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Dynamic Modeling for Simulation and Experimentation Tools Used in the Analysis of Space Vehicle Trajectories- [electronic resource]
Dynamic Modeling for Simulation and Experimentation Tools Used in the Analysis of Space Vehicle Trajectories- [electronic resource]
상세정보
- 자료유형
- 학위논문파일 국외
- 최종처리일시
- 20240214101918
- ISBN
- 9798380599375
- DDC
- 629.1
- 서명/저자
- Dynamic Modeling for Simulation and Experimentation Tools Used in the Analysis of Space Vehicle Trajectories - [electronic resource]
- 발행사항
- [S.l.]: : University of Minnesota., 2023
- 발행사항
- Ann Arbor : : ProQuest Dissertations & Theses,, 2023
- 형태사항
- 1 online resource(149 p.)
- 주기사항
- Source: Dissertations Abstracts International, Volume: 85-04, Section: B.
- 주기사항
- Advisor: Caverly, Ryan James.
- 학위논문주기
- Thesis (Ph.D.)--University of Minnesota, 2023.
- 사용제한주기
- This item must not be sold to any third party vendors.
- 초록/해제
- 요약Current and future missions to send humans to the Moon and beyond will have increasingly strict requirements on the performance and robustness of the mission vehicles. These requirements will push all aspects of the vehicles to advance to ensure mission safety and success. This includes the guidance, navigation, and control (GNC) systems operating on board.Novel GNC systems must be matured in an environment analogous to those they operate in, but these operating conditions are difficult to replicate. The first part of this dissertation presents the Cost- and Risk-Reducing Quadcopter System (CRQS, pronounced "circus"), a platform proposed to provide a low-cost, low-risk setting to mature novel GNC systems. The system is modeled, then implemented in numerical simulations to analyze a control system's ability to track a generated trajectory. The work done to fabricate a physical flying inverted pendulum, a necessary step to reach the complete CRQS, is then presented.As spacecraft grow to accommodate larger payloads and more distant destinations, the amount of liquid propellant on board grows. The interactions between a spacecraft and the liquid propellant can have detrimental effects on the performance of the spacecraft's GNC systems. The second part of this dissertation develops a low-order approximate dynamic model of a spacecraft and its liquid onboard propellant in a low-g environment. The model is then implemented in numerical simulations to analyze the trajectory of the Apollo-era service module (SM) for the probability of recontact after jettison from the command module (CM).
- 일반주제명
- Aerospace engineering.
- 일반주제명
- Astronomy.
- 일반주제명
- Aeronomy.
- 키워드
- Dynamic modeling
- 키워드
- Spacecraft
- 키워드
- Moon
- 키워드
- GNC systems
- 기타저자
- University of Minnesota Aerospace Engineering and Mechanics
- 기본자료저록
- Dissertations Abstracts International. 85-04B.
- 기본자료저록
- Dissertation Abstract International
- 전자적 위치 및 접속
- 로그인 후 원문을 볼 수 있습니다.
MARC
008240612s2023 us |||||||||||||||c||eng d■001000016935319
■00520240214101918
■006m o d
■007cr#unu||||||||
■020 ▼a9798380599375
■035 ▼a(MiAaPQ)AAI30688911
■040 ▼aMiAaPQ▼cMiAaPQ
■0820 ▼a629.1
■1001 ▼aElke, William James, III.
■24510▼aDynamic Modeling for Simulation and Experimentation Tools Used in the Analysis of Space Vehicle Trajectories▼h[electronic resource]
■260 ▼a[S.l.]:▼bUniversity of Minnesota. ▼c2023
■260 1▼aAnn Arbor :▼bProQuest Dissertations & Theses, ▼c2023
■300 ▼a1 online resource(149 p.)
■500 ▼aSource: Dissertations Abstracts International, Volume: 85-04, Section: B.
■500 ▼aAdvisor: Caverly, Ryan James.
■5021 ▼aThesis (Ph.D.)--University of Minnesota, 2023.
■506 ▼aThis item must not be sold to any third party vendors.
■520 ▼aCurrent and future missions to send humans to the Moon and beyond will have increasingly strict requirements on the performance and robustness of the mission vehicles. These requirements will push all aspects of the vehicles to advance to ensure mission safety and success. This includes the guidance, navigation, and control (GNC) systems operating on board.Novel GNC systems must be matured in an environment analogous to those they operate in, but these operating conditions are difficult to replicate. The first part of this dissertation presents the Cost- and Risk-Reducing Quadcopter System (CRQS, pronounced "circus"), a platform proposed to provide a low-cost, low-risk setting to mature novel GNC systems. The system is modeled, then implemented in numerical simulations to analyze a control system's ability to track a generated trajectory. The work done to fabricate a physical flying inverted pendulum, a necessary step to reach the complete CRQS, is then presented.As spacecraft grow to accommodate larger payloads and more distant destinations, the amount of liquid propellant on board grows. The interactions between a spacecraft and the liquid propellant can have detrimental effects on the performance of the spacecraft's GNC systems. The second part of this dissertation develops a low-order approximate dynamic model of a spacecraft and its liquid onboard propellant in a low-g environment. The model is then implemented in numerical simulations to analyze the trajectory of the Apollo-era service module (SM) for the probability of recontact after jettison from the command module (CM).
■590 ▼aSchool code: 0130.
■650 4▼aAerospace engineering.
■650 4▼aAstronomy.
■650 4▼aAeronomy.
■653 ▼aDynamic modeling
■653 ▼aSpacecraft
■653 ▼aMoon
■653 ▼aSpace vehicle trajectories
■653 ▼aGNC systems
■690 ▼a0538
■690 ▼a0367
■690 ▼a0606
■71020▼aUniversity of Minnesota▼bAerospace Engineering and Mechanics.
■7730 ▼tDissertations Abstracts International▼g85-04B.
■773 ▼tDissertation Abstract International
■790 ▼a0130
■791 ▼aPh.D.
■792 ▼a2023
■793 ▼aEnglish
■85640▼uhttp://www.riss.kr/pdu/ddodLink.do?id=T16935319▼nKERIS▼z이 자료의 원문은 한국교육학술정보원에서 제공합니다.
■980 ▼a202402▼f2024
