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Aero-servo-elastic analysis of a hypersonic aircraft

机译:超声波飞机的航空伺服弹性分析

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Aero-servo-elastic analysis of a complex hypersonic aircraft is presented in this paper. A structure geometry was designed and built based on the X-43A vehicle. First, a three-dimensional structural finite element model was proposed with effective two-dimensional elements, which can obtain effective modal analysis results without useless local modes. Second, computational fluid dynamic (CFD) simulation was adopted to find aero-heating distribution of thermal mode via this structure. Aero-heating effect was included to study thermal-modal characteristics of the present structure. Influence due to material characteristic change and thermal stress was studied. After structural finite element analysis was completed, flutter of the present vehicle was investigated. Aero-servo-elastic analysis was then started from the definition of an aero-servo-elastic closed-loop system. In this system, the present aircraft is treated as flexible structure, in which the control sensor on the aircraft received not only rigid motion signal but also elastic vibration signal, and this signal can translate into the deflection signal to form aerodynamic control force through this aero-servo control system, and this force can continually influence aerodynamic force. One of the most important steps for this analysis was computation of unsteady aerodynamic force of the present structure, and the related process was developed based on an effective fitting method. Finally, bode diagrams of pitching, rolling and yawing were investigated, form which the law of aero-servo stability of the X-43A vehicle can be observed and analyzed. It can be found from the results of this paper that effective investigation of aero-servo-elastic characteristics of a complex hypersonic aircraft should be based on accurate structural finite element modeling, modal analysis and flutter analysis. The proposed method in this paper can provide effective analysis process for the design of controller for hypersonic aircraft.
机译:本文提出了一种复杂的超声波飞机的航空伺服弹性分析。基于X-43A车辆设计和构建了结构几何形状。首先,提出了一种具有有效二维元素的三维结构有限元模型,其可以获得有效的模态分析结果而无用的本地模式。其次,采用计算流体动态(CFD)模拟通过该结构寻找热模式的航空加热分布。包括航空加热效果以研究本结构的热模态特性。研究了由于材料特征变化和热应力的影响。完成结构有限元分析后,研究了本车的颤动。然后从航空伺服弹性闭环系统的定义开始航空伺服弹性分析。在该系统中,本飞机被视为柔性结构,其中飞机上的控制传感器不仅接收到刚性运动信号,而且是弹性振动信号,并且该信号可以通过该航空转化为偏转信号以形成空气动力控制力。 -Servo控制系统,这种力可以不断影响空气动力。该分析的最重要步骤之一是计算本结构不稳定的空气动力力,并且基于有效配合方法开发相关过程。最后,研究了倾斜,轧制和偏航的凸型图,可以观察和分析X-43A载体的航空伺服稳定性定律的形式。可以从本文的结果中找到,有效调查复杂的超声波飞机的航空伺服弹性特性应基于精确的结构有限元建模,模态分析和颤动分析。本文所提出的方法可以为超音速飞机设计提供有效的分析过程。

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