Testing and Developing the Strength of Unmanned Aircraft Wing Structures

Abstract

This research has collected data on the use of the unmanned aerial vehicle Tigershark II from The Research and Development Centre for Space and Aeronautical Science and Technology, RTAF. From the data, it was found that the wing structure is robust but heavy, leading to high-speed flight and fuel inefficiency. Researchers aim to reduce wing structure weight by improving and developing internal components to decrease overall weight. The objective is to test the Tigershark II unmanned aerial vehicle wing structure according to the original plan using Finite Element Analysis with FEMAP and NX-Nastran software, and then create a new wing based on the results. Testing involved applying forces to the wing using sandbags according to NATO STANAG 4671 standards. Results showed that the original wing design weighed 26 kilograms, supporting a maximum load of 900 kilograms or a Load Factor of 7.23 times the aircraft weight. The new wing design weighed 16 kilograms less, achieving a weight reduction of 38%. It also met strength standards, exceeding the Proof Load Factor of 4.37 times the aircraft weight. However, further study is recommended, including dynamic wing testing or fatigue testing.