Yong-Bin Park/Khanh-Hung Nguyen/Jin-Hwe Kweon/Jin-Ho Choi/Jong-Su Han
International Journal of Aeronautical and Space Sicences, vol. 12, no. 1, pp.84-91, 2011

Abstract : A finite element analysis for the wing and landing gear of a composite target-drone air vehicle was performed. For the wing analysis, two load cases were considered: a 5g symmetric pull-up and a -1.5g symmetric push-over. For the landing gear analysis, a sinking velocity of 1.4 m/s at a 2g level landing condition was taken into account. MSC/NASTRAN and LS-DYNA were utilized for the static and dynamic analyses, respectively. Finite element results were verified by the static test of a prototype wing under a 6g symmetric pull-up condition. The test showed a 17% larger wing tip deflection than the finite element analysis. This difference is believed to come from the material and geometrical imperfections incurred during the manufacturing process.

Keyword : Target-drone, Glass fabric, Composite material, Finite element analysis