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ENCIT 2018
Brazilian Congress of Thermal Sciences and Engineering
EFFECTS OF O3 ADDITION ON AMMONIUM PERCHLORATE-BASED SOLID PROPELLANT COMBUSTION
Submission Author:
Ivi Silva , PA
Co-Authors:
Ivi Silva, Taiane Pereira Pantoja, Rene Gonçalves
Presenter: Ivi Silva
doi://10.26678/ABCM.ENCIT2018.CIT18-0797
Abstract
When a rocket is launched, to overcome the gravitational force that the Earth exerts on the rocket, a major boost is needed, called specific impulse. For this purpose several rocket models and different types of fuels capable of achieving such a result have been developed, as solid, liquid or hybrid fuel - which is nothing more than the joining of the two previous ones. The choice among fuel types is made according to their specificities, for example: the solid fuel presents a high specific impulse, and the liquid one has a lower impulse, but its burning can be controlled. Another advantage of solid propellants compared to liquid propellants are their lower cost and ease of production, mostly. Examples of oxidizers used in solid propellants are: Ammonium Perchlorate (AP), Ammonium Nitrate (AN), Ammonium Dintramide (ADN), Cyclotrimethylenetrinitramine (RDX) together with a binder, they compose a solid propellant. In various aerospace projects produced it is observed that one of the most used propellant grains is the AP/HTPB due to the characteristics of the salt, which decomposes generating a high quantity of gaseous oxygen. Usually a solid propellant consists of the oxidizer, binders (connectors and auxiliaries in the production of gases), such as Hydroxyl-Terminated Polybutadiene (HTPB) e Glicidyl Azide Polymer (GAP), and ballistic auxiliaries (commonly metals). It is also possible to add additives to the fuels, in order to optimize their burning. As an example, ozone (O3), which is the object in study of this work. The importance of additives that increase propellant fuel efficiency for the advancement of aerospace research is shown at this paper.
Keywords
Ammonium Perchlorate, Combustion, Rocket, ozone, solid propellant
