Flow field generated by a dielectric barrier discharge plasma actuator in quiescent air at initiation stage

A single Dielectric Barrier Discharge (DBD) plasma actuator driven by Alternating Current (AC) power, capable of inducing a starting vortex and a wall jet in quiescent air, is suited for low-Reynolds-number flow control. However, the starting vortex and the wall jet are usually observed after the plasma actuator has been operated for dozens of and hundreds of cycles of the voltage, respectively. The detail of the induced flow field at the initiation stage of the plasma actuator has rarely been addressed. At the initiation stage, a thin jet that provides the impetus for the entrainment of the induced flow at the beginning of the plasma actuation is first observed by using a high-accuracy phase-lock Schlieren technique and a high-speed Particle Image Velocimetry (PIV) system. This is the initial form of the momentum transfer from the plasma to the fluid. Then, an arched type jet is created by the plasma actuator. In addition, the whole development process of the induced flow field from the starting point of the thin jet to the quasi-steady stage of wall jet is presented for providing a comprehensive understanding of the plasma actuator and proposing a relevant enhancement of the numerical simulation model.     

喷气燃料热氧化安定性对航空发动机燃油系统沉积物生成的影响研究

利用HiReTS试验机[1]模拟发动机燃油系统,对喷气燃料沉积物的生成进行了研究。试验结果表明:加入自行研制的高热安定性添加剂,可有效提高喷气燃料的热氧化安定性;使用提高热氧化安定性的喷气燃料可以显著减少燃油系统沉积物的生成,从而延长发动机的使用寿命。     

多用途战斗机/涡扇发动机一体化循环参数优化

 针对多用途战斗机的特点,发展了基于飞/发一体化的涡扇发动机循环参数优化设计模型和相应的计算程序,优化设计模型中包括双变量控制涡扇发动机特性计算模型、进排气系统安装特性计算模型、飞机气动特性分析模型、重量组成分析模型、任务剖面分析模型、约束分析与任务分析模型和优化计算模型等。重点研究了多用途战斗机约束边界的获得方法,利用多岛遗传算法和自适应模拟退火优化算法,分别对现役多用途战斗机、不加力超声速巡航多用途战斗机以及下一代先进多用途战斗机用涡扇发动机循环参数进行了优化计算,对计算结果进行了分析,获得了对多用途战斗机用涡扇发动机循环参数选择有指导意义的结论。     

基于动态RCS的隐身飞机探测概率研究

动态RCS是影响战斗机突防概率的重要因素。围绕动态RCS这一关键要素,建立了空空动态RCS求解模型,得到了典型机动下战斗机的动态RCS变化规律,并分析了基于动态RCS的典型机动下的雷达探测概率。基于仿真的静态RCS数据库,耦合飞机抖动模型,研究了拉升机动、空间机动以及空空对抗下某型隐身飞机的动态RCS。通过仿真发现:战斗机的机腹、垂尾及尾喷管部位RCS较大,从而导致了较高的探测概率;对于拉升机动,保持较大的航路捷径更有利于隐蔽突防。     

亚声速矩形射流的噪声辐射特性和声源分布

基于射流噪声模拟试验台，对出口面积相同的圆形喷口及宽高比分别为1、1.5、2、10的矩形喷口亚声速射流的远场噪声辐射特性和噪声源分布位置进行了较为系统的研究。通过远场噪声测量，获得了不同宽高比矩形喷口在不同方位角平面的射流噪声频谱分布结果相对于圆形射流的差异，揭示了矩形射流潜在的降噪潜力。通过基于波束成形算法的传声器阵列，得到了矩形射流噪声源峰值位置随频率的变化情况，系统分析了射流速度、方位角、宽高比等参数对矩形射流噪声源分布的影响。射流速度和方位角对矩形射流噪声源分布的归一化结果影响很小，而宽高比对矩形射流噪声源分布有较大影响：随着矩形宽高比的增加，矩形射流低频段噪声源向上游偏移，高频段噪声源向下游偏移。     

单喷管火箭自由喷流噪声数值模拟

利用非定常燃气流场数值模拟方法，研究超声速喷流核心区及其外围亚声速区燃气流动态分布和流动特性，在此基础上利用欧拉方程条件的伽辽金有限元方法以及FWH方法，实现并完成喷流噪声传播特性、辐射特性数值模拟。喷流噪声数值模拟结果显示：燃气流推进初期，强喷流噪声区域紧随燃气流前锋；燃气流场相对稳定后，强喷流噪声区域主要位于燃气流等能区末稍，一些小尺度试验的燃气流激波系附近也存在较强喷流噪声。这些强喷流噪声主要由燃气流前锋带动的大涡动态卷吸、燃气流强湍流脉动以及激波扰动引起。受数值模拟网格分辨率影响，当前仅能保持中低频段声压级数值模拟结果与实测结果总体接近。     

Numerical investigation on jet interaction with a compression ramp

A numerical investigation on jet interaction in supersonic laminar flow with a compres- sion ramp is performed utilizing the AUSMDV scheme and a parallel solver. Several parameters dominating the interference flowfield are studied after defining the relative increment of normal force and the jet amplification factor as the evaluation criterion of jet control performance. The computational results show that most features of the interaction flowfield between the transverse jet and the ramp are similar to those between a jet and a flat plate, except that the flow structures are more complicated and the low-pressure region behind the jet is less extensive. The relative force increment and the jet amplification factor both increase with the distance between the jet and the ramp shortening till quintuple jet diameters. Inconspicuous difference is observed between the jet-before-ramp and jet-on-ramp cases. The variation of the injection angle changes the extent of the separation region, the plateau pressure, and the peak pressure near the jet. In the present computational conditions, 120 is indicated relatively optimal among all the injection angles studied. For cold gas simulations, although little influence of the jet temperature on the pressure distribution near the jet is observed under the computation model and the flow parameters studied, reducing jet temperature somehow benefits the improvement of the normal force and the jet efficiency. When the pressure ratio of jet to freestream is fixed, the relative force increment varies little when increasing the freestream Mach number, while the jet amplification factor increases.     

纳米胶体射流抛光技术综述

纳米胶体射流抛光技术是一种超光滑表面加工方法,加工范围广,具有广泛的应用前景。本文回顾了纳米胶体射流抛光技术的提出以及目前的研究现状,最后对其今后的发展进行了简单展望。     

公务机机翼气动外形优化研究

随着世界经济贸易的发展,轻中型公务机愈发受到客户的青睐。为了进一步提升高速涡扇公务机的总体气动性能,本文采用基于全速势方程（TRANAIR）的流场快速求解方法,集成序列二次规划（SQP）优化算法和类函数/型函数变换（CST）自由变形（FFD）技术,对某轻中型高速涡扇公务机机翼进行多点优化设计研究,并对优化结果进行对比分...     

Estimation method of domestic advanced fighter＇s fly-away cost

由于年代上的差别、技术水平的提高和国内外研发体制的不同,国外已有的成熟估算模型不能直接用于国内先进战斗机（三代以上的战斗机）的出厂费用估算.针对这种问题,研究了国内外军工体制的差异、先进战斗机的新技术特征和研制过程的新特点对费用产生的影响,将研制体制、引进仿制、航电技术升级、改进改型和研制周期拖延5种因素考虑到费用计算当中.根据战斗机出厂费用数据统计,以Burns估算模型为基础,引入了相关的＂费用因子＂,采用比例缩放、最小误差等方法,建立了一种国内先进战斗机出厂费用估算的新模型.以国外先进战斗机和国内三型战斗机作为算例,验证了新模型的有效性和实用性.