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Development and Test of a Superconducting Helicon Plasma Thruster
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| 자료유형 | 학위논문 |
|---|---|
| 서명/저자사항 | Development and Test of a Superconducting Helicon Plasma Thruster. |
| 개인저자 | Vitucci, John Joseph. |
| 단체저자명 | University of Maryland, College Park. Aerospace Engineering. |
| 발행사항 | [S.l.]: University of Maryland, College Park., 2019. |
| 발행사항 | Ann Arbor: ProQuest Dissertations & Theses, 2019. |
| 형태사항 | 209 p. |
| 기본자료 저록 | Dissertations Abstracts International 81-04B. Dissertation Abstract International |
| ISBN | 9781687914149 |
| 학위논문주기 | Thesis (Ph.D.)--University of Maryland, College Park, 2019. |
| 일반주기 |
Source: Dissertations Abstracts International, Volume: 81-04, Section: B.
Advisor: Sedwick, Raymond J. |
| 이용제한사항 | This item must not be sold to any third party vendors. |
| 요약 | Helicon thrusters have emerged as a viable technology for station-keeping and deep-space exploration applications due to their high-efficiency plasma generation and amenability to propellants such as water vapor. A proposed design and performance analysis for the superconducting helicon thruster is presented. First, a zero-dimensional power flow analysis is performed, demonstrating an increase in the power efficiency for the superconducting helicon thruster versus the baseline helicon plasma thruster. This superconducting helicon thruster is composed of two subsystems: the superconducting magnet subsystem and the thermal management subsystem. The superconducting magnet subsystem shows that by using the combination of a solenoid and permanent magnet, a desirable magnetic field geometry for a helicon plasma can be supported. By adding a high-temperature (type-II) superconductor, the induced current in the superconductor that results from quenching the solenoid can sustain the same magnetic field geometry without the need to continuously power the electromagnet. The thermal management subsystem then maintains cryogenic temperatures in a closed-loop design for continuous operation of the thruster.A triple Langmuir probe was used to experimentally characterize the bulk plasma, and the downstream ion energies were measured with a retarding potential analyzer (RPA). Using the measured electron temperature and ion energies, it was shown that the baseline helicon thruster demonstrates slightly better performance metrics, however this comes at the cost of lower propulsive efficiencies. In instances where maximum thrust and maximum specific impulses are desired, the baseline helicon thruster would be more advantageous. If RF input power mitigation is of larger concern, the superconducting helicon thruster outperforms the baseline helicon thruster. Additionally, substantially larger ion beam energies were measured using the RPA compared to other independent studies. This anomalous acceleration mechanism has the potential to provide vast improvement to the performance of the helicon thruster. |
| 일반주제명 | Aerospace engineering. |
| 언어 | 영어 |
| 바로가기 | 
: 이 자료의 원문은 한국교육학술정보원에서 제공합니다. |
