Optimal design for a NEO tracking spacecraft formation

Christie Maddock; Massimiliano Vasile

doi:10.1109/CEC.2007.4424576

Optimal design for a NEO tracking spacecraft formation

Christie Maddock, Massimiliano Vasile

Mechanical And Aerospace Engineering

Research output: Chapter in Book/Report/Conference proceeding › Chapter (peer-reviewed)

78 Downloads (Pure)

Abstract

The following paper presents the design and methodology for developing an optimal set of spacecraft orbits for a NEO tracking mission. The spacecraft is designed to fly in close formation with the asteroid, avoiding the nonlinear gravity field produced by the asteroid. A periodic orbit is developed, and the initial conditions are optimized by use of a global optimizer for constrained nonlinear problems. The asteroid Apophis (NEO 2004 MN4) was used as the case study
due the potential impact with Earth in 2036, and the need for more accurate ephemerides.

Original language	English
Title of host publication	IEEE Congress on Evolutionary Computing
Publisher	IEEE
Pages	Paper 1728
Number of pages	8
ISBN (Print)	978-1-4244-1339-3
DOIs	https://doi.org/10.1109/CEC.2007.4424576
Publication status	Published - 25 Sept 2007
Event	IEEE Congress on Evolutionary Computation (CEC) - Singapore Duration: 25 Sept 2007 → 28 Sept 2007

Conference

Conference	IEEE Congress on Evolutionary Computation (CEC)
City	Singapore
Period	25/09/07 → 28/09/07

Keywords

optimal design
near Earth objects
spacecraft formation flying
periodic orbit

Access to Document

10.1109/CEC.2007.4424576

Maddock C Vasile M Pure Optimal design for a NEO tracking spacecraft formationSubmitted manuscript, 325 KB

Cite this

@inbook{965a36e31a714ff4ad6a700e610dce3c,

title = "Optimal design for a NEO tracking spacecraft formation",

abstract = "The following paper presents the design and methodology for developing an optimal set of spacecraft orbits for a NEO tracking mission. The spacecraft is designed to fly in close formation with the asteroid, avoiding the nonlinear gravity field produced by the asteroid. A periodic orbit is developed, and the initial conditions are optimized by use of a global optimizer for constrained nonlinear problems. The asteroid Apophis (NEO 2004 MN4) was used as the case study due the potential impact with Earth in 2036, and the need for more accurate ephemerides. ",

keywords = "optimal design, near Earth objects, spacecraft formation flying, periodic orbit",

author = "Christie Maddock and Massimiliano Vasile",

year = "2007",

month = sep,

day = "25",

doi = "10.1109/CEC.2007.4424576",

language = "English",

isbn = "978-1-4244-1339-3",

pages = "Paper 1728",

booktitle = "IEEE Congress on Evolutionary Computing",

publisher = "IEEE",

note = "IEEE Congress on Evolutionary Computation (CEC) ; Conference date: 25-09-2007 Through 28-09-2007",

}

TY - CHAP

T1 - Optimal design for a NEO tracking spacecraft formation

AU - Maddock, Christie

AU - Vasile, Massimiliano

PY - 2007/9/25

Y1 - 2007/9/25

N2 - The following paper presents the design and methodology for developing an optimal set of spacecraft orbits for a NEO tracking mission. The spacecraft is designed to fly in close formation with the asteroid, avoiding the nonlinear gravity field produced by the asteroid. A periodic orbit is developed, and the initial conditions are optimized by use of a global optimizer for constrained nonlinear problems. The asteroid Apophis (NEO 2004 MN4) was used as the case study due the potential impact with Earth in 2036, and the need for more accurate ephemerides.

AB - The following paper presents the design and methodology for developing an optimal set of spacecraft orbits for a NEO tracking mission. The spacecraft is designed to fly in close formation with the asteroid, avoiding the nonlinear gravity field produced by the asteroid. A periodic orbit is developed, and the initial conditions are optimized by use of a global optimizer for constrained nonlinear problems. The asteroid Apophis (NEO 2004 MN4) was used as the case study due the potential impact with Earth in 2036, and the need for more accurate ephemerides.

KW - optimal design

KW - near Earth objects

KW - spacecraft formation flying

KW - periodic orbit

U2 - 10.1109/CEC.2007.4424576

DO - 10.1109/CEC.2007.4424576

M3 - Chapter (peer-reviewed)

SN - 978-1-4244-1339-3

SP - Paper 1728

BT - IEEE Congress on Evolutionary Computing

PB - IEEE

T2 - IEEE Congress on Evolutionary Computation (CEC)

Y2 - 25 September 2007 through 28 September 2007

ER -

Optimal design for a NEO tracking spacecraft formation

Abstract

Conference

Keywords

Access to Document

Fingerprint

Cite this