Pre and post-burning analysis of nano-aluminized solid rocket propellants

L. Galfetti; L.T. DeLuca; F. Severini; G. Colombo; L. Meda; G. Marra

首页> 外文期刊>Aerospace science and technology >Pre and post-burning analysis of nano-aluminized solid rocket propellants

【24h】

Pre and post-burning analysis of nano-aluminized solid rocket propellants

机译：纳米铝固体火箭推进剂的燃烧前和燃烧后分析

获取原文

获取原文并翻译 | 示例

掌桥外文数据库（机构版） >>

开具论文收录证明 >>

文献代查 >>

页面导航

摘要
著录项
相似文献
相关主题

摘要

Nano-aluminized propellants are investigated and compared with corresponding micro-aluminized propellants in order to evaluate the actual pros and cons in the use of metal nano-powders for solid rocket applications. A detailed characterization of the original metal powder and condensed combustion products is performed and discussed. Under the explored operating conditions, the results confirm that nano-aluminized propellants show larger steady burning rate, without significant change in pressure sensitivity, and lower aggregation/agglomeration phenomena in combustion products. Combustion efficiency is in turn favored by those factors reducing the importance of aggregation/agglomeration phenomena in the combustion process.

机译：对纳米铝化推进剂进行了研究，并将其与相应的微铝化推进剂进行比较，以评估在固体火箭应用中使用金属纳米粉体的实际优缺点。进行并讨论了原始金属粉末和冷凝的燃烧产物的详细表征。在探索的工作条件下，结果证实纳米铝化推进剂显示出较大的稳定燃烧速率，而压力敏感性没有明显变化，并且燃烧产物中的聚集/团聚现象较低。那些降低了燃烧过程中聚集/聚集现象的重要性的因素又有利于燃烧效率。

著录项

来源
《Aerospace science and technology》 |2007年第1期|p.26-32|共7页
作者
L. Galfetti; L.T. DeLuca; F. Severini; G. Colombo; L. Meda; G. Marra;
展开▼
作者单位

Politecnico di Milano, SPLab, 34 Via La Masa, 20158 Milan, Italy;

展开▼
收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
中图分类航空、航天;
关键词
nano-aluminum; composite solid propellant; condensed combustion products;

机译：纳米铝;复合固体推进剂;凝结燃烧产物;

相似文献

外文文献
中文文献
专利

1. Burning of Nano-Aluminized Composite Rocket Propellants [J] . L.T.De Luca, L.Galfetti, F.Severini, Combustion, Explosion, and Shock Waves . 2005,第6期

机译：纳米铝复合火箭推进剂的燃烧
2. Features of heat transfer in a pre-nozzle volume of a solid-propellant rocket motor with charges of complex shapes [J] . B.Ya. Benderskiy, A.A. Chernova Thermophysics and Aeromechanics . 2018,第2期

机译：固体推进剂火箭电机的预喷嘴容积中的传热特征，具有复杂形状的电荷
3. Calculation of pressure in a solid-propellant rocket motor with the use of a real dependence of the solid propellant burning rate on pressure [J] . Lipanov A. M. Combustion, Explosion, and Shock Waves . 2017,第5期

机译：使用实际推进剂燃烧率的实际依赖性对压力的实际依赖性计算固体推进剂火箭电动机的压力
4. EXPERIMENTAL INVESTIGATION AND NUMERICAL MODELING OF THE CONDENSED COMBUSTION PRODUCTS OF MICRO AND NANO-ALUMINIZED SOLID PROPELLANTS [C] . Luciano Galfetti, Luiqi T. DeLuca, Febo Severini, International Astronautical Congress(IAC2006); 20061002-06; Valencia(ES) . 2006

机译：微米和纳米铝固体推进剂凝结燃烧产物的实验研究和数值模拟
5. A simulation of the flow near a burning propellant in a solid propellant rocket motor. [D] . Ma, Yiping. 1990

机译：固体推进剂火箭发动机中燃烧推进剂附近流动的模拟。
6. Single-Walled Carbon Nanotubes (SWCNTs) as Solid-Contact in All-Solid-State Perchlorate ISEs: Applications to Fireworks and Propellants Analysis [O] . Saad S. M. Hassan, Ahmed Galal Eldin, Abd El-Galil E. Amr, 2019

机译：在所有固态高氯酸盐ISE中作为固体接触的单壁碳纳米管（SWCNT）：在烟花爆竹分析中的应用
7. Neki aspekti performansi raketnih goriva i pravci razvoja čvrstih raketnih goriva / Some aspects of rocket propellant performances and solid rocket propellant development tendencies [O] . Radun Jeremić 2004

机译：Neki aspekti performansi raketnih goriva i pravcirazvojačvrstihraketnihgoriva /火箭推进剂性能和固体火箭推进剂发展趋势的某些方面
8. Pre- and Post-Burning Analysis of Nano-Alluminized Propellants. Comparison of Four Russian Nano-Al Powders [R] . De Luca, L., Galfetti, L. 2004

机译：纳米镀铝推进剂的前后燃烧分析。四种俄罗斯纳米铝粉的比较

Pre and post-burning analysis of nano-aluminized solid rocket propellants

摘要

著录项

相似文献

相关主题

期刊订阅