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Gel propellant has the advantage of controllable flux as liquid propellant and long-term reservation as solid propellant, however, the evaporation and combustion problem of gel spray droplet bores with the gel propellant development and combustor design all the time, and hampers gel propellant practical engineering applications. In this paper, the gel single droplet combustion experiment system is designed and constructed, and then the evaporation and combustion mechanism is explored deeply based on the experimental phenomena of organic gel unsymmetrical dimethylhydrazine (UDMH) single droplet burning in nitrogen tetroxide. The organic gel spray droplet multi-component evaporation model is developed for three different evaporation phases of the gel layer, i.e. the forming, expanding and bursting of the gel layer based on the single droplet evaporation characteristics in experiment, and then the gel single droplet vaporization in high temperature gas phase is numerically simulated and compared with the result of conventional liquid droplet using the elementary model parameters and physic property parameters. The result shows that the gel content on the droplet surface increases slowly at the beginning of evaporation, however it would increase rapidly to a mass fraction of 95% and form the gel layer in a limited time after exceeding a critical evaporation time, which results in surface mass flux dropping to 0 and surface temperature reaching the UDMH boil point rapidly. After the gel layer forming, the droplet radius and surface UDMH vapor mass fraction exhibit oscillation as the swelling-bursting phenomena in experiment. The gel droplet surface temperature holds above the boil point and the mass flux of gel droplet inner boiling evaporation is stronger than the conventional liquid droplet surface steady evaporation which makes the life time of gel droplet much shorter.
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Keywords:
- gel propellant /
- spray droplet /
- gel layer /
- evaporation model
[1] Rahimi S, Hasan D, Peretz A 2004 J. Propul. Power 20 93
[2] Yasuhara W K, Finato S R, Olson A M 1993 2nd Annual AIAA SDIO Interceptor Technology Conference (Albuquerque: American Institute of Aeronautics and Astronautics)
[3] Palaszewski B, Powell R 1994 J. Propul. Power 10 828
[4] Feng S J, He B, Nie W S 2009 J. Rocket Propul. 35 1 (in Chinese) [丰松江, 何博, 聂万胜 2009 火箭推进 35 1]
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[6] Han W, Shan S Q, Du Z G, Yu J, Yang C, Wu J 2009 Chem. Propel. & Polymeric Mater. 7 38 (in Chinese) [韩伟, 单世群, 杜宗罡, 于君, 杨超, 吴金 2009 化学推进剂与高分子材料 7 38]
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[9] Solomon Y, Natan B, Cohen Y 2009 Combust Flame 156 261
[10] Desyatkov A, Madlener K, Ciezki H K 2008 44th AIAA/ASME /SAE/ASEE Joint Propulsion Conference & Exhibit (Hartford: American Institute of Aeronautics and Astronautics)
[11] Weiser V, Gläser S, Kelzenberg S, Eisenreich N, Roth E 2005 41st AIAA/ASME /SAE/ASEE Joint Propulsion Conference & Exhibit (Tucson: American Institute of Aeronautics and Astronautics)
[12] Mueller D C 1997 Ph. D. Dissertation (Pennsylvania: The Pennsylvania State University)
[13] Kunin A, Natan B, Greenberg J B 2009 Progress in Propulsion Physics 1 225
[14] Zhang M Z 2010 J. Rocket Propul. 36 1 (in Chinese) [张蒙正 2010 火箭推进 36 1]
[15] Catoire L, Chaumeix N, Pichon S, Paillard C 2006 J. Propul. Power 22 120
[16] Li Y Q, He P 2008 Transactions of Csice 26 56 (in Chinese) [李云清, 何鹏 2008 内燃机学报 26 56]
[17] Hardt S, Wondra F 2008 J. Comput. Phys. 227 5871
[18] Arnold S L http: // www. gentoogeek. org / steves_world / hypergol_properties. pdf [2011-9-25]
[19] He B, Xiao Q, Nie W S, Feng S J 2011 Journal of the Academy of Equipment Command & Technology 22 55 (in Chinese) [何博, 肖强, 聂万胜, 丰松江 2011 装备指挥技术学院学报 22 55]
[20] He B, Nie W S, Feng S J, Li G Q 2011 Adv. Mater. Res. 297 2333
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[1] Rahimi S, Hasan D, Peretz A 2004 J. Propul. Power 20 93
[2] Yasuhara W K, Finato S R, Olson A M 1993 2nd Annual AIAA SDIO Interceptor Technology Conference (Albuquerque: American Institute of Aeronautics and Astronautics)
[3] Palaszewski B, Powell R 1994 J. Propul. Power 10 828
[4] Feng S J, He B, Nie W S 2009 J. Rocket Propul. 35 1 (in Chinese) [丰松江, 何博, 聂万胜 2009 火箭推进 35 1]
[5] Wang L, Li J, Yang Y J 2004 Acta Phys. Sin. 53 160 (in Chinese) [王理, 李黎, 杨亚江 2004 53 160]
[6] Han W, Shan S Q, Du Z G, Yu J, Yang C, Wu J 2009 Chem. Propel. & Polymeric Mater. 7 38 (in Chinese) [韩伟, 单世群, 杜宗罡, 于君, 杨超, 吴金 2009 化学推进剂与高分子材料 7 38]
[7] Yang W D, Zhang M Z 2006 J. Rocket Propul. 32 12 (in Chinese) [杨伟东, 张蒙正 2006 火箭推进 32 12]
[8] Zhang M Z, Yang W D, Wang M 2008 J. Propul. Technol. 29 22 (in Chinese) [张蒙正, 杨伟东, 王玫 2008 推进技术 29 22]
[9] Solomon Y, Natan B, Cohen Y 2009 Combust Flame 156 261
[10] Desyatkov A, Madlener K, Ciezki H K 2008 44th AIAA/ASME /SAE/ASEE Joint Propulsion Conference & Exhibit (Hartford: American Institute of Aeronautics and Astronautics)
[11] Weiser V, Gläser S, Kelzenberg S, Eisenreich N, Roth E 2005 41st AIAA/ASME /SAE/ASEE Joint Propulsion Conference & Exhibit (Tucson: American Institute of Aeronautics and Astronautics)
[12] Mueller D C 1997 Ph. D. Dissertation (Pennsylvania: The Pennsylvania State University)
[13] Kunin A, Natan B, Greenberg J B 2009 Progress in Propulsion Physics 1 225
[14] Zhang M Z 2010 J. Rocket Propul. 36 1 (in Chinese) [张蒙正 2010 火箭推进 36 1]
[15] Catoire L, Chaumeix N, Pichon S, Paillard C 2006 J. Propul. Power 22 120
[16] Li Y Q, He P 2008 Transactions of Csice 26 56 (in Chinese) [李云清, 何鹏 2008 内燃机学报 26 56]
[17] Hardt S, Wondra F 2008 J. Comput. Phys. 227 5871
[18] Arnold S L http: // www. gentoogeek. org / steves_world / hypergol_properties. pdf [2011-9-25]
[19] He B, Xiao Q, Nie W S, Feng S J 2011 Journal of the Academy of Equipment Command & Technology 22 55 (in Chinese) [何博, 肖强, 聂万胜, 丰松江 2011 装备指挥技术学院学报 22 55]
[20] He B, Nie W S, Feng S J, Li G Q 2011 Adv. Mater. Res. 297 2333
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