| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 1718834 | Aerospace Science and Technology | 2007 | 7 Pages |
Abstract
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.
Related Topics
Physical Sciences and Engineering
Engineering
Aerospace Engineering
