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Erosion of Spacecraft Surfaces Due to Electric Propulsion Thruster Plumes
Erosion of Spacecraft Surfaces Due to Electric Propulsion Thruster Plumes
상세정보
- 자료유형
- 학위논문 서양
- 최종처리일시
- 20250211153011
- ISBN
- 9798384044758
- DDC
- 530
- 서명/저자
- Erosion of Spacecraft Surfaces Due to Electric Propulsion Thruster Plumes
- 발행사항
- [Sl] : University of Michigan, 2024
- 발행사항
- Ann Arbor : ProQuest Dissertations & Theses, 2024
- 형태사항
- 205 p
- 주기사항
- Source: Dissertations Abstracts International, Volume: 86-03, Section: B.
- 주기사항
- Advisor: Jorns, Benjamin A.
- 학위논문주기
- Thesis (Ph.D.)--University of Michigan, 2024.
- 초록/해제
- 요약Hall thrusters have become the most popular and successful forms of in-space propulsion ever flown. This is in large part due to their high specific impulse, which enables an increasingly wider mission space. A new push to higher-power and longer-duration missions will expose a unique risk to the spacecraft stemming from the higher exhaust velocities of electric propulsion (EP) thruster plumes. The high-energy ions from the exhaust plume can bombard surfaces of the spacecraft causing erosion. This has a potential to cause problems for the future of EP, as even surfaces exposed to low ion flux can be damaged over the long periods of time expected on an EP powered mission. There is then a pressing and growing need in the EP community to predict the extent of the erosion and, if necessary, devise methods or techniques to potentially mitigate its impact. To meet these growing needs of the community, we performed three studies to address these concerns.In the first study, an investigation into the erosion of a reflector mesh material in the plume of a Hall-effect thruster was presented. Representative samples of the meshed reflector material were exposed to different regions of the thruster plume, and erosion due to ion bombardment is characterized. These results were compared to predictions of an erosion model for non-planar composite materials calibrated to the local plasma parameters and further underscored the need for ways to reduce uncertainty in erosion predictions, or barring that, ways to mitigate it entirely.In the second study, two ion-impact erosion mitigation techniques were demonstrated and validated for sample coupons of spacecraft reflector mesh exposed to the plume of a Hall-effect thruster. In addition, a parametric pressure study was performed to demonstrate the extensibility of the most promising mitigation method to orbital pressure conditions. Profilometry measurements of the post-exposure wire geometries show that both methods significantly decrease the erosion of test coupons of the spacecraft reflector mesh when compared to unexposed control samples. Predictions of wire erosion using plume parameters extrapolated to orbital conditions show a large reduction in erosion for a sample exposed for 10,000 hours. Although these results show great promise for the future use of these techniques, the predictions still rely on valid extrapolations of orbital performance from ground-based data.In the third and final study, changes in the acceleration region dynamics and cathode coupling of a magnetically shielded Hall thruster were characterized under different pressure, electrical, and cathode configurations. A large downstream beam dump was isolated and electrically biased with respect to the ground, while simultaneously the pressure in the facility was varied. The results show that a stable far-field potential can minimally enhance the previously known pressure-related facility effects, and it reinforces that background pressure is a strong driver of how a Hall thruster operates and electrically couples to the facility.Taken together, these studies and the insights gained from them provide a measurable contribution to the current state of knowledge. Further, these results directly address a pressing need in the electric propulsion community, decreasing the risk, and enabling newer and more ambitious missions.
- 일반주제명
- Physics
- 일반주제명
- Aerospace engineering
- 일반주제명
- Electrical engineering
- 키워드
- Hall thrusters
- 기타저자
- University of Michigan Applied Physics
- 기본자료저록
- Dissertations Abstracts International. 86-03B.
- 전자적 위치 및 접속
- 로그인 후 원문을 볼 수 있습니다.
MARC
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■00520250211153011
■006m o d
■007cr#unu||||||||
■020 ▼a9798384044758
■035 ▼a(MiAaPQ)AAI31631448
■035 ▼a(MiAaPQ)umichrackham005767
■040 ▼aMiAaPQ▼cMiAaPQ
■0820 ▼a530
■1001 ▼aByrne, Matthew P.
