Abstract/Details

Characterization of nanoscale aluminum and ice solid propellants


2009 2009

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Abstract (summary)

Solid rocket motors are favored for launch applications because of their simplicity and high thrust to weight ratio. Longer space missions and manned missions will require new, higher performance propellants. Preliminary calculations by others have identified the aluminum and water combustion system as having high potential for propulsion applications. Problems achieving and sustaining combustion experienced by early research have been solved through the development of aluminum nanoparticles. As a result, aluminum and water propellants have received renewed attention. Nearly all recent work on nanoscale aluminum and water propellants has been small in scale. The purpose of this work is to provide fundamental propellant characterization and safety testing, providing a foundation for scale up and development of these propellants.

The first part of this work presents a historical overview of research pertinent to the development of aluminum and water propellants. It also discusses aluminum nanoparticles and their characterization. This work also examines the combustion characterization of aluminum and ice propellants experimentally, computationally, and analytically. The safety characterization of propellant formulations in terms of impact, shock, and electrostatic discharge sensitivity are also examined. Procedures for large-scale mixing of the propellant are presented.

Results of this work are as follows: Equilibrium combustion calculations predict Al/H2O/H2O2 propellants to have theoretical vacuum specific impulses of over 350 seconds. The linear burning rate pressure dependence of formulations has been experimentally shown to vary between 0.25-0.43 depending on formulation. Hydrogen peroxide was used to enhance the burn rate of aluminum ice mixtures containing larger nanoparticles to replicate burning characteristics of aluminum ice formulations containing smaller aluminum nanoparticles. The surfactant Neodol 91-6 was successfully used to mix hydrophobic palmitic acid coated aluminum. Sensitivity testing reveals that palmitic acid and Viton aluminum particle coatings have the potential to dramatically decrease the electrostatic discharge ignition sensitivity of dry aluminum Nanopowders. Shock sensitivity tests reveal that mixtures of aluminum and water containing 5% hydrogen peroxide in the water are detonable. Stoichiometric aluminum-ice propellants containing 38 nm Technanogy aluminum were determined to be weakly detonable. All mixtures of aluminum and ice containing between 0-10% hydrogen peroxide were insensitive to impact ignition.

Indexing (details)


Subject
Aerospace engineering;
Mechanical engineering
Classification
0538: Aerospace engineering
0548: Mechanical engineering
Identifier / keyword
Applied sciences; Aluminum; Nanoscale; Propellant; Water
Title
Characterization of nanoscale aluminum and ice solid propellants
Author
Sippel, Travis R.
Number of pages
173
Publication year
2009
Degree date
2009
School code
0183
Source
MAI 48/02M, Masters Abstracts International
Place of publication
Ann Arbor
Country of publication
United States
ISBN
9781109438529
Advisor
Son, Steven F.
Committee member
Pourpoint, Timothee L.; Qiao, Li
University/institution
Purdue University
Department
Mechanical Engineering
University location
United States -- Indiana
Degree
M.S.M.E.
Source type
Dissertations & Theses
Language
English
Document type
Dissertation/Thesis
Dissertation/thesis number
1469923
ProQuest document ID
304989310
Copyright
Database copyright ProQuest LLC; ProQuest does not claim copyright in the individual underlying works.
Document URL
http://search.proquest.com/docview/304989310
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