Affiliation:
1. Institut Teknologi Sepuluh Nopember (ITS)
Abstract
This paper investigates the result of normal modes study on half wing structure of N219 aircraft. The analysis was completed using computational method with stick model for wing structure. A short mathematical review of the normal mode study is investigated in this paper. The study was completed for three cases of flight: zero fuel, minimum fuel and maximum fuel. The results of study, i.e., natural frequencies and mode shapes, are shown here. The results will be used for further dynamic study to analyze the flutter speed of N219 aircraft. The result comparison shows that for the same normal mode input parameters, each three cases have different number of mode shapes and different frequency value. The increments of natural frequencies between full fuel to minimum fuel is 2.5% and minimum fuel to zero fuel is 2.8%.
Publisher
Trans Tech Publications Ltd
Reference19 articles.
1. C.S.A. M.R.S. a. L.G.R. Follador, Comparison of In-Flight Measured and Computed Aeroelastic Damping: Modal Identification Procedures and Modelling Approaches,, Journal Aerospace Technology Management, pp.163-177, (2016).
2. A.S.C. a. A.C. Marta, Aeroelastic Analysis of Aircraft Wings,, Congresso de Metods Numerios em Engenharia 2015, (2015).
3. J. R. Wright and J. E. Cooper, Introduction to Aircraft Aeroelasticity and Loads, Liverpool: John Wiley & Sons, Ltd, (2007).
4. J. Njuguna, Flutter Prediction, Suppression and Control in Aircraft Composite Wings as a Design Prerequisite,, Structural Control and Health Monitoring, vol. 14, no. 5, pp.715-758, (2007).
5. W. Chajec, Flutter Calculation Based on GVT-Results and Theoretical Mass Model,, Journal Aviation, vol. 13, no. 4, pp.122-129, (2010).