Fuel Weight Determination of Ultralight and Very Light Helicopters at the Preliminary Design Stage

• Autorzy: Dudnik Vitaly , Karabut Victor

Identyfikatory

DOI

10.2478/tar-2022-0016

• Języki publikacji: EN

Abstrakty

EN

In recent years, a large number of one- to two-seat-type helicopters have appeared, raising the possibility to determine the dependencies inherent in these classes. Such dependencies are extremely necessary at the preliminary design stage, in particular, for determining the fuel mass. The relative mass of fuel depends on the required range and flight time of the helicopter, as well as on the characteristics of the engine and the required power of the helicopter. Based on statistical data, the article presents an approximate relation of the hourly fuel consumption of engines that small helicopters are equipped with. The additional amount of fuel required to complete missions has also been determined. General dependency of the fuel weight that can be used at the preliminary design stage is presented according to the analysis results.

Słowa kluczowe

EN

ultralight helicopter; very light helicopter; fuel consumption; preliminary design

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Transactions on Aerospace Research
• Rocznik: 2022
• Tom: Nr 3 (268)
• Strony: 48--55
• Opis fizyczny: Bibliogr. 12 poz., fot., rys., tab., wzory

Twórcy

autor

Dudnik Vitaly

• Don State Technical University, Aircraft Manufacturing Department, 344000, Rostov-on-Don, Russia

• https://orcid.org/0000-0002-5798-8019

autor

Karabut Victor

• Southern Federal University, Insitute of Radio Engineering Systems and Control, 347922, Taganrog, Russia

• https://orcid.org/0000-0002-4310-4083

Bibliografia

• [1] Proskurin Vladimir. Calculation of the Helicopter Parameters at the Preliminary Design Stage. OGU, Orenburg (2014): 200 p.
• [2] “Structure and Design of Helicopters, Mechanical Engineering.” Encyclopedia, Part 3, Book IV. Mashinostroenie, Moscow (2004): pp. 297-404.
• [3] Rand Omri and Khromov Vladimir. “Helicopter Sizing by Statistics.” American Helicopter Society 58th Annual Forum, Montreal, 2002.
• [4] Kallinderis Yannis, Vouvakos Xenakis and Menounou Penèlope. “Linear Approximations of Relations Between Preliminary Design Parameters for Utility Helicopters.” Aerospace Science and Technology Vol. 14 (2010): pp. 235-240.
• [5] Dudnik Vitaly, Karabut Victor and Lesniak Sergey. “Rotor Parameters of Small Weight Helicopters.” 46 European Rotorcraft Forum, Moscow, 2020.
• [6] Krenik Alex and Weiand Peter “Aspects on Conceptual and Preliminary Helicopter Design.” Deutscher Luft- und Raumfahrtkongress, Document 420207, 2016.
• [7] Losev Leonid, Zaitsev Vitaly and Plankovski Sergej. Ultralight Helicopter Structure. KhAI, Kharkov (2007): 374 p.
• [8] Certification Specifications for Very Light Rotorcraft CS-VLR. EASA, Cologne (2003): 91 p.
• [9] Bekanntmachung von Lufttüchtigkeitsforderungen für Ultraleichthubschrauber LTF - ULH. DFS, Braunschweig (2019): 60 p.
• [10] Grebennikov Alexandr, Losev Leonid, Timchenko Alexey and Urbanovich Vladimir. Light Helicopters Design. KhAI, Kharkov (2013): 290 p.
• [11] Bratuhin Ivan and Perelygin Sergej. Selection of the Main Parameters of the Coaxial Scheme Helicopter. MAI, Moscow (1980): 24 p.
• [12] Tishenko Marat, Nekrasov Andrej and Radin Alexej. Helicopters. The Choice of Parameters in the Design. Mashinostroenie, Moscow (1976): 368 p.

Uwagi

Opracowanie rekordu ze środków MEiN, umowa nr SONP/SP/546092/2022 w ramach programu "Społeczna odpowiedzialność nauki" - moduł: Popularyzacja nauki i promocja sportu (2022-2023).