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This work contains the results of a modern helicopter construction analysis. It includes the comparison of almost seventy rotorcraft constructions in terms of size in line with EASA requirements – large and small helicopters. The helicopters are also divided because of a mission purpose. The proposed division for large aircrafts is: transport, mult...
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... the vehicle purpose are the dimensions. The main rotor diameter of transport helicopters, according to the rotorcrafts data from [17], is on average of 20 m, however, it depends on the aircraft payload. The heavy lift helicopters have a rotor diameter of 24 m to 34 m. The biggest representative of this group of aircrafts is Mil Mi-26 helicopter (Fig. 6). The fuselage dimensions are on average of 20 m long and of 4.45 m wide. These aircrafts are usually built with two engines, however, some heavy lifts constructions are three-engine. The motors are placed within the upper part of the fuselage, above the cargo hold and crew ...
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... This article represents the fourth phase of the research program, following previous analyses of rotorcraft construction and main rotor computational fluid dynamics (CFD) using parametric modeling. The program were preceded with an rotorcraft construction analysis which results were published in [6]. The latter parts included the main rotor CFD analysis using parametric modeling and preparing the blade structure using parametrization, this work were published in [7]. ...
This work is part of a research program aimed at finding new approaches and design solutions for helicopter main rotor modelling using multidisciplinary optimization. It is the fourth stage of an individual research program that includes preliminary tasks such as parametric modelling of a single blade, CFD modelling of a full main rotor for different flight conditions, and preliminary structural modelling of a blade. The main goal of this work is to present the parametric modelling of the rotor blade body and structure as an application for complex simulation. The paper demonstrates the method of advanced analysis of the entire rotor and provides exemplary results obtained from complicated analyses. The analytical foundation for combined fluid-structure analysis is presented. The parametric design method is shown to be applicable for different blade planform shapes and various section airfoils. The blade CFD fluid domain is also prepared using the parametric method, as well as the blade’s inner structure. The simulation parameters from the previous stages of research, which serve as inputs to the FSI analysis, are outlined. These previously obtained parameters are combined and introduced into an FSI simulation to assess their compatibility and applicability. The configuration procedure of the analysis and the boundary conditions are presented. The obtained numerical results are then compared with analytical assumptions. The simulation products, which serve as inputs for further analysis, are presented with graphical representations. The time and memory consumption of the simulation are outlined. The application of the described work in an optimization loop is proposed. As a result of this research, new options for main rotor optimization are developed. The paper demonstrates some crucial possibilities of FSI analysis in the described simulation cases. The use of combined parametric modeling with fluid-structure interaction analysis for different flight conditions is presented as a new perspective for multidisciplinary design optimization of a helicopter rotor system.
... He concluded that an increase in width and angular velocity would generally result in an increase in required power at forward flight speeds. Stanislaw Kachel et al. [5] analyzed the results of the methods of modern helicopter designs. They examined the values of 70 different rotorcraft parameters in terms of EASA requirements. ...
The main rotor is the principal factor effecting helicopter performance and fuel consumption. There are many basic geometric parameters that constitutive the main rotor design. Radius and chord are among these basic geometric parameters. In this study, it is aimed to examine the effects of variation in radius and chord on required power at different flight conditions. Based on the design values of B0105 and S-76 from utility helicopter the group, the power calculations were made for the main rotor only when the radius and only the chord changed between +8% and -8%, and both parameters changed between +8% and 8%. These calculations were repeated for hover, 50 knots, 90 knots, 130 knots forward flights, and for sea level, 5000 ft, 10000 ft altitudes. With the variation of radius and chord, the cases that the maximum reductions and increases in required power were revealed. Results shows İncreasing the chord alone resulted in an increase in required power in all flight conditions. It has been observed that the combinations obtained by variation the radius and chord of maximum decrease and increase amount in the required power are different from according to the altitude, suspension condition and forward flight velocity.
... The results of the analysis showed that there is a field were rotor construction can be improved in accordance with modern combat field requirements which are dynamically changing due to fast technological improvements. The results, with charts and a comparison of parameters were published in [20]. ...
This work is the preliminary part of a research program which is aimed at finding some new methods and design solutions for helicopter main rotor multidisciplinary optimization. The task was to develop a parametric geometric model of a single-blade main rotor applicable for varied methods of numerical aerodynamic modeling. The general analytical assumptions for the parametric main rotor design were described. The description of the main rotor blade parametric design method based on Open GRIP graphical programming was presented. Then, the parametric model of a blade was used for aerodynamic models independently developed for panel method and advanced CFD solver. The results obtained from the CFD simulations and panel analysis for main rotor aerodynamics were compared and assessed using analytical calculations. The calculations and simulations for a single-blade and completed rotor were performed for different helicopter weights and rotor pitch angles. The results of different computer aerodynamic analysis environments were compared for the possibility of their application in an optimization loop. This is preliminary work that describes only a partial problem that could be used in the future as part of a comprehensive methodology for aerodynamic and structural optimization of a helicopter rotor. As an output of the research, new options for main rotor optimization are developed. The combined parametric modeling with aerodynamic analysis, as described in this paper, provide the preliminary design for a main rotor spiral, as an element of the optimization loop
