Unified Computational Scheme for the Calculation of the Influence of Acoustic Disturbance to the Aeroelastic Stability and Dynamic Response of Structure
- Paper number
IAC-06-C2.3.09
- Author
Mr. Harijono Djojodihardjo, Universitas Al Azhar Indonesia, Indonesia
- Coauthor
Mr. Irtan Safari, Indonesia
- Year
2006
- Abstract
The foundation for the development of the computational scheme for the calculation of the influence of acoustic source to the aeroelastic stability of a structure has been carried out in previous work[1][2]. The generic approach consists of three parts. The first is the formulation of the acoustic source governed by the Helmholtz equation by using boundary element approach, which then allows the calculation of the acoustic pressure on the acoustic-structure boundaries. Next the structural dynamic problem is formulated using finite element approach. The third part involves the calculation of the unsteady aerodynamic loading on the structure using generic unsteady aerodynamic computational method. A simplified yet illustrative and instuctive example has been worked out, and the computational scheme has been validated using classical results. The purpose was to develop an in-house computational scheme using MATLAB which is considered user friendly for instructional as well as further development purposes. In the present work, further refinement as stipulated in the objectives of the work has been carried out These refinement consist of the following elements: a. utilization and further refinement of the boundary element approach for the calculation of acoustic pressure on a structure due to a known acoustic source. Various refinement of the boundary elements have been carried out to arrive at most effective setting judged from computational efficiency and accuracy. b. Refinement of the finite element formulation of the dynamic structure which will be amenable for acoustic load-structural dynamic coupling. c. Utilization of further refined scheme for the unsteady aerodynamic load calculation on the dynamic structure. For this purpose examples have been worked out using Doublet Point Method and Doublet Lattice Method. The computational scheme written in MATLAB has been validated using classical results as well as NASTRAN program, and has given satisfactory results for in aircraft aeroelasticity. Using the software developed, two problems are considred: a. parametric study to investigate the influence of acoustic disturbance to dynamic structure stability due to aerodynamic effects b. parametric study to investigate the influence of acoustic disturbance on the dynamic response characteristic of space structure. Novel results are presented and compared to those obtained in earlier work carried out by the authors as well as other investigators. [1]. Harijono djojodihardjo and Eric Tendean, A Computational Technique For The Dynamics Of Structure Subject To Acoustic Excitation, IAC Paper IAC-04-IAF31.2.09, 55th International Astronautical Congress The World Space Congress-2004, 4-8 October 2004/Vancouver Canada [2]. Harijono Djojodihardjo and Irtan Safari, Further Development Of The Computational Technique For The Dynamics Of Structure Subject To Acoustic Excitation, IAC Paper IAC-04-IAF31.2.09, 56 th International Astronautical Congress, The World Space Congress-2005, 17-21 October 2005/Fukuoka Japan
- Abstract document
- Manuscript document
IAC-06-C2.3.09.pdf (🔒 authorized access only).
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