The main aim of the presented research was to check mechanical response of human body model under loads that can occur during airplane accidents and compare results of analysis with some results of experimental tests described in literature. In simulations, new multi-purpose human body model, the VIRTHUMAN, was used. The whole model, as well as its particular segments, was earlier validated based on experimental data, which proved its accuracy to simulate human body dynamic response under condition typical for car crashes, but it was not validated for loads with predominant vertical component (loads acting along spinal column), typical for airplane crashes. Due to limitation of available experimental data, the authors focused on conducting calculations for the case introduced in 14 CFR: Parts 23.562 and 25.562, paragraph (b)(1), knowing as the 60 • pitch test. The analysis consists in comparison of compression load measured in lumbar section of spine of the FAA HIII Dummy (experimental model) and in the Virthuman (numerical model). The performed analyses show numerical stability of the model and satisfactory agreement between experimental data and simulated Virthuman responses. In that sense, the Virthuman model, although originally developed for automotive analyses, shows also great potential to become valuable tool for applications in aviation crashworthiness and safety analyses, as well.
Numerical Simulation of Glider Crash Against a Non-Deformable Barrier This study, describing computer simulation of a glider crash against a non-deformable ground barrier, is a part of a larger glider crash modeling project. The studies were intended to develop a numerical model of the pilot - glider - environment system, whereby the dynamics of the human body and the composite cockpit structure during a crash would make it possible to analyze flight accidents with focus on the pilot's safety. Notwithstanding that accidents involving glider crash against a rigid barrier (a wall, for example) are not common, establishing a simulation model for such event may prove quite useful considering subsequent research projects. First, it is much easier to observe the process of composite cockpit structure destruction if the crash is against a rigid barrier. Furthermore, the use of a non-deformable barrier allows one to avoid the errors that are associated with the modeling of a deformable substrate, which in most cases in quite problematic. Crash test simulation, carried out using a MAYMO package, involved a glider crash against a wall positioned perpendicularly to the object moving at a speed of 77 km/h. Computations allowed for determination of time intervals of the signals that are required to assess the behavior of the cockpit and pilot's body - accelerations and displacements in selected points of the glider's structure and loads applied to the pilot's body: head and chest accelerations, forces at femur, lumbar spine and safety belts. Computational results were compared with the results of a previous experimental test that had been designed to verify the numerical model. The glider's cockpit was completely destroyed in the crash and the loads transferred to the pilot's body were very substantial - way over the permitted levels. Since modeling results are fairly consistent with the experimental test, the numerical model can be used for simulation of plane crashes in the future.
One major problem associated with gliding is the safety of the crew during landings in the country outside the airfield. The analysis of glider-accident statistics shows that such out-landings may significantly influence the safety. Therefore, of vital importance are the crashworthiness properties of the glider fuselage structure. The subject of the study was the PW-5 glider fuselage made of composites and subjected to high loads typical of glider crashes. The aim was to provide experimental data for validation of a numerical model of the cockpit-pilot system during impact. Two experimental tests with the composite glider cockpit were performed using a typical car-crash track. During the first test the cockpit with a dummy inside was crashed onto the ground at the angle of 45 degrees at a speed of 55 km/h. Accelerations and deformations at chosen points in the cockpit as well as signals coming from the dummy sensors and forces in the seat belts were recorded. The second test was an impact into a concrete wall at a speed of about 80 km/h. The full-scale tests were accompanied by a number of quasi-static and dynamic laboratory tests on samples of composite material. The experimental tests provided valuable results for the parametrical identification of a simulation model developed using the MADYMO software.
Purpose This paper aims to present the assumptions, analysis and sample results of numerical modeling and analysis of dynamic events encountered in emergency cases during deployment of parachute rescue system (PRS) and hard landing of a small gyrocopter. The optimal design requires knowledge of structural loads and structural response – the information obtained often from experiment. Numerical simulation is presented as an alternative tool for estimating these data. Design/methodology/approach Structural analyses were performed using MSC.Nastran. Multibody simulations were done using MADYMO system. Findings Initial design parameters were evaluated and verified in numerical simulations. Some of the resulting conclusions were proven during the test flights. Practical implications Some chosen results of simulation of dynamic problems are presented. They can be useful as reference values for similar cases for light aircraft analysis. Originality/value The paper presents an alternative way of assessing structural response parameters in the case of emergency dynamic events of usage of PRS. The results can be used in other projects.
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