Algorithm for solving problems of aerodynamics, heat transfer and strength using an interdisciplinary principle in the study of icing of contact elements of an aircraft door


Аuthors

Mikhailov D. A.1*, Pykhalov A. A.1, 2**, Zotov I. N.1***

1. Irkutsk National Research Technical University, 83, Lermontov str., Irkutsk, 664074, Russia
2. Irkutsk State Transport University (IrGUPS), 15, Chernyshevsky str., Irkutsk, 664074, Russia

*e-mail: d.mikhaylov.835@yandex.ru
**e-mail: pikhalov_aa@irgups.ru
***e-mail: zegor-2008@yandex.ru

Abstract

The paper is devoted to the application of interdisciplinary analysis technology in relation to civil aircraft, where the lives of several hundred people depend on the functionality of each structural unit. The results of the conjugate mathematical analysis of individual airframe elements reflect the picture of the processes occurring in them, which allows us to assess the safety of aircraft operation throughout the flight, including taxiing after landing. The object of study in the paper is the passenger door of the modern MS-21 airliner, which will be supplied to the Russian airline market in 2025. The door is part of the fuselage mechanization and structurally represents an opening connected to the fuselage panel, as well as a flap that contacts the opening in the closed position using a rubber seal. Since the passenger cabin and the airspace at cruising altitude are separated by a single part made of a hyperelastic material, which is subject to high requirements in aviation, special attention is paid to the study of its stress-strain state.

The interdisciplinary analysis is presented by solving conjugate problems: gas dynamics, heat transfer, strength and icing. The study is based on a numerical solution using the finite element method, when using which the specified parameters of the finite mesh and boundary conditions provide high accuracy of results, which was proven earlier in the study of these processes using the example of an elementary body with known analytical solutions.

Since the design documentation for the body under consideration does not contain the configuration of the part in the deformed state, the beginning of the conjugate analysis is obtaining the state of the seal in airfield conditions, which allows for further study of the structure. At this stage, the experimental research work on determining the physical and mechanical characteristics of the material was previously carried out with their subsequent verification by a numerical method using finite elements.

At the next stage, a gas-dynamic calculation of the body under study is presented, as a result of which the pressure and temperature distribution on the surfaces of the structural elements is obtained. Boundary conditions for solving the heat conductivity problem are obtained with respect to this calculation.

At the next stage, as a result of studying the thermal state of the body and external forces under the influence of the air flow, boundary conditions are obtained for conducting a strength analysis that fully reflects the stress-strain state of the structure.

The final stage is the numerical modeling of icing of the structure under consideration, taking into account the deformations and other parameters obtained at the previous stages. As a result, it was revealed that under the flight conditions of modern engines and aircraft, intensive ice build-up is observed in the area of the junction of the sash and the opening, as a result of which the functionality of this aircraft unit may be lost.

Keywords:

aerodrome safety, conjugate analysis of fuselage mechanization, stress-strain state of elastomeric bodies, icing of elastomeric bodies, conjugate problem algorithm

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