Development, modeling and testing of a slow-burning solid rocket propulsion system
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017.
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| Other Authors: | |
| Format: | Thesis |
| Language: | eng |
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Massachusetts Institute of Technology
2017
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| Online Access: | http://hdl.handle.net/1721.1/112515 |
| _version_ | 1811092413184212992 |
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| author | Vernacchia, Matthew T |
| author2 | R. John Hansman, Jr. |
| author_facet | R. John Hansman, Jr. Vernacchia, Matthew T |
| author_sort | Vernacchia, Matthew T |
| collection | MIT |
| description | Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017. |
| first_indexed | 2024-09-23T15:17:46Z |
| format | Thesis |
| id | mit-1721.1/112515 |
| institution | Massachusetts Institute of Technology |
| language | eng |
| last_indexed | 2024-09-23T15:17:46Z |
| publishDate | 2017 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/1125152019-04-10T15:56:00Z Development, modeling and testing of a slow-burning solid rocket propulsion system Vernacchia, Matthew T R. John Hansman, Jr. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics. Aeronautics and Astronautics. Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017. Cataloged from PDF version of thesis. Includes bibliographical references (pages 163-168). Small, unmanned aerial vehicles (UAVs) are expanding the capabilities of aircraft systems. However, a gap exists in the size and capability of aircraft: no aircraft smaller than 10 kilograms are capable of flight faster than 100 meters per second. A small, fast aircraft requires a propulsion system which is both miniature and high-power, requirements which current UAV propulsion technologies do not meet. To meet this need, a slow-burning solid rocket motor has been developed. Such motors require slow-burning solid propellants with tailorable burn rate. This thesis reports experimental results and combustion theory for a slow-burning solid propellant. It also describes a rocket motor designed to use this propellant, and the manufacturing process used to produce it. This propellant burns slowly enough for the low-thrust, long-endurance needs of UAV propulsion. Its burn rate can be predictably tailored by addition of the burn rate suppressant oxamide. Further, this thesis presents a concept for a small, fast aircraft designed around this novel propulsion technology. The motor integrates elegantly into the aircraft's structure, and compact thermal protection system insulates other vehicle systems from the heat of combustion. These results demonstrate the feasibility slow-burning rocket propulsion systems, and their application to small aircraft. It should be possible for small, rocket-propelled UAVs to sustain powered, transonic flight for several minutes. With this technology, kilogram-scale UAVs could be able to quickly deploy over tens of kilometers, and fly joint missions alongside manned fighter jets. by Matthew T. Vernacchia. S.M. 2017-12-05T19:16:18Z 2017-12-05T19:16:18Z 2017 2017 Thesis http://hdl.handle.net/1721.1/112515 1012609937 eng MIT theses are protected by copyright. They may be viewed, downloaded, or printed from this source but further reproduction or distribution in any format is prohibited without written permission. http://dspace.mit.edu/handle/1721.1/7582 176, [2] unnumbered pages application/pdf Massachusetts Institute of Technology |
| spellingShingle | Aeronautics and Astronautics. Vernacchia, Matthew T Development, modeling and testing of a slow-burning solid rocket propulsion system |
| title | Development, modeling and testing of a slow-burning solid rocket propulsion system |
| title_full | Development, modeling and testing of a slow-burning solid rocket propulsion system |
| title_fullStr | Development, modeling and testing of a slow-burning solid rocket propulsion system |
| title_full_unstemmed | Development, modeling and testing of a slow-burning solid rocket propulsion system |
| title_short | Development, modeling and testing of a slow-burning solid rocket propulsion system |
| title_sort | development modeling and testing of a slow burning solid rocket propulsion system |
| topic | Aeronautics and Astronautics. |
| url | http://hdl.handle.net/1721.1/112515 |
| work_keys_str_mv | AT vernacchiamatthewt developmentmodelingandtestingofaslowburningsolidrocketpropulsionsystem |