Share:


Balancing an aircraft with symmetrically deflected split elevator and rudder during short landing run

    Mohammed Ba Zuhair Affiliation

Abstract

This article investigates methods for balancing aircraft during short straight-line landing run realized by employing split rudder and elevator as air-brakes after touchdown. For standard atmospheric and runway conditions, directional and longitudinal balance equations for aircraft of conventional configuration such as Il-86 are presented. Methods depend on operational and mechanical approaches, where the first requires manual or automatic trim of shortly peaking small pitching, yawing, and rolling moments using dynamic forces while the second suggest some re-design of elevator and rudder control channels to limit deflection angles. The paper describes in detail each method disadvantages and suggests the adoption of automatic operational approach due to less required system modifications and piloting skills.

Keyword : air-brake, short landing run, take-off and landing performance, split elevator and rudder, two sectioned rudder, two sectioned elevator

How to Cite
Ba Zuhair, M. (2019). Balancing an aircraft with symmetrically deflected split elevator and rudder during short landing run. Aviation, 23(1), 23-30. https://doi.org/10.3846/aviation.2019.10301
Published in Issue
May 23, 2019
Abstract Views
821
PDF Downloads
716
Creative Commons License

This work is licensed under a Creative Commons Attribution 4.0 International License.

References

Alyamovsky, A. A. (2012). SolidWorks Simulation, Kak reshat prakticheskie zadachi [SolidWorks Simulation. How to solve practical problems]. Saint Petersburg: Saint Petersburg Publisher.

Ba Zuhair, M. A. (2018). R.U. Patent No. 2,668,000. Moscow: R.U. Patent and Trademark Office.

Bazuhair, M. A. (2018). A technique for shortening landing run distance of an aircraft by symmetrical deflection of split elevator and rudder. Russian Aeronautics, 61(2), 187-193. https://doi.org/10.3103/S106879981802006X

Bekhtir, V. P. (1991). Prakticheskaja ajerodinamika samoleta Il-86 [Il-86 aircraft performance]. Ulyanovsk: Center of Civil Aviation and Council for Mutual Economic Assistance.

Buchkarev, A., et al. (1985). Aeromechanika samoleta [Aircraft aeromechanics]. Moscow: Mashinostroenie.

Dassualt-Systems. (2015). Flow Simulation 2016 Online user’s guide. SOLIDWORKS-2016. Paris: Dassualt Systems. Retrieved from https://www.faa.gov/documentLibrary/media/Advisory_Circular/AC_25-7D.pdf

Federal Aviation Administration. (2017). Approaches and landings (Chapter 8). In Airplane Flying Handbook, FAA-H-80833B. Retrieved from https://www.faa.gov/regulations_policies/handbooks_manuals/aviation/airplane_handbook/media/10_afh_ch8.pdf

Federal Aviation Administration. (2018). Circular 25-7D- Flight Test Guide for Certification of Transport Category Airplanes. Retrieved from https://www.faa.gov/documentLibrary/media/Advisory_Circular/AC_25-7D.pdf

Federal Aviation Administration. (1997). Rules and Regulations: Sino Swearingen Model SJ30–2 Airplane. Retrieved from https://www.govinfo.gov/content/pkg/FR-1997-10-31/pdf/97-28937.pdf

Jung, U. S. (2012). Alternative air brake concepts for transport aircraft steep approach (PhD Thesis). Munich Technical University, Munich, Germany.

Liebeck, R. H. (2004). Design of the blended wing body subsonic transport. Journal of Aircraft, 41(1), 10-25. https://doi.org/10.2514/1.9084

Mertol, B. A. (2008). Patent application WIPO/2008/151760. Lifting wing with adjustable spoiler.

Mkhitaryan, A. M., et al. (2012). Dinamika poleta [Eng. trans. Flight Mechanics]. Moscow: EKOLIT publisher.

NASA. (2007). Landing the space shuttle orbiter. NASA. Retrieved from http://www.nasa.gov/pdf/167415main_LandingatKSC-08.pdf