Subjects: Mechanics >> Applied Mechanics submitted time 2023-03-20 Cooperative journals: 《应用力学学报》
Abstract： The landing gear drop shock featured with wing lift directly applies the equivalent lift to thelanding gear instead of reducing the equivalent mass , and the effect of wing lift on the landing performanceof landing gear is considered. The landing process of the landing gear can be simulated more truly with theaid of the landing gear drop test featured with wing lift. This paper takes a certain type of strut-type mainlanding gear as the research object. Based on different lift loading methods ( i.e. , theoretical lift simulationand drop test lift simulation) , first , the dynamic model of landing gear drop shock featured with wing lift isestablished. Then , the numerical simulation of landing gear drop shock featured with wing lift is carried outby using ALTLAS software.Finally , the landing gear drop test is carried out on the drop test bench with thewing lift simulation device. By the verification and comparison of the results under different sinkingspeeds , the correctness and effectiveness of the application of lift loading method in the landing gear droptest featured with wing lift are verified.Drop test lift simulation realizes the loading of the equivalent lift on the landing gear via the theoretical modeling of the system of landing gear drop test featured with wing lift.The drop test lift simulation can effectively assist the development of the landing gear buffer system and theverification of the buffer performance.
Subjects: Mechanics >> Applied Mechanics submitted time 2023-03-20 Cooperative journals: 《应用力学学报》
Abstract： In order to ensure the bird strike resistance of amphibious aircraft tail , different design ideaswere proposed against the different structural parts. A numerical analysis model coupled with SPH methodwas established to simulate the bird strike resistance of the amphibious aircraft tail. The stress-strain curvesof aluminum alloy used for tail structure were obtained by quasi-static , medium-low strain rate tensiletests. Based on tensile and shear tests of fasteners at different speeds ,the ultimate tensile and shear loadsof fasteners with based aluminum metal were obtained.'The numerical analysis results were verified by thebird strike tests of amphibious aircraft tail. Numerical analysis and experimental results show that the de-sign ideas of the amphibious aircraft tail are reasonable and have good performance of bird strike resistance.Three kinds of aluminum alloys used in the structure have an obvious strain hardening effect , but thestrain rate sensitivity is weak.With the increase of loading speed, the tensile load of the four rivets decrea-ses , but is not obvious , while the shear load changes little.The numerical analysis model of bind impact isaccurate and can predict the failure mode of the structure and the process of bird impact dispersion well.
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