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Evaluation of the required ground power of a ground - based system for support of the aircraft safe take - off and landing

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EN
Abstrakty
EN
Among the most important problems faced by the air transport today there can be mentioned some negative influences of aircraft and airports on the environment and the increasing costs of air transport. One of the possibilities to improve the situation is to work out innovative solutions aimed at decreasing of the aircraft pollution and improving the transport effectiveness. Among the most innovative ideas is the use of magnetic levitation to aid the take-off and landing of the transport aircraft. The use of the aiding system will bring a lot of benefits, however, regarding its innovative character and the problems connected with it, the idea can have been realized in a couple of years or even decades. The aim of this work was to carry out the analysis of the change to the required thrust of the transport aircraft in the take-off, landing and cruise using the system of magnetic levitation. Magnetic levitation or magnetic suspension is a method by which a body floats due to a special quality of magnets. The generated electromagnetic force is used to balance the weight of the object. The current work describes the ways of determining the weights of the main systems of the aircraft with classical construction solutions where the weight of the whole aircraft is estimated on the basis of the statistical methods. It allows determining the weights of all main systems of the aircraft and verifying the results using the known examples. Thanks to this approach, it could be possible to determine the modified aircraft weight more thoroughly, adding the changes in weights of the modified systems.
Twórcy
autor
  • Rzeszow University of Technology Department of Aircrafts and Aircraft Engines Powstancow Warszawy Street 12, 35-959 Rzeszow, Poland tel.: +48 17 8651604, fax: +48 17 8543116, andrzej.majka@prz.edu.pl
Bibliografia
  • [1] Anderson, J. D. Jr,. Aircraft performance and design, McGraw-Hill, International Editions 1999.
  • [2] Badjagin, A. A., Eger, S. M., Miszin, W. F., Skljanskij, F. I., Fomin, N. A., Aircraft design, (in Russian), Maszinostrojenie, Moscow 1972.
  • [3] EUROCONTROL, Performance Review Report 2010, European Organisation for the Safety of Air Navigation, Brussels, Belgium 2011.
  • [4] Filippone, A., Flight Performance of Fixed and Rotary Wing Aircraft, ELSEVIER, Great Britain 2006.
  • [5] McCormick, B. W., Aerodynamics, aeronautics and flight mechanics, Wiley, New York 1994.
  • [6] Raymer, D. P., Aircraft Design: A Conceptual Approach, AIAA Education Series, Washington, D.C. 1992.
  • [7] Rohacs, J., Rohacs, D., Jankovics, I., Possible Solutions to Take-Off and Land an Aircraft, Deliverable D2.4. Integrated Ground and on-Board system for Support of the Aircraft Safe Take-off and Landing – GABRIEL, EU project number 284884, Budapest 2012.
  • [8] Roskam, J., Airplane Design. Part V: Component Weight Estimation, Roskam Aviation and Engineering Corporation, Ottawa, Kansas 1985.
  • [9] Roskam, J., Airplane Design. Part VI: Preliminary Calculation of Aerodynamic, Thrust and Power Characteristics, Roskam Aviation and Engineering Corporation, Ottawa, Kansas 1987.
  • [10] Torenbeek E., Synthesis of Subsonic Airplane Design, Delft Iniversity Press, Rotterdam 1976.
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-article-BUJ5-0049-0003
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