Numerical modeling of a partial dynamic model of main landing gear engleskom jeziku: assembly for analysis of landing a fighter aircraft dynamics

Abstract

Diplomski rad usmjeren je na razvoj i validaciju simulacijskog modela podvozja borbenog zrakoplova, temeljenog na oleo-pneumatskom sustavu. Model je izrađen u alatu MATLAB i Simulink prema referentnom radu Sivakumara i suradnika. Cilj rada bio je provesti detaljnu analizu dinamike podvozja tijekom slijetanja zrakoplova, verificirati model usporedbom s referentnim rezultatima te ga prilagoditi za primjenu na borbeni zrakoplov nalik na Dassault Rafale. Rezultati simulacija pokazali su visoku razinu podudarnosti s referentnim podacima, što potvrđuje točnost matematičkog modela i njegovu sposobnost simulacije dinamičkog ponašanja podvozja. Model je zatim prilagođen specifičnim karakteristikama borbenog zrakoplova, uključujući različite parametre mase, opružne krutosti i prigušenja. Ovaj rad pruža čvrstu osnovu za daljnje istraživanje i optimizaciju podvozja, a razvijeni model može se primijeniti na druge zrakoplove sa sličnim karakteristikama podvozja, čime doprinosi povećanju sigurnosti i pouzdanosti sustava u zrakoplovstvu.Thesis focuses on the development and validation of a landing gear simulation model for a fighter aircraft, based on an oleo-pneumatic system. The model was created using MATLAB and Simulink, following the methodology outlined in the reference work by Sivakumar et al. The objective of this research was to conduct a detailed analysis of the dynamics of landing gear during aircraft landing, validate the model by comparing it with reference results, and adapt it for use on a fighter aircraft similar to the Dassault Rafale. The simulation results demonstrated a high level of agreement with the reference data, confirming the accuracy of the mathematical model and its capability to simulate the dynamic behavior of landing gear. The model was then adapted to the specific characteristics of a fighter aircraft, including variations in mass, spring stiffness, and damping parameters. This research provides a solid foundation for further exploration and optimization of landing gear systems. Moreover, the developed model can be applied to other aircraft with similar landing gear configurations, contributing to improved safety and reliability in aviation