HAN基电控固体推进剂电热耦合特性及燃烧特性实验研究

doi:10.13675/j.cnki.tjjs.200821

推进技术 ›› 2021, Vol. 42 ›› Issue (6): 1410-1417.DOI: 10.13675/j.cnki.tjjs.200821

HAN基电控固体推进剂电热耦合特性及燃烧特性实验研究

鲍立荣^1,2，汪辉^1,2，王志文^1,2，谢海明^1,2，向书杰^1,2，张伟^1,2，张晓军³，黄寅生²，沈瑞琪^1,2，叶迎华^1,2

1.南京理工大学空间推进技术研究所，江苏南京 210094;2.南京理工大学化工学院，江苏南京 210094;3.西安近代化学研究所，陕西西安 710065

出版日期:2021-06-15 发布日期:2021-08-15
作者简介:鲍立荣，博士生，研究领域为电化学推进技术。E-mail：blr1216@njust.edu.cn
基金资助:
中央高校基本科研业务专项（30919012102）；西安近代化学研究所开放合作创新基金（SYJJ17；SYJJ200314）。

Experimental Study on Electrothermal Coupling and Combustion Characteristics of HAN-Based Electrically Controlled Solid Propellant

1.Institute of Space Propulsion，Nanjing University of Science and Technology，Nanjing 210094，China;2.School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China;3.Xi’an Modern Chemistry Research Institute，Xi’an 710065，China

Online:2021-06-15 Published:2021-08-15

摘要/Abstract

摘要： 为了探究HAN基电控固体推进剂（ECSP）的电热耦合特性和燃烧性能，通过改变施加电压和环境压力对ECSP进行燃烧性能测试。在ECSP燃烧性能测试装置中采用电压、电流探头记录燃烧过程中通过推进剂的电压和电流，利用高速摄影仪记录推进剂的燃烧过程，借助法拉第电化学分解定律计算推进剂理论电化学分解质量在总燃烧消耗质量中的占比，分析电压和压力对推进剂燃速和质量损失的影响，同时拟合出ECSP燃速（r）与功率（P）和压力（p）的经验公式。结果表明：随着电压和压力的增加，ECSP理论电化学分解质量和实际燃烧质量增加，电解质量占比降低，燃速和质量损失增加。在ECSP的可控燃烧范围内，其燃速与功率和压力满足r = 0.0105P^0.705p^0.251。本文得到了热分解反应在ECSP的燃烧过程中占主导地位是高压力下造成推进剂不可控燃烧的主要原因，为揭示ECSP的燃烧可控机理提供理论基础。

关键词: 电控固体推进剂;电热耦合特性;燃烧性能;电化学分解;热分解反应

Abstract: In order to explore the electrothermal coupling characteristics and combustion performance of HAN-based electrically controlled solid propellant （ECSP）， the combustion performance test of ECSP was performed by changing the voltage and pressure. In the ECSP combustion performance test device， voltage probe and current probe were used to record the voltage and current passing through the propellant during the combustion process. The combustion process of propellant was recorded by high speed camera. According to Faraday's law of electrochemical decomposition， the proportion of theoretical electrochemical decomposition mass in total combustion consumption mass of propellant was calculated. The effects of voltage and pressure on the burning rate and mass loss of propellant were analyzed， and the empirical formulas of ECSP burning rate （r） and power （P） and pressure （p） were fitted. The results show that with the increase of voltage and pressure， the theoretical electrochemical decomposition mass and actual combustion mass of ECSP increase， the electrolysis mass ratio decreases， and the burning rate and mass loss increase. Within the controllable combustion range of ECSP， the empirical formula of ECSP burning rate can be fitted as r = 0.0105P^0.705p^0.251. This article shows that the thermal decomposition reaction is dominant in the combustion process of ECSP and is the main reason for the uncontrollable combustion of the propellant under high pressure. It provides a theoretical basis for revealing the controllable combustion mechanism of ECSP.

Key words: Electrically controlled solid propellant;Electrothermal coupling characteristics;Combustion performance;Electrochemical decomposition;Thermal decomposition reaction

鲍立荣，汪辉，王志文，谢海明，向书杰，张伟，张晓军，黄寅生，沈瑞琪，叶迎华. HAN基电控固体推进剂电热耦合特性及燃烧特性实验研究[J]. 推进技术, 2021, 42(6): 1410-1417.

BAO Li-rong^1,2, WANG Hui^1,2, WANG Zhi-wen^1,2, XIE Hai-ming^1,2, XIANG Shu-jie^1,2, ZHANG Wei^1,2, ZHANG Xiao-jun³, HUANG Yin-sheng², SHEN Rui-qi^1,2, YE Ying-hua^1,2. Experimental Study on Electrothermal Coupling and Combustion Characteristics of HAN-Based Electrically Controlled Solid Propellant[J]. Journal of Propulsion Technology, 2021, 42(6): 1410-1417.

