电控固体推进剂热分解和燃烧性能研究

推进技术 ›› 2018, Vol. 39 ›› Issue (11): 2588-2594.

电控固体推进剂热分解和燃烧性能研究

胡建新,李洋,何志成,段炼,冯浩

重庆大学航空航天学院，重庆 400044,重庆大学航空航天学院，重庆 400044,重庆大学航空航天学院，重庆 400044,重庆大学航空航天学院，重庆 400044,重庆大学航空航天学院，重庆 400044

发布日期:2021-08-15

Study on Thermal Decomposition and Combustion Performance of Electrically Controlled Solid Propellant

College of Aerospace Engineering，Chongqing University，Chongqing 400044，China,College of Aerospace Engineering，Chongqing University，Chongqing 400044，China,College of Aerospace Engineering，Chongqing University，Chongqing 400044，China,College of Aerospace Engineering，Chongqing University，Chongqing 400044，China and College of Aerospace Engineering，Chongqing University，Chongqing 400044，China

Published:2021-08-15

摘要/Abstract

摘要： 针对能实现多次启动和推力可控的固体火箭发动机需求，研究了成型过程快、钝感、电控性能好和贮存稳定的离子盐电控固体推进剂(ECSP)热分解和燃烧性能。采用同步热分析仪(TG-DSC)、钨铼微热电偶、单幅照相技术和扫描电镜-能谱仪，研究了ECSP的热分解特性、燃烧波温度分布、熄火表面形貌以及元素分布。结果表明:ECSP的热分解过程中依次发生PVA分解反应、PVA分解产物与LiClO4强烈相互作用，其中小组分添加剂加快了PVA分解；其燃烧区域分为预热区、凝相反应区、气相反应区；电点火到稳态燃烧过程为:通入电流加热推进剂，ECSP开始点火，释放出大量的热和可燃性气体，产生初步火焰；热解产生的气相产物在气相区域进一步燃烧，同时大量熔岩状明亮颗粒在热分解气流作用下从燃面逸出，在气相区域燃烧并发出明亮的光。本文提出了ECSP的燃烧过程，为该类推进剂燃烧物理模型奠定基础。

关键词: 电控固体推进剂；同步热分析仪；热分解；燃烧波；火焰结构

Abstract: In order to meet the technical requirements of solid rocket motor for controllable thrust and multiple starts and stops， ionic salt electrically controlled solid propellant (ECSP)， which was easy preparation， insensitive， electrically controlled and stable storage， was investigated on thermal decomposition and combustion performance including the flame structure， combustion wave temperature distribution， quenched surface and element distribution. Such performances are investigated by thermogravimetric analysis(TG) and differential scanning calorimetry(DSC)， W-Re micro-thermocouple， flame photo technique， and sanning electron microscopy(SEM)-energy spectrometer. Results show that thermal decomposition process of ECSP includes that PVA firstly decomposed， then those decomposition products of PVA interact with LiClO4. In addition， other additives accelerate decomposition of PVA. The combustion wave is divided into three zones including preheating zone， solid-phase reaction zone， and gas-phase reaction zone. Moreover， the process of the ECSP from ignition applied by current to stable combustion is described. ECSP is preheated by applied electrical power， then ignited， and releasing a large number of heat and gases， finally generating primary flame. Those gases production further combust in gas-phase reaction zone. Meanwhile， a large number of lava-like bright particles are ejected from the burning surface with gas production， and burn in the gas phase. The combustion process of ECSP propellant is suggested， which builds the foundations for combustion physical model of those propellants.

Key words: Electrically controlled solid propellant (ECSP)；Thermogravimetric-differential scanning calorimetry (TG-DSC)；Thermal decomposition；Combustion wave；Flame structure

胡建新,李洋,何志成,段炼,冯浩. 电控固体推进剂热分解和燃烧性能研究[J]. 推进技术, 2018, 39(11): 2588-2594.

