Sun-Earth triangular Lagrange point orbit insertion and satellite station keeping

Julio Cesar Benavides, David Bradley Spencer

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

Abstract

Minimizing the amount of fuel needed to place a satellite into Earth orbit and then inserting it into its operational altitude is an important driver of space mission analysis and design. This paper analyzes the velocity changes required to transfer satellites initially in Earth orbit to the Sun-Earth triangular Lagrange points and estimates the minimum velocity changes needed for station keeping at those points after the satellite's two-body motion around the Sun has been gravitationally perturbed. Times of flight required by each insertion and station keeping scenario investigated are also analyzed. Analytical, co-orbital rendezvous equations for an elliptical Earth orbit are derived as a function of Earth true anomaly and solved numerically due to their transcendental nature. These equations predict that total, minimum velocity changes are comparable to the solution of Lambert's problem for various times of flight. When these velocity change results are compared to the velocity changes required to transfer a satellite from Earth orbit to the planets, it can be concluded that a transfer from Earth orbit to the Sun-Earth L4 and L5 Lagrange points is comparable to a transfer from the Earth to Venus or the Earth to Mars. Station keeping velocity changes and times of flight are investigated by solving Lambert's problem for various initial conditions. The investigation shows that the minimum velocity changes needed to station keep a satellite positioned at L4 or L5 are in general inversely proportional to the corresponding times of flight needed to implement the station keeping maneuvers and directly proportional to the perturbation time elapsed when the maneuvers are commenced.

Original languageEnglish (US)
Title of host publicationAmerican Astronautical Society - Space Flight Mechanics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting
Pages1961-1985
Number of pages25
Volume127 PART 2
StatePublished - 2007
Event17th Annual Space Flight Mechanics Meeting - Sedona, AZ, United States
Duration: Jan 28 2007Feb 1 2007

Other

Other17th Annual Space Flight Mechanics Meeting
CountryUnited States
CitySedona, AZ
Period1/28/072/1/07

Fingerprint

orbit insertion
Sun
Earth orbits
sun
Orbits
stations
Earth (planet)
Satellites
maneuvers
orbital rendezvous
elliptical orbits
satellite orbits
Venus (planet)
space missions
station
mars
planets
insertion
Planets
Venus

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

Benavides, J. C., & Spencer, D. B. (2007). Sun-Earth triangular Lagrange point orbit insertion and satellite station keeping. In American Astronautical Society - Space Flight Mechanics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting (Vol. 127 PART 2, pp. 1961-1985)
Benavides, Julio Cesar ; Spencer, David Bradley. / Sun-Earth triangular Lagrange point orbit insertion and satellite station keeping. American Astronautical Society - Space Flight Mechanics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting. Vol. 127 PART 2 2007. pp. 1961-1985
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Benavides, JC & Spencer, DB 2007, Sun-Earth triangular Lagrange point orbit insertion and satellite station keeping. in American Astronautical Society - Space Flight Mechanics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting. vol. 127 PART 2, pp. 1961-1985, 17th Annual Space Flight Mechanics Meeting, Sedona, AZ, United States, 1/28/07.

Sun-Earth triangular Lagrange point orbit insertion and satellite station keeping. / Benavides, Julio Cesar; Spencer, David Bradley.

American Astronautical Society - Space Flight Mechanics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting. Vol. 127 PART 2 2007. p. 1961-1985.

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

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Benavides JC, Spencer DB. Sun-Earth triangular Lagrange point orbit insertion and satellite station keeping. In American Astronautical Society - Space Flight Mechanics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting. Vol. 127 PART 2. 2007. p. 1961-1985