Canonical modelling of relative spacecraft motion via epicyclic orbital elements

N. Jeremy Kasdin, Pini Gurfil

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

2 Scopus citations

Abstract

This paper presents a Hamiltonian approach to modelling relative spacecraft motion based on a derivation of canonical coordinates for the relative statespace dynamics. The Hamiltonian formulation facilitates the modelling of high-order terms and orbital perturbations within the context of the Clohessy- Wiltshire solution. First, the Hamiltonian is partitioned into a linear term and a high-order term. The Hamilton-Jacobi equations are solved for the linear part by separation, and new constants for the relative motions are obtained, called epicyclic elements. The influence of higher order terms and perturbations, such as Earth's oblateness, are incorporated into the analysis by a variation of parameters procedure. As an example, closed-form solutions for J2-invariant orbits are obtained.

Original languageEnglish (US)
Title of host publicationAIAA Guidance, Navigation, and Control Conference and Exhibit
StatePublished - 2003
EventAIAA Guidance, Navigation, and Control Conference and Exhibit 2003 - Austin, TX, United States
Duration: Aug 11 2003Aug 14 2003

Publication series

NameAIAA Guidance, Navigation, and Control Conference and Exhibit

Other

OtherAIAA Guidance, Navigation, and Control Conference and Exhibit 2003
CountryUnited States
CityAustin, TX
Period8/11/038/14/03

All Science Journal Classification (ASJC) codes

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

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  • Cite this

    Kasdin, N. J., & Gurfil, P. (2003). Canonical modelling of relative spacecraft motion via epicyclic orbital elements. In AIAA Guidance, Navigation, and Control Conference and Exhibit (AIAA Guidance, Navigation, and Control Conference and Exhibit).