密封-转子系统气流激振问题数值仿真

对于密封中发生气流激振的故障诊断问题,基于有限元方法,应用Muzynska非线性密封力模型建立了密封-转子系统动力学模型,通过数值积分方法研究了升/降速过程的气流激振失稳规律和振动特性,并分析了在变速和稳速情况下偏心量的影响。结果表明:气流激振力会使系统固有频率升高,使发生共振时的振幅降低;发生气流激振会出现锁频现象并伴有组合频率特征;降速时由于气体的流动性强从而导致切向惯性力很弱,惯性效应不明显;当偏心量较小时频谱上只出现了锁频,随着偏心增大组合频率出现并不断丰富;稳速时气流激振频率随偏心的提高而增大,并出现了频率突变。      

Validation of numerical prediction of dynamic derivatives: The DLR-F12 and the Transcruiser test cases

The dynamic derivatives are widely used in linear aerodynamic models in order to determine the flying qualities of an aircraft: the ability to predict them reliably, quickly and sufficiently early in the design process is vital in order to avoid late and costly component redesigns. This paper describes experimental and computational research dealing with the determination of dynamic derivatives carried out within the FP6 European project SimSAC. Numerical and experimental results are compared for two aircraft configurations: a generic civil transport aircraft, wing-fuselage-tail configuration called the DLR-F12 and a generic Transonic CRuiser, which is a canard configuration. Static and dynamic wind tunnel tests have been carried out for both configurations and are briefly described within this paper. The data generated for both the DLR-F12 and TCR configurations include force and pressure coefficients obtained during small amplitude pitch, roll and yaw oscillations while the data for the TCR configuration also include large amplitude oscillations, in order to investigate the dynamic effects on nonlinear aerodynamic characteristics. In addition, dynamic derivatives have been determined for both configurations with a large panel of tools, from linear aerodynamic (Vortex Lattice Methods) to CFD. This work confirms that an increase in fidelity level enables the dynamic derivatives to be calculated more accurately. Linear aerodynamics tools are shown to give satisfactory results but are very sensitive to the geometry/mesh input data. Although all the quasi-steady CFD approaches give comparable results (robustness) for steady dynamic derivatives, they do not allow the prediction of unsteady components for the dynamic derivatives (angular derivatives with respect to time): this can be done with either a fully unsteady approach i.e. with a time-marching scheme or with frequency domain solvers, both of which provide comparable results for the DLR-F12 test case. As far as the canard configuration is concerned, strong limitations for the linear aerodynamic tools are observed. A key aspect of this work are the acceleration techniques developed for CFD methods, which allow the computational time to be dramatically reduced while providing comparable results.     

超声波加工系统动力特性的研究

一、引言 近20年来,宇航工业广泛地采用耐高温材料,以保证宇航器的某些部件在高温环境下有较好的耐久寿命。耐高温的材料往往具有硬而脆的特性。这就要求人们发展一种新的（非传统的）加工技术。在这些技术之中,特别值得提出来的是超声波加工技术,见图1。     

复合材料泡沫夹芯结构低速冲击损伤研究

随着复合材料夹芯结构在航空领域的广泛应用,对其抗冲击性能的研究变得越来越重要。本文对泡沫夹芯结构的低速冲击问题采用试验及数值分析的手段进行研究,比较了不同冲击能量下泡沫夹芯结构的冲击响应特点,并利用数值分析手段揭示了冲击损伤的破坏机理,同时计算得到了该夹芯结构的临界冲击能量,模拟结果与试验吻合较好,可为工程设计提供一定...     

基于气/固耦合非定常流动的叶栅颤振分析

采用二维N-S方程／结构振动方程组耦合数值方法，分析计算了二维非定常气动力强迫振动条件下振动能量及气动力对叶栅所做的功，分别根据振动能量和气动力做功分析了叶栅的颤振特性。NACA0012和PROF叶栅在不同折合频率下气动参数随时间的变化表明，折合频率是影响叶栅颤振的重要因素。气固耦合方法得到的NA-CA0012叶栅颤振折合频率比非耦合的结果高，而对PROF叶栅则相反。这表明叶栅结构动力参数对其发生颤振时的折合频率影响很大且很复杂，要准确预测颤振应该考虑叶栅结构动力与气动力的耦合因素。     

