超燃冲压发动机喷管推力性能理论预测

超燃冲压发动机发展60多年来,虽然取得了很大的进步,但是对其推力大小的理论评估是一个没有很好解决的问题.超燃冲压发动机的推力主要由喷管产生,因此重点研究了喷管的推力特性.将燃烧室出口参数作为喷管入口边界条件,利用等熵膨胀理论,通过对喷管壁面压力积分,得到了简化的无量纲推力公式,获得了影响推力大小的关键参数和物理规律.理...     

鱼类自主游动水动力学特性的数值模拟

通过对推力和阻力进行重新定义, 从根本上解决了鱼游研究中推力和阻力无法区分的难题.在此基础上, 利用自适应网格下的ghost-cell浸没边界方法, 模拟了鱼类以鲹科模式在黏性流体(309 \le Re \le 14\,581)和无黏流体 (相当于雷诺数无穷大情形)中的二维自主游动.结果表明: (1) Strouhal数随雷诺数增大而减小,当雷诺数趋向于无穷时, Strouhal数趋向于0.25; (2)在所有雷诺数情况下, 推力主要来源于压力分量; 当Re<3000时, 阻力的压力分量小于黏性力分量, 而当Re>3000, 二者的关系就会反过来; (3)推进效率随着雷诺数的增大而增大,当雷诺数趋向于无穷大时, 推进效率最高可以达到70%, 说明鲹科模式适用于较高雷诺数下的游动.      

Role of wing morphing in thrust generation

In this paper, we investigate the role of morphing on flight dynamics of two birds by simulating the flow over rigid and morphing wings that have the characteristics of two different birds, namely the Giant Petrel and Dove Prion. The simulation of a flapping rigid wing shows that the root of the wing should be placed at a specific angle of attack in order to generate enough lift to balance the weight of the bird. However, in this case the generated thrust is either very small, or even negative, depending on the wing shape. Further, results show that morphing of the wing enables a significant increase in the thrust and propulsive efficiency. This indicates that the birds actually utilize some sort of active wing twisting and bending to produce enough thrust. This study should facilitate better guidance for the design of flapping air vehicles.     

柴达木盆地北缘新生代右行走滑冲断构造带的几何学和运动学

通过露头地质调查、地震剖面解释和地层残余厚度图的分析,发现柴迭木盆地北缘新生代以右行走滑冲断构造变形为主.走滑冲断构造带内的断层在平面上呈分支复合,剖面上表现为花状构造,走滑逆冲断层上、下盘地层呈不协调产出.右行走滑冲断构造带形成的应力来源于阿尔金断裂左行走滑的拖拽力作用以及北东-南西和北西-南东向的简单剪切应力作用.     

圆形瓦推力轴承动特性研究

建立了圆形可倾瓦推力轴承动特性计算的数学模型,考虑瓦变形对轴承性能的影响,对中心支承条件下的圆瓦推力轴承的动特性数学模型进行了有限元求解,得出了圆瓦推力轴承的动特性系数值,同时讨论了弹簧支承时的弹簧刚度选取依据,所得结果可用于指导圆形瓦推力轴承的设计和应用。     

推力电磁轴承的电磁场分析

利用有限元法对推力电磁轴承的磁场分布进行了分析计算,并通过对某一实际电磁轴承的推力轴承磁场分布及漏磁的分析计算,得出了推力轴承和推力盘之间的气隙及推力轴承和转子之间的气隙之比的最佳设计值,所得结果可作为推力电磁轴承实际设计的准则     

推力轴承热稳定性非线性分析及周期稳态解的全局特性研究

建立了考虑瞬态油膜压力影响的热稳定性分析模型 ,用求解系统周期解分岔的 PNF法对推力轴承系统的热稳定性进行了研究 ,结合 Poincare映射与胞映射法思想 ,提出了用于分析系统周期稳态解全局特性的数值计算 PCM方法 ,并对推力轴承热系统周期稳态解的全局特性进行了考察     

两串列扑翼的相位差对平均推力影响机理的实验研究

在一个低雷诺数的循环水洞中,实验研究了前后翅翼之间的相位差对两串列扑翼平均推力的影响.利用一个三分量的Kistler 压力传感器来测量扑翼的瞬时力;利用一个数字粒子测速仪系统(TSI DPIV) 来测量扑翼的前缘涡以及其周围的流场. 当相位差从0° 增加到360°,前翅的平均推力随着相位差正弦变化;前翅平均推力的增加是由于后翅的前缘涡和滞止区域增加了前翅的有效攻角. 后翅平均推力曲线有一个明显的V 字形低谷.低谷处较小的平均推力是由于前翅的脱落涡抑制了后翅前缘涡的形成并且减小了其有效攻角.当间距为0.5倍弦长相位差约为290°时,前后翅翼平均推力系数的合值能达到最大值0.667,明显大于两倍的单翼平均推力系数(2×0.255).      

基于预测控制的直接侧向力气动力复合控制方法研究

针对大气层内拦截导弹直接侧向力与气动力复合控制系统设计问题, 首先, 根据发动机的配置建立了复合控制系统模型;其次, 提出了复合控制策略, 包括动态分配算法、直接力控制子系统、气动力控制子系统3部分; 然后, 在考虑两套执行机构动态特性差别的情况下,基于预测控制思想给出了过载误差动态分配算法; 在此基础上, 根据直接侧向力的离散特性, 基于预测控制方法设计了直接力控制规律, 考虑到直接力控制作用对弹体产生的扰动, 基于自抗扰方法设计了气动力子系统; 最后, 通过仿真验证了直接力气动力复合控制策略与方法的有效性.     

Fully suspended, five-axis, three-magnetic-bearing dynamic spin rig with forced excitation

A significant advancement in the dynamic spin rig (DSR), i.e., the five-axis, three-magnetic-bearing DSR, is used to perform vibration tests of turbomachinery blades and components under rotating and non-rotating conditions in a vacuum. The rig has three magnetic bearings as its critical components: two heteropolar radial active magnetic bearings and a magnetic thrust bearing. The bearing configuration allows full vertical rotor magnetic suspension along with a feedforward control feature, which enables the excitation of various modes of vibration in the bladed disk test articles. The theoretical, mechanical, electrical, and electronic aspects of the rig are discussed. Also presented are the forced-excitation results of a fully levitated, rotating and non-rotating, unbladed rotor and a fully levitated, rotating and non-rotating, bladed rotor in which a pair of blades were arranged 180° apart from each other. These tests include the “bounce” mode excitation of the rotor in which the rotor was excited at the blade natural frequency of 144 Hz. The rotor natural mode frequency of 355 Hz was discerned from the plot of acceleration versus frequency. For non-rotating blades, a blade-tip excitation amplitude of approximately 100 g A⁻¹ was achieved at the first-bending critical (≈144 Hz) and at the first-torsional and second-bending blade modes. A blade-tip displacement of 1.778×10⁻³m (70 mils) was achieved at the first-bending critical by exciting the blades at a forced-excitation phase angle of 90° relative to the vertical plane containing the blades while simultaneously rotating the shaft at 3000 rpm.