| Aircraft crashworthiness has two meanings. The first meaning is the reliability of theaircraft fuselage and landing gear systems during landing. The second meaning is the abilityto protect occupants in an event of emergency landing fall or other accidents.Landing gear is the main load-bearing part during landing which plays an extremelyimportant role in taking off and landing.Its performance will directly affect the reliability ofthe aircraft. Research on the crashworthiness in emergency landing is to advance the structureand restraint systems and improve the probability of occupants’ survival in an accident.Taxiing induced response is due to the effects of road roughness, it will cause randomvibration during the aircraft taxiing on the runway. Research on the dynamic taxiing responseof the aircraft fuselage can reduce aircraft shimmy, enhance passenger comfort and improvethe ability of pilots to control the aircraft. On the other hand, research on aircraft taxiing onthe random vibration will confirm the load course of the aircraft, and obtain the fatigue loadspectrum.Based on multi-body system dynamics theory, this paper used Adams, Patran, CATIAand other CAE software to create rigid-flexible coupling machine models of a certain type ofaircraft. Based on the characteristics of modern aircraft taxiing runway, this paper used thespatial power spectral density function of the measured statistics of the U.S. military standardrunway, employed the harmonic superposition method and inverse Fourier transform (IFFT)to construct three-dimensional runway. On that basis, using the Adams the simulation on anormal landing crashworthiness of an aircraft was completed. By calculating different waysand different landing weight landing conditions, we got various buffer forces and theoverloads of landing gear. Comparison of the results demonstrated the reasonableness of thebuffer parameter. Subsequently, this paper simulated taxiing induced response of different fuelloads fuselage, obtained the gravity acceleration of the fuselage center, wing tips, and the tailtip, then transformed the load process curve into load roll spectrum, and summed up theinfluence of fuel load in Taxiing induced response. Finally, on the base of statistics of generalaircraft crash investigation report, we analyzed the different parts of the body in fatal aviationaccidents and fatal injury frequency. Considering different tolerance against impact of various body regions, General Injury Criterion (GIC) was proposed to address the application inaviation, which aims at being an evaluation index for designing aircraft seat and restraintsystem. In union of seat dynamic test of a certain light amphibious aircraft for theseaworthiness certification, the finite element model of the test was analyzed, and GIC wasused to assess severe injury risk corresponding to various seat positions forward andbackward. |
