LAYOUT GENERATOR OF SMALL SIZED UNMANNED AERIAL VEHICLE

Developing quick aerodynamic design method of small unmanned aerial vehicle based on artificial neural webs technology requires a rich database used for creating, learning and testing algorythms. This database must be significantly larger than the number of existing vehicles, that's why creating a layout generator is important. On the first stage the database was increased by varying the parameters of the layout mathematical model in the accepted range. The layout generator is an artificial neural web trained on the rich database of unmanned aerial vehicles layouts in the frames of the simplified mathematical model. The important element in creating a new layout is the selection algorithm applied to the neural network output.The initial number of layouts was equal to 25. The simplified mathematical model describes the unmanned aerial vehicle layouts with 50 parameters. The layout generator forms an input file for the CFD code, which dimension is of the order of several thousands. The CFD codes BLWF and VISTRAN were chosen for this task. They add to each layout theinformation about its aerodynamic characteristics. Selection of the database was done into two levels. At first it was im-plemented on the layout generator output. Then on output vector after the CFD calculation. The selected databaser was used for creating an artificial neural networks number of which were equal to the number of aerodynamic coefficients. The algorithm was built in MATLAB and has convenient interface, which can be used for design process.

aircraft layout, small unmanned aircraft vehicle, artificial neural network, computational fluid dynamics, artificial intelligence

1. Dorofeev E.A., Romanov V.V., Sviridenko Yu.N. Application of Neural Networks Technology to Aerodynamic Problems. International Symposium on Aeronautical Sciences near Aviation Technologies of the XXI century, Flight Safety as a Pledge of Success. Zhukovsky, Russia, 17–22 August 1999.

2. Kuleshov A.P. Tehnologija bystrogo vychislenija harakteristik slozhnyh tehnicheskih obektov [Quick calculation technology of complex technical objects]. Informatsionnye tekhnologii [Information Technologies], 2006, no. 3, pp. 17–22. (in Russian)

3. Dorofeev Ye.А., Sviridenko Yu.N. Primenenie iskusstvennyh nejronnyh setej v zadachah ajerodinamicheskogo proektirovanija i opredelenija harakteristik letatel'nyh apparatov [Application artificial neural networks for aerodynamic design and estimating aircraft aerodynamic characteristics]. Trudy TsAGI [Papers of TsAGI], 2002, no. 2655, pp. 156–159. (in Russian)

4. Vyshinsky V.V., Dorofeev Ye.А., Sviridenko Yu.N. Fast aerodynamic design technologies. ICAS 2010 CD-ROM proceedings. ISBN 978-0-9565333-0-2. ICAS 2010-2.7.1. ID19. Pp. 1–9. 27th Congress of the international council of the aeronautical sciences 19–24 September 2010. Nice. France.

5. Vyshinsky V.V., Kislovskiy A.O., Kolchev S.A. Uproshchennaya matematicheskaya model'' komponovki malorazmernogo letatel'nogo apparata [Simplified mathematical model of small sized unmanned aircraft vehicle layout]. Nauchnyi Vestnik MGTU GA [Scientific Bulletin of MSTUCA], 2016, vol. 20, no. 1, pp. 84–92. (in Russian)

6. Vyshinsky V.V., Sudakov G.G. Primenenie chislennyh metodov v zadachah ajerodinamicheskogo proektirovanija [Application computational methods in aerodynamic design]. TsAGI. 2007. 142 p. (in Russian)

7. Kovalev V.E., Karas O.V. Computation of a transonic airfoil flow considering viscous effects and thin separated regions. La Recherche. Aérospatiale, 1991, No. 1.

8. Kovalev V.E., Karas O.V. Calcul de l’écoulement transsonique autour d’une configuration aile-plus-fuselage compte tenu des effects visqueux et d’une région décollée mince. La Recherche. Aérospatiale. 1994. No. 1. Pp. 23–38.

9. Volkov А.V., Liapunov S.V. Metod rascheta vjazkogo otryvnogo obtekanija sistem krylovyh profilej [Calculation method for viscose separated flows around system of wing airfoils]. TsAGI Scientific Notes, 1998, vol. XXIX, no. 3–4, pp. 49–63. (in Russian)

10. Vyshinsky V.V. Vlijanie stepeni turbulentnosti nabegajushhego potoka i sherohovatosti poverhnosti na polozhenie i protjazhennost' oblasti perehoda pogranichnogo sloja na kryle i fjuzeljazhe [Influence of the turbulence level of the flow and surface roughness on the location of the boundary layer laminar-turbulent transition region on the wing and fuselage]. Trudy TsAGI [Papers of TsAGI], 1994, no. 2560, pp. 1–28. (in Russian)

11. Vyshinsky V.V., Sviridenko Yu.N. Primenenie tehnologii bystrogo vychislenija harakteristik slozhnyh tehnicheskih obektov dlja rascheta ajerodinamicheskih harakteristik samoleta [Application of quick calculations technology for estimating aircraft aerodynamic characteristics]. Informatsionnye tekhnologii [Information Technologies], 2006, no. 3, pp. 12–17. (ISSN 1684-6400). (in Russian)