Relative motion of satellites in elliptical orbits

Research output: Contribution to journalArticle

3 Citations (Scopus)

Abstract

The classic treatment of rendezvous mechanics, or other problems involving the relative motion of two spacecraft, assumes a circular reference orbit, allowing a relatively simple closed-form description of the motion. This paper develops a solution for an elliptical reference orbit, expanding the state transition matrix in powers of eccentricity, and gives matrix elements up to second order in eccentricity for both Cartesian and cylindrical coordinates. An example application is given for the proposed LISA (Laser Interferometer Space Antenna) gravity wave experiment.

Original languageEnglish (US)
Pages (from-to)2075-2085
Number of pages11
JournalAdvances in the Astronautical Sciences
Volume97 PART 2
StatePublished - Dec 1 1997

Fingerprint

elliptical orbits
eccentricity
Orbits
Satellites
orbits
rendezvous
LISA (observatory)
matrix
cylindrical coordinates
Gravity waves
Cartesian coordinates
gravity waves
interferometer
gravity wave
Interferometers
mechanics
Spacecraft
antenna
Mechanics
spacecraft

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

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abstract = "The classic treatment of rendezvous mechanics, or other problems involving the relative motion of two spacecraft, assumes a circular reference orbit, allowing a relatively simple closed-form description of the motion. This paper develops a solution for an elliptical reference orbit, expanding the state transition matrix in powers of eccentricity, and gives matrix elements up to second order in eccentricity for both Cartesian and cylindrical coordinates. An example application is given for the proposed LISA (Laser Interferometer Space Antenna) gravity wave experiment.",
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Relative motion of satellites in elliptical orbits. / Melton, Robert Graham.

In: Advances in the Astronautical Sciences, Vol. 97 PART 2, 01.12.1997, p. 2075-2085.

Research output: Contribution to journalArticle

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N2 - The classic treatment of rendezvous mechanics, or other problems involving the relative motion of two spacecraft, assumes a circular reference orbit, allowing a relatively simple closed-form description of the motion. This paper develops a solution for an elliptical reference orbit, expanding the state transition matrix in powers of eccentricity, and gives matrix elements up to second order in eccentricity for both Cartesian and cylindrical coordinates. An example application is given for the proposed LISA (Laser Interferometer Space Antenna) gravity wave experiment.

AB - The classic treatment of rendezvous mechanics, or other problems involving the relative motion of two spacecraft, assumes a circular reference orbit, allowing a relatively simple closed-form description of the motion. This paper develops a solution for an elliptical reference orbit, expanding the state transition matrix in powers of eccentricity, and gives matrix elements up to second order in eccentricity for both Cartesian and cylindrical coordinates. An example application is given for the proposed LISA (Laser Interferometer Space Antenna) gravity wave experiment.

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