경비행기 “코멧”의 동체 구조해석 = Fuselage Stress Analysis of Light Aircraft “Comet”

다국어 초록 (Multilingual Abstract)

The light aircraft, "Comet" with twin seats was developed with the fuselage made of 4130 steel tube. In this paper, the stress analysis results of the fuselage are presented. For the stress analysis, three load cases are considered based on the 4.4g symmetric pull-up, -1.8g symmetric push-over, and balanced landing conditions. The fuselage structures are idealized by the truss and bar elements. MSC/PATRAN and MSC/NASTRAN were utilized as the pre/post-processor and the solver. Margins of safety of the structures are estimated based on the static strength and the Euler buckling stress. In the first design, some elements showed the negative margins of safety by the column buckling for the load conditions 1 and 3. Finally the elements were modified to have positive values. Verification of the structural safety of the fuselage will be conducted by the flight test of the prototype.