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首页> 外文会议>56th International Astronautical Congress 2005 vol.6 >FURTHER DEVELOPMENT OF THE COMPUTATIONAL TECHNIQUE FOR DYNAMICS OF STRUCTURE SUBJECTED TO ACOUSTIC EXCITATION
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FURTHER DEVELOPMENT OF THE COMPUTATIONAL TECHNIQUE FOR DYNAMICS OF STRUCTURE SUBJECTED TO ACOUSTIC EXCITATION

机译：声激励作用下结构动力学计算技术的进一步发展

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In a previous study, the influence of acoustic source, along with aerodynamic excitations, to the dynamic of structures, is addressed. The acoustic source excitation is formulated using boundary element formulation of the governing Helmholtz equation for the acoustic wave propagation, and the acoustic loading on the structure is calculated. Then the loading is superposed to the aerodynamic loading on the structure, and the structural dynamic problem associated with acoustic and aerodynamic excitation is worked out following the standard procedure in aeroelasticity. The acoustic-structural coupling is formulated using coupled BEM/FEM techniques. Hence the acousto-aeroelastic problem will be formulated as the extension of the BEM/FEM coupling with the structural part incorporates the aerodynamic terms. The acoustic loading on the structure is calculated on the part L of the boundary of the acoustic domain Ω, which coincides with the structural surface as defined by the problem. In the specific case considered, this boundary is similar to the surface on the structure, at which the aerodynamic force is acting. A particular example being dealt with is the coupled acoustically modified aeroelastic instability problem, where the acoustic terms on the right hand side is assumed to be an isolated monopole or quadrupole acoustic source. The applicability of the principles of superposition is assumed, and the pressure field due to the acoustic wave propagation is incorporated as excitation force field in the Structural Dynamic equation of the structure. The solution to this equation has been reworked for the coupled unsteady aerodynamic and acoustic excitation in the aeroelastic instability problem. A simplified version uses classical lumped mass system for the structural model and classical unsteady aerodynamics using Theodorsen approach. Each of the generic problem of aeroelastic instability and acoustic excitation is validated. Parametric study is then carried out to look into the effect of the location, strength and frequency of the acoustic source. To this end only monopole source is considered, since as can be theoretically predicted, quadrupole source has less significant influence to the flutter stability compared to monopole one.
机译：在先前的研究中，研究了声源以及气动激励对结构动力学的影响。使用控制亥姆霍兹方程的边界元公式来确定声源的激励，以进行声波传播，并计算结构上的声载荷。然后，将载荷叠加到结构上的气动载荷上，并按照标准的气动弹性程序来计算与声学和气动激励相关的结构动力学问题。声学结构耦合是使用耦合BEM / FEM技术制定的。因此，将声—气弹性问题表述为BEM / FEM联轴器与结构部件的扩展包含了空气动力学术语。结构上的声载荷是在声域Ω边界的部分L上计算的，该部分与问题定义的结构表面重合。在所考虑的特定情况下，该边界类似于空气动力作用于结构上的表面。一个特定的示例正在处理，这是耦合的声学修改后的气动弹性不稳定性问题，其中右侧的声学项假定为隔离的单极或四极声源。假定叠加原理的适用性，并且将声波传播引起的压力场作为激励力场并入结构的结构动力学方程中。对于气动弹性不稳定性问题中的非定常气动和声学激励，已经对该方程的解进行了重新设计。简化版本使用经典集总质量系统作为结构模型，并使用Theodorsen方法使用经典非稳态空气动力学。空气弹性不稳定性和声激发的一般问题均得到验证。然后进行参数研究，以研究声源的位置，强度和频率的影响。为此，仅考虑单极子源，因为如理论上可以预测的那样，与单极子源相比，四极子源对颤振稳定性的影响较小。

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