Hybrid Rocket Motor (HRM) Test Stand: An Investigation of the Effects of Additives

Persistent Link:
http://hdl.handle.net/10150/297738
Title:
Hybrid Rocket Motor (HRM) Test Stand: An Investigation of the Effects of Additives
Author:
Schultz, Robert Gregory
Issue Date:
2013
Publisher:
The University of Arizona.
Rights:
Copyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.
Abstract:
In comparison to solid and liquid fueled rockets, hybrids are attractive for their relatively low cost, simple design, and safety, while combining some of the characteristics of both liquid and solid fueled rockets. This paper describes a hybrid rocket motor (HRM) design that was constructed for testing fuels with little to no known experimental data. The HRM utilizes nitrous oxide as the propellant oxidizer and was chemically combusted with paraffin wax based fuels. Paraffin wax is a relatively new type of hybrid rocket fuel and has ample opportunity for research. The paraffin wax was tested alone as a baseline comparison test as well as mixed with two additives: lithium aluminum hydride and magnesium powder. These additives act as performance enhancers in the fuel grain with each additive mixed at 5% and 10% of the fuel mass. This project allowed for 25 total test fires with different propellant combinations. The data was compiled, analyzed, and has given insight to the magnitude in which the new type of fuel and/or the use of additives affect the efficiency of the hybrid rocket engine.
Type:
text; Electronic Thesis
Degree Name:
B.S.
Degree Level:
bachelors
Degree Program:
Honors College; Aerospace Engineering
Degree Grantor:
University of Arizona
Advisor:
Shkarayev, Sergey

Full metadata record

DC FieldValue Language
dc.language.isoenen_US
dc.titleHybrid Rocket Motor (HRM) Test Stand: An Investigation of the Effects of Additivesen_US
dc.creatorSchultz, Robert Gregoryen_US
dc.contributor.authorSchultz, Robert Gregoryen_US
dc.date.issued2013-
dc.publisherThe University of Arizona.en_US
dc.rightsCopyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.en_US
dc.description.abstractIn comparison to solid and liquid fueled rockets, hybrids are attractive for their relatively low cost, simple design, and safety, while combining some of the characteristics of both liquid and solid fueled rockets. This paper describes a hybrid rocket motor (HRM) design that was constructed for testing fuels with little to no known experimental data. The HRM utilizes nitrous oxide as the propellant oxidizer and was chemically combusted with paraffin wax based fuels. Paraffin wax is a relatively new type of hybrid rocket fuel and has ample opportunity for research. The paraffin wax was tested alone as a baseline comparison test as well as mixed with two additives: lithium aluminum hydride and magnesium powder. These additives act as performance enhancers in the fuel grain with each additive mixed at 5% and 10% of the fuel mass. This project allowed for 25 total test fires with different propellant combinations. The data was compiled, analyzed, and has given insight to the magnitude in which the new type of fuel and/or the use of additives affect the efficiency of the hybrid rocket engine.en_US
dc.typetexten_US
dc.typeElectronic Thesisen_US
thesis.degree.nameB.S.en_US
thesis.degree.levelbachelorsen_US
thesis.degree.disciplineHonors Collegeen_US
thesis.degree.disciplineAerospace Engineeringen_US
thesis.degree.grantorUniversity of Arizonaen_US
dc.contributor.advisorShkarayev, Sergey-
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