一种基于数字综合算法的MTD滤波器设计方法

利用空间阵列方向图合成中的数字综合算法 ,提出了一种新的MTD滤波器设计方法。该方法通过在滤波器频率响应的副瓣区放置大量的干扰信号 ,改变干扰信号的功率强度 ,从而自适应地控制滤波器频率响应的副瓣电平。这种方法所设计的MTD滤波器 ,其频率响应不仅在零频附近有宽而深的零陷 ,而且在其他副瓣区域可以为任意形状 ,具有较好的实用性。设计实例证实了这种方法的有效性。     

超音速、高超音速飞行器动导数的高效计算方法

将超音速、高超音速气动力工程计算方法综合起来,推广到非定常气动力的计算,并用于求解任意外形飞行器作强迫运动时的非定常气动力.在此基础上进一步发展了一种适合于超音速、高超音速大迎角状态的飞行器动导数计算方法和程序.计算结果与国际标准实验数据作了比较,证明了该程序的正确性和精度.研究了减缩频率和基本迎角对动导数的影响,结果表明基本迎角对动稳定性导数影响较大,而减缩频率在小迎角范围内对动导数影响很小.     

超/高超声速飞行器动态稳定性导数极快速预测方法

飞行器设计早期阶段需要预测大量工况下的动导数。本文发展了一种面向超/高超声速飞行器的动导数极快速预测方法：首先基于当地流活塞理论，将飞行器进行小幅非定常运动所受到的气动力分为受自由来流引起的无附加扰动项以及受物面变形或运动引起的附加扰动项；通过当地表面斜度法、激波后等熵关系求解物面当地流动参数，进而结合非定常运动规律求出飞行器所受非定常气动力；再采用待定系数法对非定常气动力进行提取、辨识，最终得到超/高超声速飞行器动导数。该方法克服了传统方法对CFD流场参数的依赖和耦合，具有极高的计算效率；同时典型算例验证表明，该方法在超声速、高超声速工况下都能够很好预测动导数变化趋势。将该方法应用于复杂外形飞行器动导数预测，并讨论了与CFD方法的误差来源。本文方法可作为高速飞行器总体设计阶段布局选型的工具。     

非定常超音速侧滑机翼的升力、力矩系数及动导数的数值计算

 本文利用分布在机翼平面上的非定常超音速点源的特征线网格法给出非定常超音速侧滑机翼的数值解。本文给出侧滑机翼作沉浮、俯仰、滚转谐振时的振型以及计算升力、力矩和动导数（包括交叉导数）的计算方法。按本文用非定常理论数值解对典型的无侧滑机翼计算出的动导数与常用的按准定常理论解析公式计算结果进行比较和鉴定,结果表明本文方法是令人满意的。     

Study on dynamic stiffness of supporting structure and its influence on vibration of rotors

The dynamic response of the rotor depends on not only itself but also the dynamical characteristics of the structures that support it. In this paper, the coupling vibration characteristics of the rotor and supporting structure are studied using one simple rotor-supports model firstly, and then the dynamic stiffness of the typical supporting structure of an aero-engine is investigated in use of both numerical and experimental methods. While, one simulation strategy is developed to include dynamic stiffness of realistic supports in the dynamical analysis of the rotor system. The simulated and tested results show that the dynamic stiffness of the supporting structure not only depends on the structural parameters but also is related to the frequency of the excitation force. The dynamic stiffness is affected by the damping and inertia effect when the excitation frequency is high and closed to the resonance frequency of the support, which may decrease the dynamic stiffness sharply. More resonance frequencies may be induced and the critical speed could be reduced or increased. While higher vibration response peak and overload of the bearing may also be caused by the varied dynamic stiffness, which needs to be avoided in the design of the rotor-supports system.     

涡轮级三维粘性流场的数值模拟

本文给出了一种求解涡轮级三维定常粘性流场的计算方法,并对某型航空发动机的高压涡轮进行了数值模拟。该计算程序考虑到了涡轮级工作温度范围较大而引起的变比热问题。文中采用了三阶精度的TVD格式和B-L湍流模型。叶列间参数的传递采用了“混合平面”法。叶列间处理采用外推无反射边界条件来保证参数在交接面上的周向不均匀。同时在交接面上构造了Riemann解和使用松弛因子来提高程序在叶列间小间隙情况下的稳定性。      

封闭行星齿轮传动系统的扭振特性研究

本文建立了封闭行星齿轮传动系统的扭振计算模型,模型中考虑了行星轮和星轮的啮合相位,行星架的弹性变形和负载惯性。用数值解法获得了在受周期性变化的齿轮啮合刚度和齿频综合误差激励下的齿轮啮合动载荷和在不同的输入转速下的动载荷系数。分析了在星形轮系和行星轮系动力耦合情况下齿轮系统的动态特性,得出了对封闭行星齿轮传动设计有意义的结论。      