HU Jian-xin,LI Yang,HE Zhi-cheng,DUAN Lian,FENG Hao. Study on Thermal Decomposition and Combustion Performance of Electrically Controlled Solid Propellant[J]. Journal of Propulsion Technology, 2018, 39(11): 2588-2594.

参考文献

[1] 王秀萍. 美国固体火箭发动机的发展及其在机载战术导弹上的应用[J]. 航空兵器, 2016, (3): 14-17.
[2] 彭瑾, 熊本炎. 标准-3导弹固体火箭发动机关键技术分析[J]. 飞航导弹, 2015, (6): 76-80.
[3] 张育林. 变推力液体火箭发动机及其控制技术[M]. 北京:国防工业出版社, 2001.
[4] 聂聆聪, 张政伟, 李岩. 燃气发生器压力闭环波动描述函数分析方法研究[J]. 推进技术, 2016, 37(3):540-545. (NIE Ling-cong, ZHANG Zheng-wei, LI Yan. Research of Describing Function Method on Gas Generator Pressure Closed-Loop Oscillation[J]. Journal of Propulsion Technology, 2016, 37(3): 540-545.)
[5] 田赤军, 黄海龙, 高新锋, 等. 低燃速贫氧推进剂燃气发生器端面燃烧规律动态诊断研究[J]. 推进技术, 2015, 36(6): 933-939. (TIAN Chi-jun, HUANG Hai-long, GAO Xin-feng, et al. Diagnosis of Transient End Burning Law for Gas Generator with Low Burning Velocity Fuel Rich Propellant[J]. Journal of Propulsion Technology, 2015, 36(6): 933-939.)
[6] Tao Y, Wu X, Chen X, et al. Design of a Micro Solid Rocket Motor[C]. USA: Joint Propulsion Conference and Exhibit, 1997.
[7] Sawka W N. Highly Insensitive, Solid State, Electrically-Controlled Propellants for Divert Propulsion[R]. Digital Solid State Propulsion LLC, N06-181.
[8] Sawka W N. Family of Modifiable High Performance Electrically Controlled Propellant and Explosives[P]. US: 0067789, 2009-05-15.
[9] Sawka W N. Solid State Digital Propulsion-Cluster Thrusters-for Small Satellites, Using High Performance Electrically Controlled Extinguishable Solid Propellant[C]. USA: 19th annual AIAA/USU Conference on Small Satellites, 2005.
[10] Sawka W N, McPherso M. Electrical Solid Propellants: A Safe, Micro to Macro Propulsion Technology[C]. USA: 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013.
[11] Sawka W N. Controllable Digital Solid State Cluster Thruster Rocket Propulsion and Gas Generation[P]. US: 0134924, 2008-05-05.
[12] Amrousse R. Hydroxylammonium Nitrate(HAN)-Based Green Propellant as Alternative Energy Resource for Potential Hydrazine Substitution: From Lab Scale to Pilot Plant Scale-Up[J]. Combustion and Flame, 2017, 176: 334–348.
[13] Amrousse R. New HAN-Based Mixtures for Reaction Control System and Low Toxic Spacecraft Propulsion Subsystem: Thermal Decomposition and Possible Thruster Applications[J]. Combustion and Flame, 2015, 162: 2686–2692.
[14] Sawka W N. Electrode Ignition and Control of Electrically Ignitable Materials[P]. US: 8857338, 2009-05-15.
[15] Marshall B T. Lithium Perchlorate as a Solid/Liquid State Oxygen Source for Molecular Beam Epitaxy[D]. USA: Georgia Institute of Technology, 2015.
[16] Jeffrey W G, David L V, Takashi K. Thermal Decomposition Chemistry of Poly(vinyl alcohol)[J]. ACS Symposium Series, 1994, 599: 161-185.
[17] 邓明周. PVA基聚合物电解质的制备及应用[D]. 长沙:中南大学, 2012.(编辑:张荣莉)　　　　　　　　　　　　　　收稿日期:2017-09-28；修订日期:2017-11-13。通讯作者:胡建新,博士,教授,研究领域为新型推进技术。E-mail: hujianxin@cqu.edu.cn