University of Hertfordshire

By the same authors

Fixed-Wing approach techniques for complex environments

Research output: Contribution to journalArticle

View graph of relations
Original languageEnglish
Article number4109
Number of pages18
Pages (from-to)999-1016
JournalThe Aeronautical Journal
Journal publication date1 Aug 2015
Volume119
Issue1218
DOIs
Publication statusPublished - 1 Aug 2015

Abstract

The landing approach for fixed-wing small unmanned air vehicles (SUAVs) in complex environments such as urban canyons, wooded areas, or any other obscured terrain is challenging due to the limited distance available for conventional glide slope descents. Alternative approach methods, such as deep stall and spin techniques, are beneficial for such environments but are less conventional and would benefit from further qualitative and quantitative understanding to improve their implementation. Flight tests of such techniques, with a representative remotely piloted vehicle, have been carried out for this purpose and the results are presented in this paper. Trajectories and flight data for a range of approach techniques are presented and conclusions are drawn as to the potential benefits and issues of using such techniques for SUAV landings. In particular, the stability of the vehicle on entry to a deep stall was noticeably improved through the use of symmetric inboard flaps (crow brakes). Spiral descent profiles investigated, including spin descents, produced faster descent rates and further reduced landing space requirements. However, sufficient control authority was maintainable in a spiral stall descent, whereas it was compromised in a full spin. - See more at: http://aerosociety.com/News/Publications/Aero-Journal/Online/3384/Fixedwing-approach-techniques-for-complex-environments#sthash.dfFiOay6.dpuf

Notes

P. R. Thomas, S. Bullock, U. Bhandari and T. S. Richardson, 'Fixed-wing approach techniques for complex environments', The Aeronautical Journal, Vol. 119 (1218): 999-1016, August 2015, available on line at doi: 10.1017/S0001924000004292 Cambridge University Press. © 2015 Royal Aeronautical Society

ID: 9290025