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Small UAV Design Development and Sizing

  • Steven A. Brandt
Reference work entry

Abstract

This chapter describes a rationale for selecting a low-risk UAV (Unmanned Aerial Vehicle) configuration and a methodology for sizing and optimizing the shape of both fueled and electric-powered aircraft. Three examples are given of low-risk UAV configurations. These are shown to be essentially similar from the point of view of optimization and sizing. The sizing methodology for fueled aircraft is described in detail, and a similar one for electric-powered aircraft is described to the extent that it differs from that for fueled aircraft. The chapter also gives typical values of technology-related parameters used in sizing calculations. It then shows an example of a small UAV designed using this methodology. The UAV design project showed that the methodology is useful in obtaining aircraft of minimum size for the performance and payload required.

Keywords

Design Mission Wing Area Wing Loading Fuel Flow Rate Constraint Analysis 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

References

  1. S.A. Brandt, F.P. Gilliam, A design analysis methodology for solar-powered aircraft. J. Aircr. 766–780 (1994)Google Scholar
  2. S.A. Brandt et al., Introduction to Aeronautics: A Design Perspective. AIAA Education Series, 2nd edn. (AIAA, Reston, 2004)Google Scholar
  3. J.R. Smith, P.G. Batish, S.A. Brandt, S.R. Morton, A student-developed sizing methodology for electric-powered aircraft applied to small UAVs, in WAC Paper 2000-01-5536, Proceedings of the 5th AIAA/SAE World Aviation Congress, San Diego, 10–12 Oct 2000Google Scholar

Copyright information

© Springer Science+Business Media Dordrecht 2015

Authors and Affiliations

  1. 1.Department of AeronauticsUnited States Air Force AcademyColorado SpringsUSA

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