Open AccessМАТЕМАТИЧНЕ МОДЕЛЮВАННЯ УДАРУ ПРУЖНОГО ЛІТАЛЬНОГО АПАРАТА НА ПОСАДЦІ
Author(s) -
В. М. Онищенко
Publication year - 2019
Publication title -
otkrytye informacionnye i kompʹûternye integrirovannye tehnologii
Language(s) - English
Resource type - Journals
eISSN - 2663-2411
pISSN - 2071-1077
DOI - 10.32620/oikit.2019.84.09
Subject(s) - aeroelasticity , parametric statistics , vibration , structural engineering , chassis , landing gear , computer science , nonlinear system , constructive , aerospace engineering , engineering , aerodynamics , physics , mathematics , statistics , process (computing) , quantum mechanics , operating system
The development of a direction oriented towards the creation and advanced operation of mathematical models (MM) of aircraft - their mathematical doublers on the example of calculating the impact dynamics and loading of an elastic plane on landing is shown. The relevance of such an approach in the design and operation of aircraft due to the complexity and limited capabilities of terrestrial experimental facilities and flight experiment are noted. The example of a lightweight aircraft presents the results of the application of a simplified MM and the numerical calculation of the impact dynamics on the computer and the load of the elastic construction at landing. Determination of the dynamic reaction of the aircraft and the load of the elastic structure at landing refers to the actual problem of dynamic aeroelasticity. In the article the basic equations used to construct the MM of an elastic plane with a nonlinear landing gear are given. The basic parameters that characterize the structural load are determined. The results of the calculation analysis of the impact of the aircraft are presented, extensive parametric studies have been carried out on the influence of a number of constructive and operational factors on dynamic processes, and analyzed the patterns and features of impact and loading of an elastic aircraft on landing. It is shown that the load must be determined taking into account elastic structural vibrations. Dynamic loads from elastic oscillations are significant in magnitude and, as it turns out, most often determine the strength of the glider and the chassis. It is emphasized that the condition of the application of the calculated method is the mathematical models of the operation of the aircraft and the availability of information on the aircraft – mass-inertial, rigid and aerodynamic characteristics.