Geometric integration of impact during an orbital docking procedure

Corrina Gibson*, Todd D. Murphey

*Corresponding author for this work

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

Abstract

Simulations of orbiting bodies that experience self-impact during manuevers are known to potentially lead to numerical instability. In this paper it is demonstrated that the dynamics of an orbiting articulated body experiencing forcing and impacting can be stably simulated using variational integration. A prominent advantage of using variational integration is that conservation properties are maintained (even in the presence of external forcing) and natively can resolve impacts. Using variational integration, the configuration of the spacecraft is updated discretely to ensure that the system-subject to any applied constraints, forces, or impacts-will yield a new configuration that satisfies all conservation properties. Furthermore, variational integrators allow impacts to be easily implemented into the configuration update.

Original languageEnglish (US)
Title of host publication2010 IEEE International Conference on Automation Science and Engineering, CASE 2010
Pages928-932
Number of pages5
DOIs
StatePublished - Nov 17 2010
Event2010 IEEE International Conference on Automation Science and Engineering, CASE 2010 - Toronto, ON, Canada
Duration: Aug 21 2010Aug 24 2010

Publication series

Name2010 IEEE International Conference on Automation Science and Engineering, CASE 2010

Other

Other2010 IEEE International Conference on Automation Science and Engineering, CASE 2010
CountryCanada
CityToronto, ON
Period8/21/108/24/10

ASJC Scopus subject areas

  • Control and Systems Engineering

Fingerprint Dive into the research topics of 'Geometric integration of impact during an orbital docking procedure'. Together they form a unique fingerprint.

Cite this