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Guidance and Optimization of Planeta...

Sandoval, Sergio Alfonso.

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Guidance and Optimization of Planetary Entry and Powered Descent.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Guidance and Optimization of Planetary Entry and Powered Descent./
作者:	Sandoval, Sergio Alfonso.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2023,
面頁冊數:	290 p.
附註:	Source: Dissertations Abstracts International, Volume: 85-01, Section: B.
Contained By:	Dissertations Abstracts International85-01B.
標題:	Aerospace engineering. -
電子資源:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30422753
ISBN:	9798379918873

Guidance and Optimization of Planetary Entry and Powered Descent.
Sandoval, Sergio Alfonso.

Guidance and Optimization of Planetary Entry and Powered Descent. - Ann Arbor : ProQuest Dissertations & Theses, 2023 - 290 p.

Source: Dissertations Abstracts International, Volume: 85-01, Section: B.

Thesis (Ph.D.)--University of California, San Diego, 2023.

This item must not be sold to any third party vendors.

Safety, 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.

ISBN: 9798379918873Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Planetary entry

Guidance and Optimization of Planetary Entry and Powered Descent.
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245 1 0 $a Guidance and Optimization of Planetary Entry and Powered Descent.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2023
300 $a 290 p.
500 $a Source: Dissertations Abstracts International, Volume: 85-01, Section: B.
500 $a Advisor: Lu, Ping;Hwang, John T.
502 $a Thesis (Ph.D.)--University of California, San Diego, 2023.
506 $a This item must not be sold to any third party vendors.
520 $a Safety, 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.
590 $a School code: 0033.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Planetology. $3 546174
650 4 $a Mechanical engineering. $3 649730
653 $a Planetary entry
653 $a Lunar landing
653 $a Mars landing
653 $a Powered descent
653 $a EDL mission
690 $a 0538
690 $a 0548
690 $a 0590
710 2 $a University of California, San Diego. $b Mechanical and Aerospace Engineering (Joint Doctoral with SDSU). $3 3694457
773 0 $t Dissertations Abstracts International $g 85-01B.
790 $a 0033
791 $a Ph.D.
792 $a 2023
793 $a English
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30422753