参考文献

[1] 鲍立荣，陈永义，陈苏杭，等. 可控固体推进技术研究进展［J］. 推进技术， 2020， 41（5）： 961-973.
[2] Tahsini A， Farshchi M. Thrust Termination Dynamics of Solid Propellant Rocket Motors［J］. Journal of Propulsion and Power， 2007， 23（5）： 1141-1143.
[3] Grix C E， Sawka W N. Family of Modifiable High Performance Electrically Controlled Propellants and Explosives［P］. US： 993084， 2014-11-18.
[4] Sawka W N， Mcpherson M. Electrical Solid Propellants： A Safe， Micro to Macro Propulsion Technology［C］. San Jose： 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference， 2013.
[5] Nicholas A， FinnE T， Sawka W N， et al. Spinsat Mission Overview［C］. Logan： 27th Annual AIAA/USU Conference on Small Satellites， 2013.
[6] Chung K， Rozumov E， Kaminsky D， et al. Development of Electrically Controlled Energetic Materials （ECEM）［J］. ECS Transactions， 2013， 50（40）： 59-66.
[7] Zamir I， Grinstein D， Gany A. Testing Electric Effects on the Burning Rate of Ammonium Nitrate-Based Solid Propellants［J］. International Journal of Energetic Materials and Chemical Propulsion， 2017， 16（1）： 39-47.
[8] Koehler F， Langhenry M， Summers M， et al. Electric Propellant Solid Rocket Motor Thruster Results Enabling Small Satellites［C］. Logan： 30th Annual AIAA/USU Conference on Small Satellites， 2017.
[9] 胡建新，李洋，何志成，等. 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.
[10] He Z C， Xia Z X， Hu J X， et al. Lithium-Perchlorate/Polyvinyl-Alcohol-Based Aluminized Solid Propellants with Adjustable Burning Rate［J］. Journal of Propulsion and Power， 2019， 35（3）： 512-519.
[11] 鲍立荣，张伟，陈永义，等. HAN基电控固体推进剂的热分解和电导率特性［J］. 含能材料， 2019， 27（9）： 743-748.
[12] Bao L R， Wang H， Zheng T T， et al. Exploring the Influences of Conductive Graphite on Hydroxylammonium Nitrate （HAN）-Based Electrically Controlled Solid Propellant［J］. Propellants， Explosives， Pyrotechnics， 2020， 45（11）： 1790-1798.
[13] Bao L R， Zhang W， Zhang X J， et al. Impact of MWCNT/Al on the Combustion Behavior of Hydroxyl Ammonium Nitrate （HAN）-Based Electrically Controlled Solid Propellant［J］. Combustion and Flame， 2020， 218： 218-228.
[14] He Z C， Xia Z X， Hu J X， et al. Thermodynamic Properties of Polyvinyl Alcohol Binder of Electrically Controlled Solid Propellant［J］. Journal of Polymer Research， 2019， 26（9）.
[15] He Z C， Xia Z X， Hu J X， et al. Thermal Decomposition and Kinetics of Electrically Controlled Solid Propellant Through Thermogravimetric Analysis［J］. Journal of Thermal Analysis and Calorimetry， 2020， 139（3）： 2187-2195.
[16] Hiatt A T， Frederick R A. Laboratory Experimentation and Basic Research Investigating Electric Solid Propellant Electrolytic Characteristics［C］. Salt Lake City： 52nd AIAA/SAE/ASEE Joint Propulsion Conference， 2016.
[17] 王新强，邓康清，李洪旭，等. 电控固体推进剂点火技术研究［J］. 固体火箭技术， 2017， 40（3）： 313-318.
[18] Glascock M S， Rovey J L， Williams S， et al. Observation of Late-Time Ablation in Electric Solid Propellant Pulsed Microthrusters［C］. Salt Lake City： 52nd AIAA/SAE/ASEE Joint Propulsion Conference， 2016.
[19] Glascock M S， Rovey J L， WIlliams S， et al. Plume Characterization of Electric Solid Propellant Pulsed Microthrusters［J］. Journal of Propulsion and Power， 2017， 33（4）： 870-880.
[20] Glascock M S， Drew P D， Rovey J L， et al. Thermodynamic Properties of Hydroxylammonium Nitrate-Based Electric Solid Propellant Plasma［J］. Journal of Thermophysics and Heat Transfer， 2020， 34（3）： 522-529.
[21] Baird J K， Huang S， Frederick R A. Space Charge Limited Conduction and Internal Electric Field in the Polyvinyl Alcohol + Hydroxyl Ammonium Nitrate Solid Propellant［C］. Cincinnati： 2018 Joint Propulsion Conference， 2018.
[22] Baird J K， Huang S， Frederick R A. Space Charge Limited Conduction in Polyvinyl+Hydroxyl Ammonium Nitrate Solid Propellant［J］. Journal of Propulsion and Power， 2020， 36（3）： 479-484.

HAN基电控固体推进剂电热耦合特性及燃烧特性实验研究

Experimental Study on Electrothermal Coupling and Combustion Characteristics of HAN-Based Electrically Controlled Solid Propellant

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价