Substantiation of choosing rational appearance of nose of aircraft with the use of mathematical modeling

Barabanov, Alexander; Serebryansky, Sergey

doi:10.1007/s42401-020-00079-2

Cited by 13 publications

(6 citation statements)

References 5 publications

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“…Power: 2 engines of 200 hp, total 400 hp (294 kW); Number of passengers: 5 passengers, mail, cargo (total 500-700 kg) Flight range, cruising and maximum flight speeds are specified in the source data at the first stages of the life-cycle [8,9], since these characteristics are the main criteria.…”

Section: Initial Datamentioning

confidence: 99%

Investigation of the feasibility of using wing struts and non-retractable landing gear struts on a light multi-purpose aircraft

et al. 2023

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In this paper, we consider a method for determining the feasibility of using a wing strut and non-retractable landing gear on a light multi-purpose aircraft. In a certain range of cruising speeds and flight ranges, it is advisable to use non-retractable landing gear and wing strut. With an increase in cruising speed and flight range, these engineering solutions must be abandoned to improve aerodynamic characteristics. The dependencies obtained in this work make it possible to make decisions on the use of a wing strut and non-retractable landing gear at the early design stages. To obtain aerodynamic characteristics in the Siemens NX program, a three-dimensional model of a light multi-purpose aircraft was created and an aerodynamic experiment was performed in the FloEFD program. Then the calculation of flight performance was carried out. As a result of the study, the dependence of the speed up to which it is advisable to use the undercarriage strut and fixed landing gear on the flight range for a light multi-purpose aircraft weighing 2000 kg was obtained. When designing an aircraft, it is necessary to make decisions about the use of one or another engineering solution, which, on the one hand, has a positive effect on aerodynamics and negatively on the weight of the aircraft, and vice versa. In this article, using the example of a wing strut and fixed landing gear in the first version of the aircraft, and a cantilever wing and retractable landing gear in the second version, a model for solving such a problem is shown.

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Section: Initial Datamentioning

confidence: 99%

Investigation of the feasibility of using wing struts and non-retractable landing gear struts on a light multi-purpose aircraft

et al. 2023

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“…The density of the heat flux of radiation from the surface of the aircraft is determined by the Stefan-Boltzmann law according to the formula (5).…”

Section: Problem Statementmentioning

confidence: 99%

“…Secondly, heating of the structure can lead to the occurrence of temperature stresses in its elements and elements of aircraft systems [4]. Thirdly, the creep phenomenon may occur, that is, continuous plastic deformation of structural elements under constant load [5].…”

Section: Problem Statementmentioning

confidence: 99%

On the issue of reducing the temperature heating of the airframe structure of a supersonic aircraft

et al. 2023

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In this paper, the influence of heating of the structure on its strength is considered in three aspects: a decrease in the mechanical characteristics of structural materials at high temperature, heating of the structure can lead to temperature stresses in its elements and elements of aircraft systems and the occurrence of the phenomenon of creep of structural materials - continuous plastic deformation of structural elements under constant load. There are several options for reducing heat flows due to modification of the basic aerodynamic layout: increasing the sweep angles of the bearing surfaces and the radius of the wing tip and the front edges of the inflows, reducing the area of the washed surface due to the “flattening” of the initial aerodynamic contours. Each of the considered existing and promising methods of thermal protection separately will not allow to fully develop thermal protection of promising reusable supersonic aircraft. A comprehensive approach is needed. At the same time, it is necessary to consider both the replacement of structural materials of panels and cladding with titanium or steel alloys, as well as design solutions for the use of fuel lines.

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“…The existing trends in the development of aviation technology show a constant increase in the flight speeds of modern aircraft, both cruising and marginal. This leads to the emergence of new tasks requiring solutions at various stages of the life cycle, taking into account the assessment of their cost and the possibility of cost optimization [1][2][3]. The most important of them are the tasks of modeling working conditions [4], the development of new structural materials, design optimization [5], the organization of conditions for their production and tests [6], as well as supply and quality management of all processes.…”

Section: Introductionmentioning

confidence: 99%

Evaluation of the possibility of developing and manufacturing integral composite structures for airframe elements

et al. 2023

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Nowadays, the degree of structural integrity is as important as the specific load bearing capacity. An integral product can be called a product obtained by combining structural elements of different configurations and functional purposes into a single object that does not contain joints. The concept of “integral”, obviously, is synonymous with the concept of “monolithic”. However, the word “monolithic” is traditionally identified with a massive structure, in which all fragments have the same order of measurement. The very concept of “degree of integration” is very conditional, since now there is no clear methodology for its assessment in quantitative terms. Issues related to the design, manufacture and operation of such products should be addressed in a comprehensive manner based on design solutions, technological capabilities, as well as data obtained as a result of strength calculations. In this paper strength calculations were made for metal and composite panels. Besides, composite panel has integral design. Production specifics of integral composite structures as well as advantages and disadvantages.

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Substantiation of choosing rational appearance of nose of aircraft with the use of mathematical modeling

Cited by 13 publications

References 5 publications

Investigation of the feasibility of using wing struts and non-retractable landing gear struts on a light multi-purpose aircraft

Investigation of the feasibility of using wing struts and non-retractable landing gear struts on a light multi-purpose aircraft

On the issue of reducing the temperature heating of the airframe structure of a supersonic aircraft

Evaluation of the possibility of developing and manufacturing integral composite structures for airframe elements

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