集.2007.ZHAO Shengguo,SONG Minggang.Research on high solid NEPE high energy propellant[C]//The 24th Annual Meeting of Solid Rocket Propulsion of China Academy of Aerospace Society,2007.
[4]Lempert D B,Nechiporenko G N,Manelis G B.Energetic capabilities of high-density composite solid propellants containing zirconium or its hydride[J].Combustion Explosion&Shock Waves,2011,47(1):45-54.
[5]Lempert D B,Brambilla M,Deluca L T.Ballistic effectiveness of Zr-containing composite solid propellants as a function of binder nature and mass fraction[J].Progress in Propulsion Physics,2013(4):15-32.
[6]Alekseev A P,Lempert D B,Nemtsev G G,et al.Combustion of zirconium-containing model compositions of solid propellant[J].Russian Journal of Physical Chemistry B,2012,5(6):997-999.
[7]Min B S,Hyun H S.Study on combustion characteristics and performance of HTPB/AP propellants containing zirconium[J].Journal of Propulsion&Power,2015,28(1):211-213.
[8]Oshima H,Tanabe M,Kuwahara T.Ignition characteristics of Zr with micro ducted rockets[R].AIAA 2006-5248.
[9]李猛,赵凤起,徐司雨,等.含金属氢化物的复合推进剂能量特性[J].固体火箭技术,2014,37(1):86-90.LI Meng,ZHAO Fengqi,XU Siyu,et al.Energetic characteristics of composite propellant containing different metal hydride[J].Journal of Solid Rocket Technology,2014,37(1):86-90.
[10]YANG Yanjing,ZHAO Fengqi,YUAN Zhifeng,et al.On the combustion mechanisms of Zr H2in double-base propellant[J].Physical Chemistry Chemical Physics,2017,48(19):32597-32604.