Unsteady rotor flow analysis using a diagonally implicit harmonic balance method and an overset mesh topology

The diagonally implicit harmonic balance method is developed in an overset mesh topology and applied to unsteady rotor flows analysis. Its efficiency is by reducing the complexity of a fully implicit harmonic balance method which becomes more flexible in handling the higher harmonics of the flow solutions. Applied to the overset mesh topology, the efficiency of the method becomes greater by reducing the number of solution interpolations required during the entire solution procedure as the method reduces the unsteady computation into periodic steady state. To verify the accuracy and efficiency of the method, both hovering and unsteady forward flight of Caradonna and Tung and AH-1G rotors are solved. Compared with wind-tunnel experiments, the numerical results demonstrate good agreements at computational cost an order of magnitude more efficient than the conventional time-accurate computation method. The proposed method has great potential in other engineering applications, including flapping wing vehicles, turbo-machinery, wind-turbines, etc.     

Virtual flight simulation of a dual rotor micro air vehicle

In this paper, a new computational method is developed based on computational fluid dynamics (CFD) coupled with rigid body dynamics (RBD) and flight control law in an in-house programmed source code. The CFD solver is established based on momentum source method, preconditioning method, lower–upper symmetric Gauss–Seidel iteration method, and moving overset grid method. Two-equation shear–stress transport k ? ω turbulence model is employed to close the governing equations. Third-order Adams prediction-correction method is used to couple CFD and RBD in the inner iteration. The wing-rock motion of the delta wing is simulated to validate the capability of the computational method for virtual flight simulation. Finally, the developed computational method is employed to simulate the longitudinal virtual flight of a dual rotor micro air vehicle (MAV). Results show that the computational method can simulate the virtual flight of the dual rotor MAV.     

双转子涡喷发动机气动性能优化控制研究

航空发动机的控制规律作用巨大,它决定了发动机能否获得设定的稳态工作下性能指标,同时保证工作过程中的压气机和涡轮的气动稳定性。双转子涡喷发动机气动性能优化控制的目的就是有效地挖掘发动机的使用潜力。研究方法采用部件特性法对发动机进行稳态建模,并针对某双转子涡喷发动机的稳态模型进行三种不同稳态控制规律下的仿真,得到发动机性能参数的不同变化趋势,并对其进行了详细的分析。结果表明：保持低压转子转速不变的情况下,随着压气机进口总温的增加,高压转子转速上升,涡轮前温度升高,发动机推力增加;保持涡轮前温度不变的情况下,随着压气机进口总温的升高,低压压气机气动负荷变重,低压转子转速降低;高压转子转速也下降,但是下降幅度很小;燃油流量增加;保持高压转子转速不变的情况下,随着压气机进口总温的升高,燃油流量有一定的增加,低压转子转速有所降低;推力受多重因素的影响,推力值变化趋势较为复杂。     

Analytical study of nonlinear synchronous full annular rub motion of flexible rotor–stator system and its dynamic stability

The nonlinear synchronous full annular rub motion of a flexible rotor induced by the mass unbalance and the contact-rub force with rigid and flexible stator is studied analytically. The nonlinear property is due to the dry friction force between stator and rotor. The exact solutions of the synchronous full annular rub motion and its run speed regions are obtained. The stability of the synchronous full annular rub motion is discussed analytically. The stability criterion and the stability regions of the synchronous full annular rub motion are obtained. A simplified approximate criterion formula for dynamic stability is also derived under the conditions of large impact stiffness, small damping and small friction. The simplified criterion formula can be used conveniently in engineering and matches the real situations of industry.     

Analogy between a flapping wing and a wind turbine with a vertical axis of revolution

Based on an analysis of available experimental data, the hypothesis about an analogy between a flapping wing and a wind turbine of the Darrieus rotor type is justified. It is demonstrated that the torque on the shaft of the Darrieus rotor is generated by thrust forces acting on the blades in a pulsed flow. A conclusion is drawn that it is necessary to perform aerodynamic calculations of blades on the basis of the nonlinear theory of the wing in an unsteady flow with allowance for the airfoil thickness. __________ Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 50, No. 2, pp. 152–155, March–April, 2009.     

基于DEM的推土机铲刀曲面参数化设计分析

为合理地选择推土机铲刀曲面参数,本文利用基于离散单元法(DEM)的EDEM软件模拟铲运过程．模拟中选用三种形状的石块混合物料作为被铲运介质,对三种曲率半径的圆弧面铲刀和两种形式的直线-圆弧复合式铲刀在水平铲运工作时所受的工作阻力进行了对比分析,发现不同曲面参数的铲刀在水平铲运时的工作阻力主要来自于水平前进方向,圆弧面铲刀的水平阻力随曲率半径的减小而增大,而竖直向阻力会随着曲率半径增大而由向上逐渐转变为向下;直线在上-圆弧在下复合式铲刀所受的水平阻力始终大于直线在下-圆弧在上复合式铲刀所受的水平阻力,铲刀曲面几乎不受侧向力．     

转子与定子碰摩的非线性动力学研究

转子与定子碰摩的动力学行为及其与系统参数关系对旋转机械设计和安全运行至关重要. 转子/定子碰摩系统是一类多参数控制的高维非光滑强非线性系统, 其动力学行为非常复杂. 本文主要从动力学与控制的角度对过去半个世纪有关转子与定子碰摩的研究成果进行归纳和总结, 其目的在于帮助读者尽可能全面系统地了解该问题的研究现状, 提炼尚待解决的问题, 以求推动转子与定子碰摩研究的进一步深入, 并为解决实际问题提供帮助. 本文将首先从碰摩局部模型和碰摩系统模型两个方面对已有的转子/定子碰摩系统的建模进行了简单的划分和归类. 其次, 以典型碰摩非线性响应为主线, 分别介绍了有关同频碰摩响应、谐波周期碰摩响应、准周期局部碰摩响应、干摩擦自激反向全周涡动响应、碰摩的全局响应行为以及碰摩响应的分岔与混沌方面的研究成果. 接下来讨论了在主被动抑制碰摩振动方面取得的结果. 最后, 给出结论并提出有待进一步研究的问题.     

旋转型单分子机器

分子机器是一种分子水平上的机器,它是一类通过外部刺激（如化学能、电能、光照等）将能量转化为可控运动的分子器件。由于人工分子机器在纳米科技领域的应用越来越普遍,已经引起人们的广泛关注。人工合成的分子机器在模拟机器运动时主要有线性运动和旋转运动两种基本运动方式,本文重点介绍了几种旋转型的单分子机器,包括分子齿轮、分子转门、分子闸和分子棘轮、分子马达等。这类分子机器的结构特点是由轴、转子和定子三部分组成,其运动特点是转子通过轴围绕定子进行双向或单向旋转。本文在介绍这类分子转子的同时,简单讨论了其设计理念和在溶液状态下所表现出的动力学行为,同时还展望了分子转子和分子马达的发展前景和面临的挑战。     

影像测量技术在叶尖间隙测量中的应用

针对航空涡轮发动机叶尖间隙测量难度大、精确度不高的问题,提出利用影像测量技术对装配过程中的叶尖间隙进行高精度测量,采用自定义标定、改进的边缘检测和Hough变换、图像超分辨率复原技术,通过运动控制机构、工业CCD摄像机、计算机视觉库,设计了独特的图像测量体系,实现了叶尖间隙的高精度非接触测量。实验结果表明,测量精度达到了15 m,与其他叶尖间隙测量以及影像测量系统相比,该方法不仅精确度有所提高,而且移植性好、成本低。