ΔV-optimal rendezvous maneuvers in CIS-lunar Halo orbits around EML2

Davide Conte; David B. Spencer

ΔV-optimal rendezvous maneuvers in CIS-lunar Halo orbits around EML2

Davide Conte, David B. Spencer

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Abstract

This paper presents solution techniques for finding Δv-optimal maneuvers to rendezvous with a target spacecraft in cis-lunar halo orbits around the Earth-Moon Lagrange point 2 (EML2). This family of orbits was chosen due to the rising interest in cis-lunar space for human and robotic exploration. The dynamics and the stability of relative motion in the Circular Restricted Three-Body Problem (CR3BP) are analyzed using Floquet theory. In order to determine optimal maneuvers that the chaser spacecraft needs to accomplish to rendezvous with the target vehicle, simplified models of the relative motion in the CR3BP are explored and utilized, and compared to the full non-linear CR3BP model.

Original language	English (US)
Title of host publication	ASTRODYNAMICS 2017
Editors	John H. Seago, Nathan J. Strange, Daniel J. Scheeres, Jeffrey S. Parker
Publisher	Univelt Inc.
Pages	3151-3166
Number of pages	16
ISBN (Print)	9780877036456
State	Published - 2018
Event	AAS/AIAA Astrodynamics Specialist Conference, 2017 - Stevenson, United States Duration: Aug 20 2017 → Aug 24 2017

Publication series

Name	Advances in the Astronautical Sciences
Volume	162
ISSN (Print)	0065-3438

Other

Other	AAS/AIAA Astrodynamics Specialist Conference, 2017
Country/Territory	United States
City	Stevenson
Period	8/20/17 → 8/24/17

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Space and Planetary Science

Cite this

@inproceedings{6113d251072c4b43abc43d7346e75e28,

title = "ΔV-optimal rendezvous maneuvers in CIS-lunar Halo orbits around EML2",

abstract = "This paper presents solution techniques for finding Δv-optimal maneuvers to rendezvous with a target spacecraft in cis-lunar halo orbits around the Earth-Moon Lagrange point 2 (EML2). This family of orbits was chosen due to the rising interest in cis-lunar space for human and robotic exploration. The dynamics and the stability of relative motion in the Circular Restricted Three-Body Problem (CR3BP) are analyzed using Floquet theory. In order to determine optimal maneuvers that the chaser spacecraft needs to accomplish to rendezvous with the target vehicle, simplified models of the relative motion in the CR3BP are explored and utilized, and compared to the full non-linear CR3BP model.",

author = "Davide Conte and Spencer, {David B.}",

year = "2018",

language = "English (US)",

isbn = "9780877036456",

series = "Advances in the Astronautical Sciences",

publisher = "Univelt Inc.",

pages = "3151--3166",

editor = "Seago, {John H.} and Strange, {Nathan J.} and Scheeres, {Daniel J.} and Parker, {Jeffrey S.}",

booktitle = "ASTRODYNAMICS 2017",

address = "United States",

}

ΔV-optimal rendezvous maneuvers in CIS-lunar Halo orbits around EML2. / Conte, Davide; Spencer, David B.
ASTRODYNAMICS 2017. ed. / John H. Seago; Nathan J. Strange; Daniel J. Scheeres; Jeffrey S. Parker. Univelt Inc., 2018. p. 3151-3166 (Advances in the Astronautical Sciences; Vol. 162).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

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N2 - This paper presents solution techniques for finding Δv-optimal maneuvers to rendezvous with a target spacecraft in cis-lunar halo orbits around the Earth-Moon Lagrange point 2 (EML2). This family of orbits was chosen due to the rising interest in cis-lunar space for human and robotic exploration. The dynamics and the stability of relative motion in the Circular Restricted Three-Body Problem (CR3BP) are analyzed using Floquet theory. In order to determine optimal maneuvers that the chaser spacecraft needs to accomplish to rendezvous with the target vehicle, simplified models of the relative motion in the CR3BP are explored and utilized, and compared to the full non-linear CR3BP model.

AB - This paper presents solution techniques for finding Δv-optimal maneuvers to rendezvous with a target spacecraft in cis-lunar halo orbits around the Earth-Moon Lagrange point 2 (EML2). This family of orbits was chosen due to the rising interest in cis-lunar space for human and robotic exploration. The dynamics and the stability of relative motion in the Circular Restricted Three-Body Problem (CR3BP) are analyzed using Floquet theory. In order to determine optimal maneuvers that the chaser spacecraft needs to accomplish to rendezvous with the target vehicle, simplified models of the relative motion in the CR3BP are explored and utilized, and compared to the full non-linear CR3BP model.

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BT - ASTRODYNAMICS 2017

A2 - Seago, John H.

A2 - Strange, Nathan J.

A2 - Scheeres, Daniel J.

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PB - Univelt Inc.

T2 - AAS/AIAA Astrodynamics Specialist Conference, 2017

Y2 - 20 August 2017 through 24 August 2017

ER -

ΔV-optimal rendezvous maneuvers in CIS-lunar Halo orbits around EML2

Abstract

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Other

All Science Journal Classification (ASJC) codes

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