國立虎尾科技大學 |

Guidance and Optimization of Planetary Entry and Powered Descent.

紀錄類型:	書目-語言資料,手稿 : Monograph/item
正題名/作者:	Guidance and Optimization of Planetary Entry and Powered Descent./
作者:	Sandoval, Sergio Alfonso.
面頁冊數:	1 online resource (290 pages)
附註:	Source: Dissertations Abstracts International, Volume: 85-01, Section: B.
Contained By:	Dissertations Abstracts International85-01B.
標題:	Mechanical engineering. -
電子資源:	click for full text (PQDT)
ISBN:	9798379918873

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

Guidance and Optimization of Planetary Entry and Powered Descent. - 1 online resource (290 pages)

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

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

Includes bibliographical references

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.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798379918873Subjects--Topical Terms:

557493
Mechanical engineering.
Subjects--Index Terms:

Planetary entryIndex Terms--Genre/Form:

554714
Electronic books.

Guidance and Optimization of Planetary Entry and Powered Descent.
LDR:03664ntm a22003977 4500 001 1143768
005 20240517104947.5
006 m o d
007 cr mn ---uuuuu
008 250605s2023 xx obm 000 0 eng d
020 $a 9798379918873
035 $a (MiAaPQ)AAI30422753
035 $a AAI30422753
040 $a MiAaPQ $b eng $c MiAaPQ $d NTU
100 1 $a Sandoval, Sergio Alfonso. $3 1468556
245 1 0 $a Guidance and Optimization of Planetary Entry and Powered Descent.
264 0 $c 2023
300 $a 1 online resource (290 pages)
336 $a text $b txt $2 rdacontent
337 $a computer $b c $2 rdamedia
338 $a online resource $b cr $2 rdacarrier
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.
504 $a Includes bibliographical references
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.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2024
538 $a Mode of access: World Wide Web
650 4 $a Mechanical engineering. $3 557493
650 4 $a Planetology. $3 593937
650 4 $a Aerospace engineering. $3 686400
653 $a Planetary entry
653 $a Lunar landing
653 $a Mars landing
653 $a Powered descent
653 $a EDL mission
655 7 $a Electronic books. $2 local $3 554714
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 1468557
710 2 $a ProQuest Information and Learning Co. $3 1178819
773 0 $t Dissertations Abstracts International $g 85-01B.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30422753 $z click for full text (PQDT)