Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization

Davide Conte, Guanwei He, David Bradley Spencer, Robert Graham Melton

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

In this paper a simple and efficient way of computing impulsive maneuver transfers from a user-defined Low Earth Orbit (LEO) to a desired lunar halo orbit around the Earth-Moon Lagrange point 2 (EML2) utilizing a heuristic optimization method is presented. The dynamical framework utilized is the Circular Restricted Three-Body Problem (CR3BP). Sample LEO to lunar halo trajectories along with their required 'V costs and Time-of-Flight (TOF) are provided and compared to known numerical techniques to assert the validity of the proposed method. The obtained results are close in both 'V and TOF to what the existing literature reports.

Original languageEnglish (US)
Title of host publicationAAS/AIAA Astrodynamics Specialist Conference, 2018
EditorsPuneet Singla, Brandon A. Jones, Ryan M. Weisman, Belinda G. Marchand
PublisherUnivelt Inc.
Pages1335-1353
Number of pages19
ISBN (Print)9780877036579
StatePublished - Jan 1 2018
EventAAS/AIAA Astrodynamics Specialist Conference, 2018 - Montreal, Canada
Duration: Aug 19 2018Aug 23 2018

Publication series

NameAdvances in the Astronautical Sciences
Volume167
ISSN (Print)0065-3438

Conference

ConferenceAAS/AIAA Astrodynamics Specialist Conference, 2018
CountryCanada
CityMontreal
Period8/19/188/23/18

Fingerprint

pyrotechnics
low Earth orbits
halos
Orbits
Earth (planet)
trajectory
Trajectories
trajectories
orbits
optimization
three body problem
maneuvers
moon
Moon
costs
heuristics
cost
Costs
method

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

Conte, D., He, G., Spencer, D. B., & Melton, R. G. (2018). Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization. In P. Singla, B. A. Jones, R. M. Weisman, & B. G. Marchand (Eds.), AAS/AIAA Astrodynamics Specialist Conference, 2018 (pp. 1335-1353). (Advances in the Astronautical Sciences; Vol. 167). Univelt Inc..
Conte, Davide ; He, Guanwei ; Spencer, David Bradley ; Melton, Robert Graham. / Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization. AAS/AIAA Astrodynamics Specialist Conference, 2018. editor / Puneet Singla ; Brandon A. Jones ; Ryan M. Weisman ; Belinda G. Marchand. Univelt Inc., 2018. pp. 1335-1353 (Advances in the Astronautical Sciences).
@inproceedings{c28f96bdbbba485da93e4ec11ed325d7,
title = "Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization",
abstract = "In this paper a simple and efficient way of computing impulsive maneuver transfers from a user-defined Low Earth Orbit (LEO) to a desired lunar halo orbit around the Earth-Moon Lagrange point 2 (EML2) utilizing a heuristic optimization method is presented. The dynamical framework utilized is the Circular Restricted Three-Body Problem (CR3BP). Sample LEO to lunar halo trajectories along with their required 'V costs and Time-of-Flight (TOF) are provided and compared to known numerical techniques to assert the validity of the proposed method. The obtained results are close in both 'V and TOF to what the existing literature reports.",
author = "Davide Conte and Guanwei He and Spencer, {David Bradley} and Melton, {Robert Graham}",
year = "2018",
month = "1",
day = "1",
language = "English (US)",
isbn = "9780877036579",
series = "Advances in the Astronautical Sciences",
publisher = "Univelt Inc.",
pages = "1335--1353",
editor = "Puneet Singla and Jones, {Brandon A.} and Weisman, {Ryan M.} and Marchand, {Belinda G.}",
booktitle = "AAS/AIAA Astrodynamics Specialist Conference, 2018",
address = "United States",

}

Conte, D, He, G, Spencer, DB & Melton, RG 2018, Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization. in P Singla, BA Jones, RM Weisman & BG Marchand (eds), AAS/AIAA Astrodynamics Specialist Conference, 2018. Advances in the Astronautical Sciences, vol. 167, Univelt Inc., pp. 1335-1353, AAS/AIAA Astrodynamics Specialist Conference, 2018, Montreal, Canada, 8/19/18.

Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization. / Conte, Davide; He, Guanwei; Spencer, David Bradley; Melton, Robert Graham.

AAS/AIAA Astrodynamics Specialist Conference, 2018. ed. / Puneet Singla; Brandon A. Jones; Ryan M. Weisman; Belinda G. Marchand. Univelt Inc., 2018. p. 1335-1353 (Advances in the Astronautical Sciences; Vol. 167).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

TY - GEN

T1 - Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization

AU - Conte, Davide

AU - He, Guanwei

AU - Spencer, David Bradley

AU - Melton, Robert Graham

PY - 2018/1/1

Y1 - 2018/1/1

N2 - In this paper a simple and efficient way of computing impulsive maneuver transfers from a user-defined Low Earth Orbit (LEO) to a desired lunar halo orbit around the Earth-Moon Lagrange point 2 (EML2) utilizing a heuristic optimization method is presented. The dynamical framework utilized is the Circular Restricted Three-Body Problem (CR3BP). Sample LEO to lunar halo trajectories along with their required 'V costs and Time-of-Flight (TOF) are provided and compared to known numerical techniques to assert the validity of the proposed method. The obtained results are close in both 'V and TOF to what the existing literature reports.

AB - In this paper a simple and efficient way of computing impulsive maneuver transfers from a user-defined Low Earth Orbit (LEO) to a desired lunar halo orbit around the Earth-Moon Lagrange point 2 (EML2) utilizing a heuristic optimization method is presented. The dynamical framework utilized is the Circular Restricted Three-Body Problem (CR3BP). Sample LEO to lunar halo trajectories along with their required 'V costs and Time-of-Flight (TOF) are provided and compared to known numerical techniques to assert the validity of the proposed method. The obtained results are close in both 'V and TOF to what the existing literature reports.

UR - http://www.scopus.com/inward/record.url?scp=85065738719&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85065738719&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:85065738719

SN - 9780877036579

T3 - Advances in the Astronautical Sciences

SP - 1335

EP - 1353

BT - AAS/AIAA Astrodynamics Specialist Conference, 2018

A2 - Singla, Puneet

A2 - Jones, Brandon A.

A2 - Weisman, Ryan M.

A2 - Marchand, Belinda G.

PB - Univelt Inc.

ER -

Conte D, He G, Spencer DB, Melton RG. Trajectory design for lEO to lunar halo orbits using manifold theory and fireworks optimization. In Singla P, Jones BA, Weisman RM, Marchand BG, editors, AAS/AIAA Astrodynamics Specialist Conference, 2018. Univelt Inc. 2018. p. 1335-1353. (Advances in the Astronautical Sciences).