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New techniques in astrodynamics for ...

Campagnola, Stefano.

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New techniques in astrodynamics for moon systems exploration.

紀錄類型:	書目-語言資料,印刷品 : Monograph/item
正題名/作者:	New techniques in astrodynamics for moon systems exploration./
作者:	Campagnola, Stefano.
面頁冊數:	159 p.
附註:	Source: Dissertation Abstracts International, Volume: 71-06, Section: B, page: 3783.
Contained By:	Dissertation Abstracts International71-06B.
標題:	Applied Mathematics. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3403534
ISBN:	9781109771299

New techniques in astrodynamics for moon systems exploration.
Campagnola, Stefano.

New techniques in astrodynamics for moon systems exploration. - 159 p.

Source: Dissertation Abstracts International, Volume: 71-06, Section: B, page: 3783.

Thesis (Ph.D.)--University of Southern California, 2010.

ESA and NASA scientific missions to the Jupiter and Saturn systems will answer fundamental questions on the habitability of icy worlds. The missions include unprecedented challenges, as the spacecraft will be placed in closed, stable orbits near the surface of the moons. This thesis presents methods to design trajectories that tour the moons and ultimately insert the spacecraft into orbits around them, while mitigating the mission costs and/or risks.

ISBN: 9781109771299Subjects--Topical Terms:

1669109
Applied Mathematics.

New techniques in astrodynamics for moon systems exploration.
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245 1 0 $a New techniques in astrodynamics for moon systems exploration.
300 $a 159 p.
500 $a Source: Dissertation Abstracts International, Volume: 71-06, Section: B, page: 3783.
500 $a Adviser: Paul Newton.
502 $a Thesis (Ph.D.)--University of Southern California, 2010.
520 $a ESA and NASA scientific missions to the Jupiter and Saturn systems will answer fundamental questions on the habitability of icy worlds. The missions include unprecedented challenges, as the spacecraft will be placed in closed, stable orbits near the surface of the moons. This thesis presents methods to design trajectories that tour the moons and ultimately insert the spacecraft into orbits around them, while mitigating the mission costs and/or risks.
520 $a A first technique is the endgame, a sequence of moon flyby preceding the orbit insertion. Historically, the endgame is designed with two approaches with different results: the vinfinity-leveraging transfer (VILT) approach leads to high-Deltav (hundreds of m/s), short time-of-flight (months) endgames, while the multi-body approach leads to low-Deltav (tens of m/s), long time-of-flight (years) endgames. This work analyzes and develops both approaches.
520 $a We introduce a fast design method to automatically compute VILT endgames, which were previously designed in an ad-hoc manner. We also derive an important simple quadrature formula for the minimum Deltav attainable with this approach. This formula is the first important result of this work, as it provides a lower bound for assessment studies.
520 $a We explain and develop the complex multi-body approach introducing the Tisserand-Poincare (T-P) graph, which is the second important result of this work. It provides a link between the two approaches, and shows the intersections between low-energy trajectories around different moons. With the T-P graph we design a five-month transfer between low-altitude orbits at Europa and Ganymede, using almost half the Deltav of the Hohmann transfer.
520 $a We then focus on missions to low-mass moons, like Enceladus. We show that nontangent VILT (an extension of the traditional VILT) significantly reduce the Deltav while maintaining a satisfactory transfer time (< 4 years in the Saturn system). With a new design method we compute a 52 gravity-assist trajectory from Titan to Enceladus. The time of flight is 2.7 years, and the Deltav is almost 10 times better then the Titan-Enceladus Hohmann-like transfer. This trajectory and the design method are the third important contribution of this work; they enable a new class of missions which were previously considered unfeasible.
520 $a Finally we study the capture problem, which seeks chaotic trajectories with multiple orbit insertion opportunities. We explore the solution space extending the design techniques used by ESA for the BepiColombo mission capture to Mercury. Such problems are better modeled in the spatial, elliptic, restricted three-body problem, which we analyze in detail. We define new regions of motions and to compute new families of periodic orbits and their stability properties. This analysis is the fourth important contribution of this work. Finally we show that capture trajectories shadow the manifolds of special periodic and quasi periodic orbits. This is the last important contribution of this report, as if both explains the complex dynamics of capture trajectories, and suggests new ways to design them.
590 $a School code: 0208.
650 4 $a Applied Mathematics. $3 1669109
650 4 $a Engineering, Aerospace. $3 1018395
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690 $a 0538
710 2 $a University of Southern California. $b Aerospace Engineering. $3 1030508
773 0 $t Dissertation Abstracts International $g 71-06B.
790 1 0 $a Newton, Paul, $e advisor
790 1 0 $a Kanso, Eva $e committee member
790 1 0 $a Flashner, Henryk $e committee member
790 1 0 $a Ghanem, Roger $e committee member
790 1 0 $a Baxendale, Peter $e committee member
790 $a 0208
791 $a Ph.D.
792 $a 2010
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3403534