■24510▼aErosion of Spacecraft Surfaces Due to Electric Propulsion Thruster Plumes
■260 ▼a[Sl]▼bUniversity of Michigan▼c2024
■260 1▼aAnn Arbor▼bProQuest Dissertations & Theses▼c2024
■300 ▼a205 p
■500 ▼aSource: Dissertations Abstracts International, Volume: 86-03, Section: B.
■500 ▼aAdvisor: Jorns, Benjamin A.
■5021 ▼aThesis (Ph.D.)--University of Michigan, 2024.
■520 ▼aHall thrusters have become the most popular and successful forms of in-space propulsion ever flown. This is in large part due to their high specific impulse, which enables an increasingly wider mission space. A new push to higher-power and longer-duration missions will expose a unique risk to the spacecraft stemming from the higher exhaust velocities of electric propulsion (EP) thruster plumes. The high-energy ions from the exhaust plume can bombard surfaces of the spacecraft causing erosion. This has a potential to cause problems for the future of EP, as even surfaces exposed to low ion flux can be damaged over the long periods of time expected on an EP powered mission. There is then a pressing and growing need in the EP community to predict the extent of the erosion and, if necessary, devise methods or techniques to potentially mitigate its impact. To meet these growing needs of the community, we performed three studies to address these concerns.In the first study, an investigation into the erosion of a reflector mesh material in the plume of a Hall-effect thruster was presented. Representative samples of the meshed reflector material were exposed to different regions of the thruster plume, and erosion due to ion bombardment is characterized. These results were compared to predictions of an erosion model for non-planar composite materials calibrated to the local plasma parameters and further underscored the need for ways to reduce uncertainty in erosion predictions, or barring that, ways to mitigate it entirely.In the second study, two ion-impact erosion mitigation techniques were demonstrated and validated for sample coupons of spacecraft reflector mesh exposed to the plume of a Hall-effect thruster. In addition, a parametric pressure study was performed to demonstrate the extensibility of the most promising mitigation method to orbital pressure conditions. Profilometry measurements of the post-exposure wire geometries show that both methods significantly decrease the erosion of test coupons of the spacecraft reflector mesh when compared to unexposed control samples. Predictions of wire erosion using plume parameters extrapolated to orbital conditions show a large reduction in erosion for a sample exposed for 10,000 hours. Although these results show great promise for the future use of these techniques, the predictions still rely on valid extrapolations of orbital performance from ground-based data.In the third and final study, changes in the acceleration region dynamics and cathode coupling of a magnetically shielded Hall thruster were characterized under different pressure, electrical, and cathode configurations. A large downstream beam dump was isolated and electrically biased with respect to the ground, while simultaneously the pressure in the facility was varied. The results show that a stable far-field potential can minimally enhance the previously known pressure-related facility effects, and it reinforces that background pressure is a strong driver of how a Hall thruster operates and electrically couples to the facility.Taken together, these studies and the insights gained from them provide a measurable contribution to the current state of knowledge. Further, these results directly address a pressing need in the electric propulsion community, decreasing the risk, and enabling newer and more ambitious missions.
■590 ▼aSchool code: 0127.
■650 4▼aPhysics
■650 4▼aAerospace engineering
■650 4▼aElectrical engineering
■653 ▼aHall thrusters
■653 ▼aElectric propulsion
■653 ▼aSpacecraft interactions
■653 ▼aOrbital pressure conditions
■653 ▼aErosion predictions
■690 ▼a0538
■690 ▼a0605
■690 ▼a0544
■71020▼aUniversity of Michigan▼bApplied Physics.
■7730 ▼tDissertations Abstracts International▼g86-03B.
■790 ▼a0127
■791 ▼aPh.D.
■792 ▼a2024
■793 ▼aEnglish
■85640▼uhttp://www.riss.kr/pdu/ddodLink.do?id=T17164505▼nKERIS▼z이 자료의 원문은 한국교육학술정보원에서 제공합니다.
