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Structural model with controls of a very light airplane for numerical flutter calculations

Robert Rogólski (Faculty of Mechatronics and Aerospace, Wojskowa Akademia Techniczna im Jaroslawa Dabrowskiego, Warsaw, Poland)
Aleksander Olejnik (Faculty of Mechatronics and Aerospace, Wojskowa Akademia Techniczna im Jaroslawa Dabrowskiego, Warsaw, Poland)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 17 October 2018

Issue publication date: 19 March 2020

174

Abstract

Purpose

The finite element model developed for a new-designed aircraft was used to solve some problems of structural dynamics. The key purpose of the task was to estimate the critical flutter velocities of the light airplane by performing numerical analysis with application of MSC Software.

Design/methodology/approach

Flutter analyses processed by Nastran require application of some complex aeroelastic model integrating two separate components – structural model and aerodynamic model. These sub-models are necessary for determining stiffness, mass and aerodynamic matrices, which are involved in the flutter equation. The aircraft structural model with its non-structural masses was developed in Patran. To determine the aerodynamic coefficient matrix, some simplified aerodynamic body-panel geometries were developed. The flutter equation was solved with the PK method.

Findings

The verified aircraft model was used to determine its normal modes in the range of 0-30 Hz. Then, some critical velocities of flutter were calculated within the range of operational velocities. As there is no certainty that the computed modes are in accordance with the natural ones, some parametric calculations are recommended. Modal frequencies depend on structural parameters that are quite difficult to identify. Adopting their values from the reasonable range, it is possible to assign the range of possible frequencies. The frequencies of rudder or elevator modes are dependent on their mass moments of inertia and rigidity of controls. The critical speeds of tail flutter were calculated for various combinations of stiffness or mass values.

Practical implications

The task described here is a preliminary calculational study of normal modes and flutter vibrations. It is necessary to prove the new airplane is free from flutter to fulfil the requirement considered in the type certification process.

Originality/value

The described approach takes into account the uncertainty of results caused by the indeterminacy of selected constructional parameters.

Keywords

Acknowledgements

The material presented in this paper is thematically associated with the research project: Project Development and Construction of Ultra-Light Aircraft Technology Demonstrator as Part of a Network-Centric System of Reconnaissance and Command Support. The work was funded by the Polish National Centre for Research and Development (NCRD) and accomplished under the leadership of the MUT in years 2010-2014. Research program concerning the OSA airplane is being continued within the framework of the currently ongoing project PBS3/B6/35/2015 entitled: Increasing the Usability of the Very Light Airplane with an Innovative Aerodynamic Configuration Typical for STOL Aircraft (funded by the NCRD).

Citation

Rogólski, R. and Olejnik, A. (2018), "Structural model with controls of a very light airplane for numerical flutter calculations", Aircraft Engineering and Aerospace Technology, Vol. 92 No. 3, pp. 304-317. https://doi.org/10.1108/AEAT-01-2018-0059

Publisher

:

Emerald Publishing Limited

Copyright © 2018, Emerald Publishing Limited

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