This chapter analyzes a unmanned aerial vehicle (UAV) configuration and provides design feedbacks by UAV design program. It presents a few design analyses: flight stability analysis; flight performance analysis; controllability analysis; and cost analysis. Mass and moment of inertia of components such as wing, fuselage, tail, engine, and landing gear, plus payload, fuel and autopilot, have a significant impact on stability and control of a UAV. The aircraft and mass moment of inertia calculations provide feedbacks in the overall design process. The chapter also presents a technique to determine the UAV center of gravity. An important UAV design requirement is flight stability. Stability is often divided into two branches: static stability and dynamic stability. Another design analysis is the UAV flight mechanics evaluation which mainly concentrates on performance parameters such as maximum speed, rang, and endurance. A significant step in a UAV design project is the cost analysis, which forecasts the UAV life‐cycle cost.
Design Analysis and Feedbacks
Design of Unmanned Aerial Systems ; 565-600
2020-03-23
36 pages
Article/Chapter (Book)
Electronic Resource
English
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