Guidance and Optimization of Planetary Entry and Powered Descent- [electronic resource]
Guidance and Optimization of Planetary Entry and Powered Descent- [electronic resource]
- 자료유형
- 학위논문파일 국외
- 최종처리일시
- 20240214100116
- ISBN
- 9798379918873
- DDC
- 629.1
- 서명/저자
- Guidance and Optimization of Planetary Entry and Powered Descent - [electronic resource]
- 발행사항
- [S.l.]: : University of California, San Diego., 2023
- 발행사항
- Ann Arbor : : ProQuest Dissertations & Theses,, 2023
- 형태사항
- 1 online resource(290 p.)
- 주기사항
- Source: Dissertations Abstracts International, Volume: 85-01, Section: B.
- 주기사항
- Advisor: Lu, Ping;Hwang, John T.
- 학위논문주기
- Thesis (Ph.D.)--University of California, San Diego, 2023.
- 사용제한주기
- This item must not be sold to any third party vendors.
- 초록/해제
- 요약Safety, precision, and efficiency are the key ingredients for successful future human-scale entry, descent, and landing (EDL) missions to the Moon and Mars. In this work, a complete investigation into each component of an EDL mission, including an emergency scenario, revealed some of the necessary techniques that need to be implemented to effectively reach these goals. An often-ignored aspect of EDL is the requirement to have a safety protocol in place in case of an emergency. In this work, a newly developed abort guidance technique revealed that an ascent-abort into orbit can be achieved from any point during the lunar powered descent phase. The two-phase abort methodology is inspired in the optimal ascent guidance problem and can be activated autonomously to guide the vehicle towards a safe orbit with the least amount of propellant possible. Validation of two state-of-the-art algorithms for entry and optimal powered descent guidance in different mission scenarios and in a high-fidelity simulation environment, demonstrated that a complete non-optimized EDL trajectory can be generated quickly and reliably. With the addition of an adaptive powered descent initiation logic, based on the indirect method of optimal control, the total propellant consumption during powered descent can be greatly reduced even when the powered descent guidance is not optimal. The complexity of the end-to-end EDL problem limits the extent to which the problem can be optimized by the known optimal control techniques. Optimization using the direct method of optimal control can generate a theoretical solution, albeit in an impractical amount of time. Leveraging the robustness of a state-of-the-art entry guidance and an optimal powered descent guidance algorithm, a novel ap- proach to the optimization of the end-to-end EDL problem emerged. The problem is solved with a bi-level optimization approach in which an inner loop optimizes the propellant consumption during powered descent, and an outer loop modifies the entry trajectory to provide the best PDI condition. This innovative approach results in a fast and reliable trajectory with near-optimal propellant consumption in a matter of seconds. All the results from this investigation are tested for robustness in Monte Carlo simulations.
- 일반주제명
- Aerospace engineering.
- 일반주제명
- Planetology.
- 일반주제명
- Mechanical engineering.
- 키워드
- Planetary entry
- 키워드
- Lunar landing
- 키워드
- Mars landing
- 키워드
- Powered descent
- 키워드
- EDL mission
- 기타저자
- University of California, San Diego Mechanical and Aerospace Engineering (Joint Doctoral with SDSU)
- 기본자료저록
- Dissertations Abstracts International. 85-01B.
- 기본자료저록
- Dissertation Abstract International
- 전자적 위치 및 접속
- 로그인 후 원문을 볼 수 있습니다.