الفهرس 
صفحة العنوانOnly 14 pages are availabe for public view
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Abstract
Weight reduction of Unmanned Aerial Vehicle (UAV) components and systems is an essential factor for aviation. Take-off gross weight can be divided into crew weight, payload weight, fuel weight, and empty weight. The empty weight is divided into the structure, engine/s, landing gear, avionics and fixed equipment. Engine/s, landing gear, avionics and fixed equipment are selective items. Weight optimization can be made for structure and landing gear to minimize aircraft total weight.
The main objective of this study is optimizing weight and reach safe landing for a medium range Unmanned Aerial Vehicle (UAV) Landing gear.
In the present study, ANSYS shape (Topology) optimization tool is used to get a proposed shape for the UAV landing gear. Then parametric size optimization of the shape proposed was done. Design of experiment (DOE) technique is used in order to get the minimum weight for the landing gear at a specified stress limit. Two different materials were used, Aluminum alloy 7075-T651, woven bi-directional carbon fiber.
It was found that using topology weight optimization technique reduce Aluminum Alloy landing gear weight by (30.4%) changing the material to be woven bi-directional carbon fiber without optimization reduce landing gear weight with additional value (27.9%). Optimizing woven bi-directional carbon fiber landing gear reduces the weight with additional value (4%) to be the total weight ratio by (62.3%).
Changing topology weight optimization to topography weight optimization technique reduce Aluminum Alloy landing gear weight by (22.5%), woven bi- directional carbon fiber without optimization reduce landing gear weight with additional value (35.8%). Optimizing woven bi-directional carbon fiber landing gear reduces the weight with additional value (1.1%) to be the total weight ratio by (59.4%).