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Experimental Research of Tandem-Scheme UAV Model Aerodynamic Characteristics

Treść / Zawartość
Identyfikatory
Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
Tandem-wing aerodynamic scheme became widespread for tube launch UAV due to possibility of required flight performance realization under tight dimension constraints. In this work results of wind tunnel weight and visual tests of UAV model with wingspans about 1 m are presented. Model aerodynamic characteristics were defined by six-component wind tunnel balance at Mach number 0.075 and Reynolds number 187 000 calculated for one wing chord of 0.11 m. Model stagger (390, 490, 590 mm), rear wing dihedral angle (0°, -5°, -9°), forward-to-rear wingspan ratio (0.67; 0.9; 0.92; 1.24) were variable. It was determined that model is longitudinal and directional static stable, has high maximal lift-drag ratio (in range from 10.6 to 13.7) and acceptable maximal lift coefficient without flaps (from 1.05 to 1.09) and critical angle of attack (from 15.1 to 16.4°). Stagger increasing leads to zero or positive maximal lift-drag ratio increasing. If forward wing span is larger than rear wing span than stagger increasing is more effective with zero dihedral angle. If rear wing span is larger than forward wing span than stagger increasing is more effective with negative dihedral angle.
Rocznik
Strony
63--75
Opis fizyczny
Bibliogr. 10 poz., fot., schem., tab., wykr., wzory
Twórcy
autor
  • Experimental Design Office of General Aviation, Petropavlivska Borschagivka, „Chayka” urochishche, Kyevo-Svyatoshyn distr., Kyiv reg., Ukraine
  • Antonov Aeronautical Scientific-Technical Complex, 1, Akademika Tupoleva str., Kyiv, Ukraine
autor
  • Faculty of Aviation and Space Systems, National Technical University of Ukraine “Kyiv Polytechnic Institute”, Peremogy av., 37, build. 28, Kyiv, Ukraine
Bibliografia
  • [1] Danyk Yu. H. (2008). Bezpilotni lital’ni aparaty: oznachennya. Klasyfikatsiya, stan ta perspektyvy rozvytku i vykorystannya. Kosmichna nauka i tekhnologiya, 1, 30–43.
  • [2] Ylyushko V. M., Mytrakhovych M. M., Samkov A. V. , Sylkov V. Y. , Solovev O. V. , Strelnykov V. Y. (2009). Bespilotnye letatel’nye apparaty: Metodiki priblizhennykh raschetov osnovnykh parametrov i kharakteristik. – K.: TsNYY VVT VS Ukrainy.
  • [3] Zbrutskyy O. V., Masko O. M. , Sukhov V. V. (2012)/ Bezpilotni lital’ni aparaty konteynernogo startu: suchasnyy stan i napryamky doslidzhen’. Visnyk MMI, 64, 63–66.
  • [4] Kryvokhatko I. S. (2013). Doslidzhennya vplyvu kuta poperechnoho v kryla na aerodynamichni kharakterystyky lital’noho aparatu skhemy «tandem». Mehanika giroskopichnyh system: naukovo-tehnichnyy zbirnyk, 26, 90–101.
  • [5] Sutuhyn l. Y. (1945). Osnovy proektirovaniya samoletov. – M. : Oborongiz.
  • [6] Braybrook, R (2005, June) from scepticism to Sine Quan Non. Retrieved May 09, 2014, from http://www.thefreelibrary.com/from+scepticism+to+Sine+Quan+Non.-a0133864767
  • [7] Shakhov V. H. (1984). Aerodinamicheskie usovershenstvovaniya i skhemy letatel’nykh apparatov. – Kuybyshev, Kuybyshevskiy aviatsionniy institut im. S. P. Koroleva.
  • [8] Yur’ev B. N. (1938). Eksperimental’naya aerodinamika. – Chast’ 2. Induktivnoe soprotivlenie. – M. : NKOP SSSR.
  • [9] Kryvokhatko I. S. (2013). Analiz aerodynamiky malogo bezpilotnogo lital’nogo aparatu z teleskopichnym krylom. Voprosy proektirovaniya i proizvodstva konstruktsiy letatel’nykh apparatov. Sborn. nauch. trud. NAU im. Zhukovskogo «KhAI», 3 (75), 107–116.
  • [10] Vitaliy V. Sukhov, Illia S. Kryvokhatko. (2013). Experimental Investigation Of Aerodynamic Performance Of a Small UAV With a Telescopic Wing . IEEE Ukraine Section Joint SP. AES Chapter. 17–20. dOI: 10.1109/APUAVD.2013.6705272
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-525b20e8-75da-4668-b47a-dcd404a90660
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