USE OF MATHEMATICAL MODELS OF AERO ELASTICITY AND ON-BOARD INFORMATION SYSTEMS FOR LOAD ASSESSMENT AIRCRAFT GLIDER AND STRUCTURE RESOURCE
DOI:
https://doi.org/10.54858/dndia.2022-18-14Keywords:
mathematical models of aeroelasticity, structure loading, overloading, elastic oscillations, stressed-deformed state, power elements, strength, resource, glider, sensorsAbstract
The article shows the development of a direction focused on the creation and anticipatory functioning of mathematical models (MM) of aircraft aeroelasticity - their mathematical backups for estimating the load of the structure, the stress-deformed state of the power elements, the strength and resource consumption of the airframe in flight using the data of on-board recorders and built-in sensors (sensors) built into the power system. MM aeroelasticity are built on the basis of "full" and simplified calculation models and allow to carry out numerical calculations regarding the operation and load of the aircraft in real time.
In the process of flight and technical operation of aviation equipment (AT), it is important to quickly determine the load spectrum of the main power elements of the glider, as well as to calculate and individual accounting of the resource consumption of the aircraft structure (aircraft). At different stages of the flight, the aircraft is subjected to various types of variable loads. This is the action of the turbulent atmosphere, which causes disturbed movement and dangerous oscillations of the structure, the occurrence of large dynamic loads during landing, etc.
Data on the load of the structure are necessary to determine critical places in the structure that are dangerous from the point of view of the formation and development of multi-focal damage, to make changes in the operation of active control systems with the aim of reducing the airframe load and the rate of aircraft resource consumption, as well as for development of the methodology for inspecting the fleet of aircraft and reliable identification of defects in critical areas of the structure and substantiation of inspection intervals.
Using the example of military transport and light aircraft, the results of the application of the MM of aeroelasticity and the numerical calculation of the load of the elastic structure on a computer are given.
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