Anatolii Kretov

The paper continues the theme developed by the author of the application of sensitivity analysis of the initial mass of aircraft to design changes. In this

The purpose of this research is to improve the approach for evaluating of new design solutions based on sensitivity analysis of takeoff mass (SFM) to initial changes in the basic project. The approach is based on the changes assessment in maximum takeoff mass of a developed project or an already existed basic variant of an aircraft with local design (project) changes, including the aerodynamic ones, that ensure the developing of a more advanced aircraft. In comparison with the existed known approaches based on the mass growth factors, which were considered constant, the proposed approach takes into account more exactly the dependence of the takeoff mass on the initial local change in mass in terms of their functional purpose, as well as the aerodynamic characteristics. This approach allows the designer to calculate more precisely the final maximum takeoff mass changes in the early (preliminary) stages of conceptual design when looking for new design solutions. On numerical examples, carried out on the examples of transport category airplanes, a significant dependence of the wing aspect ratio influence on fuel efficiency is shown. The considered approach using SFM with semi-analytical aerodynamic analysis combination is simple, reliable and convenient in the analysis and synthesis of a new project for the design process based on the base variant.

The application of the wings with a high aspect ratio for future-oriented transport category aircraft is being considered. Such a solution makes it possible to increase fuel efficiency by reducing induced drag. This goal is achieved by increasing the wingspan, when the wings made of composite materials are used. The wings of an increased span complicate the arrangement of the aircraft in the existing infrastructure of airports. To eliminate this drawback, the application of folding wingtips was considered. The effect of such a folding device on the mass of the airplane was estimated. The approach to estimating the mass of composite structures with folding wingtips has been proposed. A conceptual assessment of the Boeing 737 and A-320 aircraft with higher aspect ratio composite wings was performed.

The impact of design changes on the basic model of the helicopter is estimated based on the sensitivity analysis of the take-off mass in order to obtain a

Based on the analysis of the sensitivity of mass to the initial change of parameters, an assessment is made of the transition from the traditional layout o

A mass-economic assessment of replacement of aviation kerosene with cryogenic fuel is carried out based on the analysis of the mass sensitivity to the init

The work, dedicated to the blessed memory of Vladimir Chizhukhin, deals with the problem of rescuing the blocks of carrier rockets for their subsequent use. The priority method is the use of aerospace parachute systems (ASPS), which are the lightest of all possible rescue systems. The possibility of using parachutes at space altitudes has been proven by the longterm practice of using them in M-100 meteorological rockets. Based on specific examples, numerical studies have been carried out on the possibility of using such a system, showing its great capabilities in combination with helicopter pick-up at the final stage of landing or with a rocket-dynamic soft-landing system.

Purpose: The purpose of this work is to further develop the methodology for calculating the aircraft take-off mass and its main functional components for the conceptual analysis and synthesis of new projects. Design/methodology/approach: The method is based on the assessment of changes in the take-off gross mass (TOGM) of the already developed project or already existing a basic version of the aircraft when making local mass changes for its modification or for the numerical researches to create a more advanced project. The method is based on the “sensitivity factors of mass” (SFM) of aircraft, which represents the ratio of TOGM to initial (local) mass changes of its main functional components. The method of analytical refined calculation of SFM for the initial mass change and the main aerodynamic characteristics is given. Findings: In comparison with the long-known method based on weight (mass) growth factors, which were considered constant, this method takes into account the dependence from the value of the initial local mass change and its functional purpose. Practical implications: This method allows the designer to calculate more strictly the final changes in the TOGM on the initial stages of conceptual design when finding new project solutions. Numerical calculations are given on the example of passenger aircraft. The dependence of SFM and TOGM and its functional masses on the value of the initial change of the structure mass are shown. This method is used in the educational process at the college of Aerospace Engineering in the Aircraft Design department. Originality/value: The considered method based on SFM is simple and convenient and more accurate for conducting project research on many project parameters when analyzing and synthesizing a new project.

Optimization methods providing maximum strength and rigidity of the thin-walled structure are considered. A critical overview of the works related to the optimization including the heated design is done. To optimize for several cases of loading, a minimization of functional is applied, which is the sum of the total potential strain energies for each case of loading. The optimization process begins with the initial basic structure, which includes all possible variants of the location of the power elements. In the optimization process, inefficient elements are eliminated by minimizing their rigidity. Numerical optimization studies on the example of truss construction are carried out.