基于后缘小翼的旋翼翼型动态失速控制分析

针对后缘小翼(TEF)的典型运动参数对旋翼翼型动态失速特性的控制进行了研究。发展了一套适用于带有后缘小翼控制的旋翼翼型非定常流动特性模拟的高效、高精度CFD方法。通过求解Poisson方程生成围绕旋翼翼型的黏性贴体和正交网格,为保证后缘小翼附近的网格生成质量,建立了基于翼型点重构的方法来描述后缘小翼的偏转运动;为克服变形网格方法可能导致网格畸变的不足,发展了一套适用于带有后缘小翼控制的旋翼翼型运动嵌套网格方法。基于非定常雷诺平均Navier-Stokes(URANS)方程、双时间法、Spalart-Allmaras(S-A)湍流模型和Roe-Monotone Upwind-centered Scheme for Conservation Laws(Roe-MUSCL)插值格式,发展了旋翼翼型非定常气动特性分析的高精度数值方法,并采用Lower-Upper Symmetric Gauss-Seidel(LU-SGS)隐式时间推进方法及并行技术提高计算效率。以有试验结果验证的HH-02翼型和SC1095翼型为算例,精确捕捉了动态失速状态下的气动力迟滞效应,验证了本文方法的有效性。着重针对SC1095旋翼翼型的动态失速状态开展后缘小翼的控制分析,提出了可以体现翼型升力、阻力及力矩综合特性的关系式Po和Pc,揭示了后缘小翼振荡频率、相位差和偏转幅值对动态失速特性影响的规律。研究结果表明:当后缘小翼偏转的相对运动频率为1.0,且小翼运动规律与翼型振荡规律之间的相位差为0°时,后缘小翼能够更好地抑制翼型动态失速现象;在此状态下,当偏转幅值为10°时,SC1095翼型最大阻力系数和最大力矩系数可以分别降低19%和27%。     

Numerical investigation of aerodynamic flow actuation produced by surface plasma actuator on 2D oscillating airfoil

Numerical simulation of unsteady flow control over an oscillating NACA0012 airfoil is investigated. Flow actuation of a turbulent flow over the airfoil is provided by low current DC surface glow discharge plasma actuator which is analytically modeled as an ion pressure force produced in the cathode sheath region. The modeled plasma actuator has an induced pressure force of about 2 k Pa under a typical experiment condition and is placed on the airfoil surface at 0% chord length and/or at 10% chord length. The plasma actuator at deep-stall angles(from 5° to 25°) is able to slightly delay a dynamic stall and to weaken a pressure fluctuation in down-stroke motion. As a result, the wake region is reduced. The actuation effect varies with different plasma pulse frequencies, actuator locations and reduced frequencies. A lift coefficient can increase up to 70% by a selective operation of the plasma actuator with various plasma frequencies and locations as the angle of attack changes. Active flow control which is a key advantageous feature of the plasma actuator reveals that a dynamic stall phenomenon can be controlled by the surface plasma actuator with less power consumption if a careful control scheme of the plasma actuator is employed with the optimized plasma pulse frequency and actuator location corresponding to a dynamic change in reduced frequency.     

Nonlinear modal electromechanical coupling factor for piezoelectric structures containing nonlinearities

Within the linear framework, the Modal Electromechanical Coupling Factor (MEMCF) is an important indicator to quantify the dynamic conversion of mechanical energy and electrical energy of piezoelectric structures. It is also an important tool to guide the piezoelectric damping design of linear structures. Advanced aircraft often fly in maneuvers, and the variable working conditions induce drastic changes in the load level on structures. Geometric and contact nonlinearities of thin-walled structures and joint structures are often activated. To achieve a good vibration reduction effect covering all working conditions, one cannot directly use linear electromechanical coupling theory to instruct the piezoelectric damping design for nonlinear structures. Therefore, this paper defines the Nonlinear Modal Electromechanical Coupling Factor (NMEMCF) and proposes the corresponding numerical method for the first time to quantitatively evaluate the electromechanical coupling capability of nonlinear piezoelectric structures. Three candidate definitions of the NMEMCF are given, including two frequency definitions and one energy definition. The energy definition is the most promising one. It is not only applicable to both conservative and dissipative nonlinear structures but also compatible with the linear MEMCF. In addition, based on the energy formula, the NMEMCF can be obtained by only performing one nonlinear modal analysis in the open-circuit state. The analytical findings and the numerical tool are validated against two piezoelectric structures with different types of nonlinearities. A strong correlation among the NMEMCF, geometric parameters, and energy dissipation is observed. The results confirm that the proposed NMEMCF captures the physics of the electromechanical coupling phenomenon associated with nonlinear piezoelectric structures and can be used as an essential design indicator of piezoelectric damping, especially for variable working conditions.     

