AN EXPERIMENTAL DETERMINATION AND NUMERICAL ANALYSIS OF A LOITER MUNITION UNMANNED AERIAL VEHICLE SYSTEM

Öz

This paper experimentally determinates the calculation of an Unmanned Aerial Vehicle (UAV) and analyzes the design criteria within four different scenarios. The UAV to be designed is a loiter munition UAV system. A mobile or equipment such as a parachute and/or airbag. The UAV may be operable day and night conditions, capable of 2-3 hours of flight hours, and will be launched from a catapult. The UAV navigation system is compact and easily controlled by a personal Global Positioning System (GPS). The mentioned UAV will have a vast operational capability, especially for defense and border security activities since it is equipped with advanced avionics and a small physical footprint for covert operations. As a consequence of this research, it can be claimed that the UAV's mid-wing, twin-tail, and relatively light body will have three axis stability and offer numerous benefits, particularly in terms of operational cost.

Anahtar Kelimeler

• Mission Profile
• Speed Condition
• Weight Calculation
• Unmanned Aerial Vehicle (UAV)
• Wing Design
• Tail Design

Kaynakça

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