2026-09-26T16:07:46Zhttps://dspace.mit.edu/server/oai/request

oai:dspace.mit.edu:1721.1/92972022-01-13T07:54:11Zcom_1721.1_7582com_1721.1_7581col_1721.1_131023

Alan H. Epstein. Protz, Christopher S. (Christopher Stephen), 1977- Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics 2005-08-23T12:00:00Z 2005-08-23T12:00:00Z 2000 2000 http://hdl.handle.net/1721.1/9297 45839129 Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2000. Includes bibliographical references (leaves 95-97). This thesis discusses the systems analysis of a storable bipropellant micro-rocket engine. Micro-rockets are built using MEMS technology and are projected to deliver a thrust to weight ratio up to two orders of magnitude greater than conventional rocket motors at small thrust levels making them very attractive for satellite propulsion applications and propulsion of very small launch vehicles. Several propellant combinations and engine cycles have been analyzed. Propellant combinations have been evaluated for a 125 atm combustion chamber on the basis of their performance, handling, and cooling properties. A non-toxic hydrogen peroxide/ethanol combination (302 s Isp) is chosen over a nitrogen tetroxide/hydrazine combination (322 s Isp) and a hydrogen peroxode/JP-7 combination (315 s Isp) on the basis of handling and cooling properties. Studies indicate that nitrogen tetroxide/hydrazine expander and decomposition topping cycles and hydrogen peroxide/ethanol and hydrogen peroxide/JP-7 decomposition topping cycles are feasible. It is shown that a 300 atm turbopump feed system is possible while further investigations on bearings and pump design are required to fully validate the concept. The analysis suggests that the storable bipropellant micro-rocket engine concept is feasible and identifies the engineering challenges ahead. by Christopher S. Protz. S.M. 97 leaves 5665875 bytes 5665632 bytes application/pdf application/pdf eng Massachusetts Institute of Technology M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. http://dspace.mit.edu/handle/1721.1/7582 Aeronautics and Astronautics. Systems analysis of a microfabricated storable bipropellant rocket engine Thesis application/pdf false Publication unknown unknown <Publication xmlns="https://www.openaire.eu/cerif-profile/1.1/" id="f9e33f7b-df0a-4121-9ca8-e2e0bd54fdc8"> <Type xmlns="https://www.openaire.eu/cerif-profile/vocab/COAR_Publication_Types">http://purl.org/coar/resource_type/c_1843</Type> <Language>eng</Language> <Title>Systems analysis of a microfabricated storable bipropellant rocket engine</Title> <PublishedIn> <Publication> </Publication> </PublishedIn> <PublicationDate>2000</PublicationDate> <Authors> <Author> <DisplayName>Protz, Christopher S. (Christopher Stephen), 1977-</DisplayName> <Affiliation> <OrgUnit> </OrgUnit> </Affiliation> </Author> </Authors> <Editors> </Editors> <Publishers> <Publisher> <DisplayName>Massachusetts Institute of Technology</DisplayName> <OrgUnit /> </Publisher> </Publishers> <License>http://dspace.mit.edu/handle/1721.1/7582</License> <Keyword>Aeronautics and Astronautics.</Keyword> <Abstract>This thesis discusses the systems analysis of a storable bipropellant micro-rocket engine. Micro-rockets are built using MEMS technology and are projected to deliver a thrust to weight ratio up to two orders of magnitude greater than conventional rocket motors at small thrust levels making them very attractive for satellite propulsion applications and propulsion of very small launch vehicles. Several propellant combinations and engine cycles have been analyzed. Propellant combinations have been evaluated for a 125 atm combustion chamber on the basis of their performance, handling, and cooling properties. A non-toxic hydrogen peroxide/ethanol combination (302 s Isp) is chosen over a nitrogen tetroxide/hydrazine combination (322 s Isp) and a hydrogen peroxode/JP-7 combination (315 s Isp) on the basis of handling and cooling properties. Studies indicate that nitrogen tetroxide/hydrazine expander and decomposition topping cycles and hydrogen peroxide/ethanol and hydrogen peroxide/JP-7 decomposition topping cycles are feasible. It is shown that a 300 atm turbopump feed system is possible while further investigations on bearings and pump design are required to fully validate the concept. The analysis suggests that the storable bipropellant micro-rocket engine concept is feasible and identifies the engineering challenges ahead.</Abstract> <Access xmlns="http://purl.org/coar/access_right" > </Access> </Publication>