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A Technique for Shortening Landing Run Distance of an Aircraft by Symmetrical Deflection of Split Elevator and Rudder

  • Flight Dynamics and Control of Flight Vehicles
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Abstract

In this work, we investigate an application of symmetrical deflection of the split elevators and rudder up to 45 degrees to function as air-brakes during landing run for shortening its distance. A computational analysis for the landing run under standard atmospheric conditions is conducted. The effect of the proposed solution on the aircraft structure and performance was studied.

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Authors and Affiliations

  1. Tupolev Kazan National Research Technical University, ul. Karla Marksa 10, Kazan, 420111, Russia

    M. A. Bazuhair

Authors
  1. M. A. Bazuhair
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Correspondence to M. A. Bazuhair.

Additional information

Original Russian Text © M.A. Bazuhair, 2018, published in Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2018, No. 2, pp. 39–44.

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Bazuhair, M.A. A Technique for Shortening Landing Run Distance of an Aircraft by Symmetrical Deflection of Split Elevator and Rudder. Russ. Aeronaut. 61, 187–193 (2018). https://doi.org/10.3103/S106879981802006X

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  • DOI: https://doi.org/10.3103/S106879981802006X

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