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传统的声振环境,只考虑了给定声场环境下的结构响应分析,这个给定的声场孤立于结构本身,忽略了声场、结构、流体的耦合效应,因此声气动弹性耦合这种多力学场的研究具有重要意义。基于此,提出了一种基于CFD/CSD耦合的声气动弹性数值仿真策略,相比传统的声振环境预示方法,该方法考虑了声载荷(脉动压力场)与结构的耦合关系。该文首先采用有限体积法离散Euler方程,对二维的NACA0012翼型进行求解,来验证非定常气动力的准确性。然后通过CFD/CSD耦合计算三维AGARD445.6机翼的非定常气动力,在时域内推进结构运动方程,得到弹性响应的结构历程,记录每一时刻的气动载荷,并运用声气动弹性分析的思想对机翼表面的声压级进行计算,证实了声气动弹性分析方法的可行性。
The traditional acoustic vibrational environment only considers the structural response analysis under a given acoustic field. The given acoustic field is isolated from the structure itself, ignoring the coupling effect of sound field, structure and fluid, so the acousto-elastic coupling Research is of great significance. Based on this, a numerical simulation method of acoustic aeroelasticity based on CFD / CSD coupling is proposed. Compared with the traditional predicting method of acoustic vibration, this method considers the coupling relationship between acoustic load (pulsating pressure field) and structure. In this paper, the discrete volume Euler equation is first used to solve the two-dimensional NACA0012 airfoil to verify the accuracy of unsteady aerodynamics. Then, the unsteady aerodynamic forces of the three-dimensional AGARD445.6 wing are calculated by CFD / CSD coupling, and the structural equation of motion is advanced in the time domain to obtain the structural response of the elastic response. The aerodynamic load at each moment is recorded and the acousto-aerodynamic analysis The calculation of the sound pressure level on the wing surface confirms the feasibility of the aeroelastic analysis method.