高超声速飞行器推进模块的设计参数分析

通过斜激波理论、准一维工程估算和特征线方法建立了一个与飞行器机体一体化的推进系统模块的气动分析模型,其中采用参考温度法估算模块的粘性效应。在此基础上分别研究了飞行器前体长度、前缘角及推进模块宽度等关键设计参数对推进模块气动性能的影响。结果表明:增大模块前体长度将使模块的升力、净推力和比冲先增后降;增加前缘角将增加升力,但降低净推力;增加模块宽度会导致等效升力下降。因此,在设计此类高超声速巡航飞行器时,应采用模块化的推进系统并折衷选择前体长度和前缘角的大小。      

地面系留对直升机动力响应的影响

 建立了系留状态下直升机旋翼/机体耦合非线性动力学模型,无铰旋翼简化为当量铰刚性桨叶模型,假定机体是刚性体并受起落架和系留索的约束,系留索静态时松弛并只能承受拉力。采用数值仿真研究了系留对模型旋翼地面共振的影响,对初始扰动和旋翼转速对系统动力学行为的影响也进行了仿真研究。对于无系留的模型旋翼来说,在任何转速下没有出现不稳定现象;地面系留时系统会呈现稳定响应、极限环以及大幅值振荡等非线性动力学行为,大幅值振荡将使系留索、接头和支持结构承受破坏性动力载荷。     

空气动力二阶核函数辨识方法

采用截断三阶Volterra级数模型来研究空气动力二阶核函数的辨识问题,选取一簇正交化的切比雪夫多项式对二阶核函数进行参数化处理,并将非参数辨识问题转化成参数辨识问题。相比于其他方法,本文模型能有效降低对激励信号幅值的敏感程度,保证辨识出的核函数具有较好的保真度;只针对三阶Volterra降阶模型中的一阶、二阶核函数进行辨识,即可提升原系统一阶、二阶核函数的辨识精度,却不会显著增加辨识过程的工作量;参数化辨识方法属于整体性辨识,根据已有的部分数据对(输入、输出数据)就能完成系统辨识,且能达到较好的辨识精度,从而有效地减少了执行计算流体力学(CFD)代码程序的总次数,节约了大量的时间成本。算例表明,与目前流行的非参数化方法相比,本文提出的切比雪夫函数辨识方法,精度上达到预期要求,辨识过程消耗的CFD总时间量至少可降低一个数量级。     

对称分段线性系统主共振的分叉

由ＫＢＭ法推出的分段线性系统主共振的一次近似解，导出了分叉方程，然后应用奇异性理论对主共振的分叉类型进行了系统的分析，并用计算稳态周期运动的参数延续数值方法结果与其中感兴趣的部分进行了对比，发现基于弱非线性分析的主共振一次近似解在较强的非线性情况下仍具有一定的精度。     

Is the North Atlantic Oscillation modulated by solar and lunar cycles? Some evidences from Hurst autocorrelation analysis

Several studies have suggested that the Sun and Moon cycles affect the Earth climatic dynamics. Nevertheless, there is a long-standing controversy whether solar variability and tides can significantly generate climate change, and how this may occur. Spectral analysis of climatic indices has provided only indirect evidences of the effects of solar–tidal periodicities in the Earth climate. This work addresses the issue by considering the dynamics of the daily North Atlantic Oscillation index over the period from 1950 to 2009. In contrast to previous studies, this work proposes that external cycles can be detected in the autocorrelation dynamics rather than in the raw North Atlantic Oscillation index series. Here, the R/S-scaling analysis is used to quantify, via the so-called Hurst exponent, the presence of autocorrelations along the studied years. Fourier analysis scan of the autocorrelation series thus show two prominent spectral components near (±3%) the lunar tidal 4.425 and the solar 11 years cycles. Intermediate spectral components near 6.4, 7.75 and 8.9 years are proposed to be, at least partially, a result of energy capture from internal mechanisms into cycles resulting from the nonlinear resonance of the fundamental solar–tidal cycles. The dominant effect of the solar variability is clarified by showing that in about 70% of the studied period the sunspot number and the Hurst exponent phases are synchronized, indicating that a higher solar activity enhances the North Atlantic Oscillation index predictability.     

利用声共振测量管件长度的研究

介绍一种利用声共振原理测量大长度管件长度的方法，通过测量管内空气的共振频率来确定管长。对这种方法的原理、数学模型进行了较为深入的分析，提出了具体的测量方案，并对系统进行了误差分析。结果表明，该方法的测量误差为±０．０５％，并可实现便携式仪器和单端测量。     

复合材料层合板下陷区结构设计

复合材料层合板下陷是飞机结构中应用广泛的典型结构细节。以下陷长深比、相同方向下陷区间距、两个不同方向下陷区间距为下陷区设计变量,建立参数化有限元模型;通过下陷应力应变分布、初始失效和最终承载能力分析,确定各设计变量对下陷区结构力学性能的影响,并进行参数化设计。分析结果表明:下陷区结构最先发生损伤的部位为下陷区转折处;合理的下陷参数设计变量取值为长深比B/A≥20、主受力方向上两个下陷区间距A/H≥12、不同方向上两个下陷区间距C/A_(min)≥1.5。     

Physical model for acoustic resonance in annular cavity structure

A physical model for acoustic resonance in the annular cavity structure is developed to represent the typical characteristic when acoustic resonance occurs. Firstly, the measurement of sound pressure in the casing and rotor blades vibration is operated in a multistage high pressure compressor. The sharp peak frequency and discrete multi-tone occur in the frequency spectrum of sound pressure in the compressor, and the vibration of the first stage of rotor blades synchronously presents the high amplitude. The frequencies associated with rotor blades vibration can be calculated with rotating sound source theory. It is also confirmed that acoustic resonance occurs in the multistage compressor. With acoustic similarity principle, an annular cavity model is established to simulate the typical characteristics of acoustic resonance in the compressor based on Large Eddy Simulation (LES) and Lighthill acoustic analogy. The coupling relationship between cavity acoustic mode and disc vibration mode shape is expounded when acoustic resonance occurs in the model. And acoustic resonance will be locked in the certain flow rate range. All these characteristics match well with those occur in the multistage high pressure compressor.     

PARAMETRIC SHIMMY ANALYSIS

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飞机刹车制动引起的谐振解决措施

分析了飞机着陆过程起落架和机轮受力情况,针对刹车制动引起谐振的机理,并从刹车系统角度出发,就跑道识别、智能控制技术、多级偏压调节(PBM)技术、轮速采集及滤波、防振加固等方面,介绍了一些有效解决制动引起的振动的方法和措施。为后续解决实际问题提供了具体思路。