Preliminary Design
Preliminary Design
- New search for: Sadraey, Mohammad H.
- New search for: Sadraey, Mohammad H.
This chapter covers conduct unmanned aerial vehicle (UAV) preliminary design and discusses features of current and modern UAVs. For a fixed‐wing UAV, the preliminary design phase is performed in two steps: estimate aircraft maximum takeoff weight and determine wing area and engine thrust (or power) simultaneously. For a rotary‐wing UAV (including quadcopters), the preliminary design phase is performed in two steps: estimate aircraft maximum takeoff weight and determine engine(s) thrust/power. The chapter presents matching plot technique to estimate the UAV maximum take‐off weight. The maximum takeoff weight is broken into four elements: payload weight; autopilot weight; fuel weight if non‐electric engine, or battery weight, if electric engine; and empty weight. The payload is the net carrying capacity of an UAV which is originally required and designed to carry. The payload includes sensors (e.g., camera and radar), store, military equipment, and other intended loads.
Document information
Preliminary Design
2020-03-23
29 pages
Article/Chapter (Book)
Electronic Resource
English
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