Small UAV Design Development and Sizing
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.
KeywordsDesign Mission Wing Area Wing Loading Fuel Flow Rate Constraint Analysis
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