ANSYS/LS-DYNA. skin panel. stringer. frame frame. 2 frame. strut (floor beam) 3 strut. floor beam. 4 floor beam. frame strut floor beam gusset plate
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1 ANSYS/LS-DYNA skin panel stringer 0.80mm ANSYS/LS-DYNA skin panel installation surface 2 (floor beam) 10.0mm mm 0.40mm 426.8mm 40.0mm 370.0mm 3 floor beam R=229.3mm C L 300.0mm 185.0mm 160.0mm R=222.1mm floor beam 0.80mm 15.0mm 1 floor beam 4 floor beam
2 8 0.80mm 0.40mm 10.0mm mm 14.4mm 8 skin panel floor beam 9 floor beam 0.80mm floor beam 0.80mm 0.80mm 1.60mm stringer e 1.60mm DYNA 6 9 floor beam 180.0mm 370.0mm Assumption mass of the upper part of the fuselage The seat and crewmen assumption mass Strut 40.0mm Floor beam e' skin panel skin panel 10 skin panel 6 skin panel 10 skin panel (shell163) mm The use part The use material 0.40mm skin panel Al2024-T3 sheet,, floor beam, Al7075-T6 sheet b skin panel c c' floor beam d b' 0.80mm()+0.80mm(floor beam) d' 0.80mm()+0.40mm() floor beam 0.40mm()+0.40mm(skin panel) a a' 0.80mm()+0.40mm() 7 skin panel Al2024-T3 Al7075-T6 Al2024-T3 JIS
3 11 2 Stress(GPa) standard examination tangent modulus (Gpa) Young's modulus (Gpa) two straight line approximation Strain(%) 11 Tensile stress-strain relation of Al 2024-T3 mass 12.50kgf mass 12.00kgf m/sec 0.2% GPa 2.0% 7.7% GPa GPa 13 Von Mises MIL-Spec. MIL-HDBK-5F Al2024-T3 sheet ksi GPa JIS Al2024-T3 2 2 Al2024-T3 Young s modulus(gpa) Poisson ratio Yield stress(gpa) Tangent modulus(gpa) Stress(GPa) standard examination two straight line approximation tangent modulus (Gpa) Young's modulus (Gpa) Strain(%) 12 Tensile stress-strain relation of Al7075-T6 13 skin panel Al7075-T6 Al7075-T6 JIS mass 2 mass MIL-Spec. mass Al7075-T6 3 3 Al7075-T6 Young s modulus(gpa) Poisson ratio Yield stress(gpa) Tangent modulus(gpa) mass Al2024-T3 mass
4 Displacement(mm) Al2024-T3 Al7075-T6 Al7075-T6 Al7075-T6 Al2024-T3 MIL-Spec. 4.10m/sec 20.0% 4.40m/sec m/sec 5 Al7075-T6 Young s modulus(gpa) Poisson ratio Seat and crewmen Experiment Yield stress(gpa) assumption mass 50 Tangent modulus(gpa) Assumption mass of the upper part of the fuselage Time(msec) 14 d skin panel(al2024) 15 skin panel skin panel 1 Young s modulus yield Al2024-T3 stress tangent modulus mm skin panel 0.40mm MIL-Spec. 2:1 Al7075-T6 MIL-Spec. MIL-HDBK-5F Al2024-T3 2:1 Al2024-T3 sheet ksi 0.24 Young s modulus 0.26GPa tangent modulus 2:1 0.30GPa 20.0% % 0.24GPa 3 4 Al2024-T3 Young s modulus(gpa) Poisson ratio Yield stress(gpa) Tangent modulus(gpa) Al204-T3 Al7075-T6 Al2024-T3 Al7075-T6 skin panel 15 Al7075-T6 skin panel Al2024-T3 skin panel (Al2024) (Al7075) d' (Al7075) 0.80mm()+0.40mm(skin panel) 6 Al2024-T3 Al7075-T6 Young s modulus(gpa) Poisson ratio Yield stress(gpa) Tangent modulus(gpa)
5 Young s modulus Von Mises mm a a' rivet Frame rivet 16 rivet 17 stress(gpa) Seat and crewmen assumption mass Experiment Assumption mass of the upper part of the fuselage time(msec) floor beam skin panel floor beam : tension skin panel : compression : compression skin panel : compression 18 mass 24 mass mass mass
6 15.0msec 20.0msec 15.0msec 20.0mse skin panel % Al2024-T3 6 Al7075-T6 7 7 Al2024-T3 Tension Compression Young s modulus(gpa) Poison ratio Yield stress(gpa) Tangent modulus(gpa) Al7075-T6 Tension Compression 20 Young s modulus(gpa) Poison ratio Yield stress(gpa) Tangent modulus(gpa) floor beam floor beam skin panel 20.0% stress(gpa) Experiment Assumption mass of the upper part of the fuselage Seat and crewmen assumption mass time(msec) 21 Von Mises skin panel
7 [1] " [2] " " [3] " " [4] " mass [5] "LS-DYNA3D " 5 Al2024-T3 Al7075-T [6] "ANSYS/LS-DYNA " ANSYS Conference in Japan [7]Ikuo KUMAKURA Masakatsu MINEGISHI Kazuo IWASAKI Takefumi HOSOKAWA "Impact Simulation of Simplified Structural Models of Aircraft Fuselarge" World Aviation Congress [8] " mass " [9] " " [10] "ANSYS/LS-DYNA 20.0% " ANSYS Conference in Japan ANSYS/LS-DYNA
![[7]Ikuo KUMAKURA Masakatsu MINEGISHI Kazuo IWASAKI Takefumi HOSOKAWA "Impact Simulation of Simplified Structural](/docs-images/47/23772393/images/page_7.jpg "Models of Aircraft Fuselarge\" World Aviation Congress 2000 2000. [8] \" mass \" 2001. [9] \" \" 6 2001.")
8 . LS-DYNA Summary. Numerical Simulation of Crashworthiness of Aircraft Cabin Structures Takefumi Hosokawa Division of Engineering, Specialize in System Engineering, HOSEI University Ikuo Kumakura Masakatsu Minegishi Kazuo Iwasaki Structural Integrity Group, Structures and Materials Research Center, National Aerospace Laboratory of Japan Hiroshi Takeda Department of System Control Engineering, Faculty of Engineering, HOSEI University While the rate of air accident has not been improved for more the 15 years, the number of accidents will be expected to increase in future. In case crash accident of aircraft, it is important to reduce the impact load to passengers bellow the allowable level of the human body. In this research, the behavior of the aircraft fuselage structure in crash condition is numerically analyzed by using ANSYS/LS-DYNA, and the results are compared with experimental results. The correlation between analysis and experiments are improved by introducing some assumptions on material constants. In this study, it is shown that our numerical models are applicable to predict crash behavior of aircraft fuselage structures in crash condition. Keywords. Dynamic analysis, Crashworthiness, Deformation behavior, Impact load, LS-DYNA
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