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首页> 外文期刊>Journal of Spacecraft and Rockets >Linearized Aeroelastic Analysis for a Launch Vehicle in Transonic Flight Conditions
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Linearized Aeroelastic Analysis for a Launch Vehicle in Transonic Flight Conditions

机译：跨音速飞行条件下运载火箭的线性气动弹性分析

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摘要

The purpose of the present work is the development of a linearized aeroelastic modeling and analysis for a launch vehicle in the neighborhood of a transonic flight condition. A two-dimensional airfoil transonic case selected from the technical literature (specifically, a MBB-A3 supercritical airfoil in unsteady transonic regime) has been studied to validate the procedure for identifying the linearized unsteady aerodynamics. The present methodology has been successively performed for the system identification of the linearized aerodynamics of the VEGA European small launch vehicle in a transonic flow phase and in presence of an angle of attack. This has been achieved by performing several prescribed modal-transient boundary conditions on a Euler-based computational-fluid-dynamics code and postprocessing the input/output data in the frequency domain. Finally, both a standard eigenanalysis and an iterative eigenanalysis have been performed to study the aeroelastic stability on the linearized model of the launch vehicle in transonic flow. The nature of the methodology is quite general and can be applied in the neighborhood of any arbitrary parametric flight condition of a launch vehicle.
机译：本工作的目的是为跨音速飞行条件附近的运载火箭开发线性气动弹性建模和分析。研究了从技术文献中选择的二维机翼跨音速情况（特别是在非稳态跨音速状态下的MBB-A3超临界机翼），以验证用于识别线性化非稳态空气动力学的程序。已经成功地执行了本方法学，用于系统识别跨音速流动阶段和存在迎角的VEGA欧洲小型运载火箭的线性空气动力学。这是通过对基于Euler的计算流体动力学代码执行几个规定的模态瞬态边界条件并在频域中对输入/输出数据进行后处理来实现的。最后，进行了标准特征分析和迭代特征分析，以研究跨音速流中运载火箭线性模型的气动弹性稳定性。该方法的性质是相当普遍的，并且可以应用于运载火箭的任何任意参数飞行条件的附近。

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