On the stability of displaced two-body lunar orbits

Jules Simo; Colin R. McInnes

On the stability of displaced two-body lunar orbits

Jules Simo, Colin R. McInnes

Mechanical And Aerospace Engineering

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Abstract

In a prior study, a methodology was developed for computing approximate large displaced orbits in the Earth-Moon circular restricted three-body problem (CRTBP)by the Moon-Sail two-body problem. It was found that far from the L1 and L2 points, the approximate two-body analysis for large accelerations matches well with the dynamics of displaced orbits in relation to the three-body problem. In the present study, the linear stability characteristics of the families of approximate periodic orbits are investigated.

Original language	English
Pages	1-10
Number of pages	10
Publication status	Published - Feb 2010
Event	20th AIAA Space Flight Mechanics Meeting - San Diego, California Duration: 14 Feb 2010 → 17 Feb 2010

Conference

Conference	20th AIAA Space Flight Mechanics Meeting
City	San Diego, California
Period	14/02/10 → 17/02/10

Keywords

orbits
space craft
space flight

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strathprints016461Accepted author manuscript, 133 KB

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title = "On the stability of displaced two-body lunar orbits",

abstract = "In a prior study, a methodology was developed for computing approximate large displaced orbits in the Earth-Moon circular restricted three-body problem (CRTBP)by the Moon-Sail two-body problem. It was found that far from the L1 and L2 points, the approximate two-body analysis for large accelerations matches well with the dynamics of displaced orbits in relation to the three-body problem. In the present study, the linear stability characteristics of the families of approximate periodic orbits are investigated.",

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AU - Simo, Jules

AU - McInnes, Colin R.

PY - 2010/2

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N2 - In a prior study, a methodology was developed for computing approximate large displaced orbits in the Earth-Moon circular restricted three-body problem (CRTBP)by the Moon-Sail two-body problem. It was found that far from the L1 and L2 points, the approximate two-body analysis for large accelerations matches well with the dynamics of displaced orbits in relation to the three-body problem. In the present study, the linear stability characteristics of the families of approximate periodic orbits are investigated.

AB - In a prior study, a methodology was developed for computing approximate large displaced orbits in the Earth-Moon circular restricted three-body problem (CRTBP)by the Moon-Sail two-body problem. It was found that far from the L1 and L2 points, the approximate two-body analysis for large accelerations matches well with the dynamics of displaced orbits in relation to the three-body problem. In the present study, the linear stability characteristics of the families of approximate periodic orbits are investigated.

KW - orbits

KW - space craft

KW - space flight

UR - http://www.space-flight.org/AAS_meetings/2010_winter/AAS%20San%20Diego%20Program.pdf

UR - http://www.space-flight.org/AAS_meetings/2010_winter/2010%20winter.html

M3 - Paper

SP - 1

EP - 10

T2 - 20th AIAA Space Flight Mechanics Meeting

Y2 - 14 February 2010 through 17 February 2010

ER -

On the stability of displaced two-body lunar orbits

Abstract

Conference

Keywords

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