This paper discusses the effect of sequential conflict resolution maneuvers of an infinite aircraft flow through a finite control volume. Aircraft flow models are utilized to simulate traffic flows and determine stability. Pseudo-random flow geometry is considered to determine airspace stability in a more random airspace, where aircraft flows are spread over a given positive width. The use of this aircraft flow model generalizes the orthogonal flow geometry for arbitrary flow width. A set of upper bounds on the maximal aircraft deviation during conflict resolution is derived. Also with this flow geometry it is proven that these bounds are not symmetric, unlike the symmetric bounds derived in previous papers for simpler flow configurations (i.e. orthogonal flow geometry). Stability is preserved under sequential conflict resolution algorithms for all flow geometries discussed in this paper. © 2011 AACC American Automatic Control Council.
|Original language||English (US)|
|Title of host publication||Proceedings of the American Control Conference|
|Publisher||Institute of Electrical and Electronics Engineers Inc.|
|Number of pages||6|
|State||Published - Jan 1 2011|