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Content available Designing process of landing gear in 3D CAD program
EN
This article presents selected issues related to the design methodology of the landing gear during the construction process. The 3D modelling of the landing gear nowadays is very popular method, which simplifies the process and reduces the costs of the prototype. The author used the designing program Solid Edge ST 7. The concepts and phases of designing will be shown in this elaboration. Readers can see the problems resolved by designers and this is showing the scale of designing challenges. The landing gear consist of many parts and every of this parts needs to be design to meet the requirements of construction. Only experienced designers can effort to design landing gear because they have to acquire specific knowledge. The aim of the paper is to discuss design process from the very beginning first steps to the final version of the landing gear. All of different factors like weight, durability, resistance of the weather are taken into account when designing a prototype of the landing gear as well as economical factor of the design. It is also necessary to verify the design during its creation using experimental and laboratory test data from other similar designs. The article also subscribes some methods, which help designer to find the proper solution. The presented landing gear was designed by Landing Gear Laboratory team Institute of Aviation.
EN
Dynamic analyses of a transport aircraft landing gear are conducted to determine the effort of such a complex system and provide capabilities to predict their behaviour under hazardous conditions. This kind of investigation with the use of numerical methods implementation is much easier and less expensive than stand tests. Various 3D models of the landing gear part are defined for the multistage static FE analysis. A complete system of the main landing gear was mapped as a deformable 3D numerical model for dynamic analysis with the use of LS-Dyna code. In this 3D deformable FE model, developed in a drop test simulation, the following matters were taken into consideration: contact problems between collaborating elements, the phenomena of energy absorption by a gas-liquid damper placed in the landing gear and the response of the landing gear during the touchdown of a flexible wheel with the ground. The results of numerical analyses for the selected drop tests and the results from the experiments carried out on a real landing gear were used for verification of FE models and a methodology of the landing gear dynamics analysis. The results obtained from the various simulations of the touchdown have proved the effectiveness of the 3D numerical model and how many problems can be solved in the course of only one numerical run, e.g. geometric and material nonlinearities, a question of contact between the mating components, investigation of the landing gear kinematics, investigation of the energy dissipation problem in the whole system and the stresses influence on the structure behaviour, which can appear in some elements due to overload.
PL
Podwozia lotnicze ze względu na złożoność konstrukcji, zmienność warunków pracy, różnorodność zjawisk towarzyszących ich eksploatacji i jednocześnie występowanie ekstremalnych obciążeń, badane są najczęściej na modelach uproszczonych. W pracy zaproponowano model odkształcalny 3D kompletnego układu podwozia głównego, który docelowo zastosowany będzie do analizy wpływu postępującego procesu zniszczenia jednego elementu na wytężenie kompletnego podwozia. Rezultaty otrzymane z przeprowadzonej symulacji pokazały jak bardzo efektywna jest analiza z zastosowaniem zbudowanego modelu 3D kompletnego układu podwozia i jak istotne zagadnienia są rozwiązywane metodą symulacji numerycznej tj. problem nieliniowości geometrycznych i materiałowych, zagadnienie kontaktu pomiędzy współpracującymi elementami, zbadanie kinematyki podwozia oraz zbadanie problemu dyssypacji energii w całym układzie.
EN
Results gained from the simulation have proved how effective the 3D numerical model is and how many problems can be solved in the course of only one numerical run, e.g. the geometric and material non-linearities, the question of contact between mating components, investigation into kinematics of the landing gear and the checking of possible failure influence on the structure behaviour, which can appear in some elements due to overload. The major advantage of the presented numerical method is applicability thereof to landing gear examination with artificially introduced flaws, what is impossible to be performed with other methods, including experimental testing work.
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