Eliminating perigee rotation in J 2 perturbed orbits with a constant radial acceleration

Christopher C. Wilkins, Vikram Kapila

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

Abstract

In this paper, for Earth-orbiting spacecraft in inclined, elliptical orbits, we present a control technique that uses a constant specific thrust (i.e., acceleration) to eliminate the rotation of the perigee that occurs due to the J 2 perturbation arising from Earth's oblateness. Specifically, by averaging the rate of change of orbital elements, originating from disturbing accelerations over one orbital period, we obtain an expression that relates the secular growth of the argument of the perigee to a constant radial acceleration control. This control is used to eliminate the secular growth of the argument of the perigee due to the J 2 perturbation. To justify the framework proposed in this paper, we also provide analytical expressions for the secular growth of all orbital elements caused by constant accelerations in the radial, in-plane, and out-of-plane directions. Simulation results are presented to illustrate the efficacy of the radial acceleration control in eliminating the rotation of the perigee.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007
Pages5001-5013
Number of pages13
Volume5
StatePublished - 2007
EventAIAA Guidance, Navigation, and Control Conference 2007 - Hilton Head, SC, United States
Duration: Aug 20 2007Aug 23 2007

Other

OtherAIAA Guidance, Navigation, and Control Conference 2007
CountryUnited States
CityHilton Head, SC
Period8/20/078/23/07

Fingerprint

Acceleration control
Orbits
Earth (planet)
Spacecraft

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

Cite this

Wilkins, C. C., & Kapila, V. (2007). Eliminating perigee rotation in J 2 perturbed orbits with a constant radial acceleration. In Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007 (Vol. 5, pp. 5001-5013)

Eliminating perigee rotation in J 2 perturbed orbits with a constant radial acceleration. / Wilkins, Christopher C.; Kapila, Vikram.

Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007. Vol. 5 2007. p. 5001-5013.

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

Wilkins, CC & Kapila, V 2007, Eliminating perigee rotation in J 2 perturbed orbits with a constant radial acceleration. in Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007. vol. 5, pp. 5001-5013, AIAA Guidance, Navigation, and Control Conference 2007, Hilton Head, SC, United States, 8/20/07.
Wilkins CC, Kapila V. Eliminating perigee rotation in J 2 perturbed orbits with a constant radial acceleration. In Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007. Vol. 5. 2007. p. 5001-5013
Wilkins, Christopher C. ; Kapila, Vikram. / Eliminating perigee rotation in J 2 perturbed orbits with a constant radial acceleration. Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007. Vol. 5 2007. pp. 5001-5013
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