吸气式高超声速飞行器俯仰/滚转耦合运动特性

针对一种类似SR-72构型的吸气式高超声速飞机开展了进气道通流状态下俯仰/滚转耦合运动相关研究。通过数值模拟获得了滚转单自由度静稳定性、动稳定性以及强迫俯仰/自由滚转运动下的两自由度耦合动稳定性，研究了飞行器转动惯量以及俯仰运动频率对耦合运动的影响，简要分析了耦合运动的机理。研究发现虽然此飞行器具有滚转静稳定性和动稳定性，但是在强迫俯仰/自由滚转运动过程中，滚转通道却出现了小幅度振荡与大振幅振荡交替出现的情况，最大滚转角超过70°。小幅度振荡出现在正弦俯仰振荡的上半周期，其振荡频率随轴向转动惯量增加而降低，幅值随俯仰振荡频率增加而增大；大振幅振荡出现在下半周期，其幅值基本不变，而振荡频率与俯仰振荡一致。这种现象基本不受惯性耦合作用影响，可以认为是由气动力主导的。     

叠片式箔片气体动压推力轴承的静动态特性

针对一种叠片式箔片气体动压推力轴承,提出相应的结构刚度模型。运用有限差分法(FDM)求解可压缩气体雷诺方程,并与箔片弹性变形方程耦合求解得到该类型轴承的静动态特性。结果表明:由于支承结构在径向和周向都具有变刚度特点,导致单瓣箔片上出现二次收敛楔形效应,因此形成两个压力峰值,与传统类型轴承相比能在一定程度上提高承载能力。随着最小气膜厚度的增加,轴承承载能力和摩擦力矩都不断下降,且动态刚度也逐渐下降,但对动态阻尼的影响较小。存在最优楔形高度值以实现较大承载能力的同时,也能达到较小摩擦力矩,减小功率损耗,并且还能获得较高的动态刚度和动态阻尼系数。      

由飞行试验数据求取直升机气动导数的最佳方法研究

本文主要介绍利用频率法、卡尔曼滤波和最大似然法求取气动导数的方法。方法的特点是,通过频率法使旋翼高频成份的影响减至最小,同时求取试验数据的测量噪声和过程噪声,然后通过卡尔曼滤波使试验数据包含的随机噪声减小,最后使用最大似然法使试验数据包含的随机噪声进一步减小,并求取最终的气动导数。计算结果表明,该方法可使试验数据中包含的噪声减至最小,复合相关系数提高到0.95以上,特征根更接近真值,其准确度优于最小二乘法、频率法、卡尔曼滤波方法和最大似然法,它保留了使用低通滤波数据的卡尔曼滤波方法的优点,克服了原方法振荡模态频率偏低的缺点,适合于各种直升机的导数识别。     

三次样条插值法在气动导数计算中的应用

在飞行仿真建模过程中,快速、精确的气动导数查寻可以提高仿真系统的实时性和逼真性。在研究大量现有气动导数查寻方法的基础上,提出了一种运用三次样条法、双三次样条法进行气动导数查寻的新思路,该方法不仅避免了以往线性插值的"局部性",提高了计算结果的精度,而且还克服了函数(多项式)拟合法导致动力学模型通用性差的缺陷。仿真实验表明,该方法在气动力和气动力矩的计算中是有效的、可行的。     

涨圈密封挤压油膜阻尼器流场与阻尼特性

为研究两端密封型挤压油膜阻尼器流场与阻尼特性,建立了涨圈密封挤压油膜阻尼器三维非定常流场数值仿真模型。基于Fluent软件中的Mixture多相流模型和Schnerr-Sauer空化模型数值模拟得到动态油膜压力与气相体积分数的周向分布规律。将计算得到的阻尼器油膜压力与文献中的试验数据对比,结果显示:两者具有较高的一致性。由动态油膜力导出的平均等效阻尼系数与试验采用阻抗法识别的结果相比仅有0.6%的偏差,从而验证了该数值模型与预测方法的有效性。进一步的数值计算表明增大进动半径、进动频率、涨圈密封的狭缝宽度均会使挤压油膜阻尼器流场中的空化现象加重,同时等效阻尼系数降低。