Geometrical and electrical optimization of NS-SDBD streamwise plasma heat knife for aircraft anti-icing

Ice accretion on aircraft encountering supercooled water droplets in clouds poses great risks to flight performance and safety. With the aim of optimizing the newly developed streamwise plasma heat knife method for anti-icing, a parametric investigation is carried out in this work. The influence of the detailed voltage profile on the heating effects of a Surface Dielectric Barrier Discharge driven by Nanosecond Pulses (NS-SDBD) is investigated, and a comparison of the anti-icing performance among different configurations of streamwise plasma heat knife is made. The results show that columnar high-temperature regions produced by a multi-streamer discharge appear at small pulse rise time, but become diffuse as the pulse rise time increases. An optimal pulse rise time exists to provide a wide range and high value of temperature, which is found to be 150 ns for the setup in the present study. The influence of the pulse fall time is much weaker than that of the rise time. The range and value of the temperature decrease with increasing pulse fall time. A greater pulse width is found to improve the heating effect by increasing the discharge power. When a spanwise electrode is placed connecting the streamwise electrodes of the streamwise plasma heat knife at the airfoil leading edge, the anti-icing performance becomes poorer, whereas good performance is achieved when the spanwise electrode is at the edge of the streamwise electrodes. Based on this, a three-level configuration of the plasma heat knife is proposed, and its anti-icing performance is found to be much better than that of the original configuration.     

低速三角翼纳秒脉冲等离子体激励实验

在30m/s来流速度下,进行了纳秒脉冲介质阻挡放电等离子体气动激励改善47°后掠角钝前缘三角翼气动特性的测力实验.为寻求优化的激励位置,实验研究了5种不同激励位置的流动控制效果.实验结果表明:激励位置对流动控制效果有决定性影响,位于三角翼前缘的等离子体气动激励能有效改善三角翼的气动特性,推迟失速,而上翼面不同展向位置的等离子体气动激励的流动控制效果十分微弱;激励频率是流动控制效果的重要影响因子,激励电压峰峰值为13kV时,激励频率为200Hz下的流动控制效果最好,在迎角30°时可使升力系数由1.31增大到1.44,增大9.6%,升阻比提高3.3%.     

毛细管放电型脉冲等离子体推力器输出特性分析

为了研究毛细管放电型脉冲等离子体推力器输出特性,借助电学诊断手段展开实验研究,获得了推力器典型放电波形,系统研究了不同毛细管内径和施加电压对等离子体等效阻抗、沉积能量效率的影响规律。利用微冲量测量台架,测试了不同参数下毛细管推力器输出元冲量,并通过计算获得了推力器比冲、总体效率的变化规律。实验结果表明,当毛细管内径不断增大时,能量沉积效率不断下降,元冲量下降,比冲降低。主电容电压增大时,放电能量不断增大,能量沉积效率降低,元冲量和单次等效烧蚀质量不断增大,但推力器比冲和总体效率均先增加并趋于稳定。当毛细管腔体长度为16mm,内径3mm,主电容2.5μF,充电电压为2kV时,输出元冲量350.79±7.50μN?s,比冲531s,总体效率可达18.3%。     

Experimental characteristics of a two-electrode plasma synthetic jet actuator array in serial

Plasma Synthetic Jet (PSJ) actuators have shown wide and promising application prospects in high-speed flow control, due to their advantages including high exhaust speed, wide frequency band, rapid response, and non-moving components. Although previous studies on PSJ actuators are abundant, most of them have focused on the performance of a single actuator. However, in practice, an actuator array is very necessary for large-scale aerodynamic actuation on account of the small affected area of a single PSJ. In this paper, the characteristics of a two-electrode plasma synthetic jet actuator array in serial are investigated experimentally. Compared to a parallel actuator array, the serial actuator array requires simpler power supply design and is much easier to realize. High-speed photography of the discharge evolution, voltage-current measurement, and shadowgraphy visualization are used in the investigation. Experimental results show that, for the serial actuator array, weak discharges happen firstly between energized and suspending electrodes, and then a strong pulse arc discharge is triggered. The breakdown voltage in serial is irrelevant to such factors as the number of actuators, the maximum or minimum gap in serial, the connection sequence, etc. It is mainly determined by the sum of gaps. For serial actuators with the same anode-to-cathode spacing, the energy deposition is the same, and the jet is synchronous and similar. Because of the entrainment and merging of adjacent jet vortices, the jet front speed of an aligned synchronous jet array increases as the orifice distance decreases. To achieve the highest jet front velocity, the orifice of the actuator has an optimal diameter.     

基于求解校验序列的(n,k,m)卷积码盲识别

针对卫星通信和深空探测等采用的(n,k,m)卷积码盲识别问题,提出了一种新的识别方法。首先,根据卷积码本身的线性约束关系改进分析矩阵模型的构造方法,有效地减小了识别所需数据量。在通过矩阵化简识别出码长、码字起始位置和校验序列基础上,提出了由校验序列推导出生成多项式矩阵的方法,进而完成卷积码的识别。仿真实例表明,该识别方法不需要任何先验条件,能够有效识别所有(n,k,m)卷积码。     

齿形几何参数对直通篦齿封严泄漏特性影响的正交实验

针对影响直通篦齿泄漏特性的6个主要几何参数(齿宽、封严间隙、齿高、齿距、前倾角和后倾角)及其常用的取值范围,依据正交原理设计了25个篦齿实验件,实验研究了其对泄漏特性的影响.结果表明:上述参数对流量系数的影响趋势有明显的区别;根据实验结果推断:封严效果最好的齿形结构为齿宽取0.1mm、封严间隙取0.3mm、齿高取3mm、齿距取9mm、前倾角取0°、后倾角取15°;上述参数在实验范围内的变化对流量系数影响程度的主次排序为:齿距→封严间隙→后倾角→齿宽→齿高→前倾角,齿距影响非常显著,封严间隙影响显著,后倾角和齿宽有一般影响,齿高和前倾角影响不显著.      

完全互补序列在MIMO雷达中的应用

多输入多输出(MIMO,Multiple-Input Multiple Output)雷达系统采用多天线方式,利用发射信号之间的正交性提高系统性能,但传统的单码序列之间不能满足完全正交(自相关和互相关旁瓣全为0)的特性,影响了系统性能.针对上述问题,结合完全互补序列的特点,推导了完全互补序列模糊函数的数学表达式,进行了相应的计算机仿真,仿真结果充分验证了模糊函数的有效性;并对基于完全互补序列的雷达速度分辨率进行了分析.另外,研究了完全互补序列在MIMO雷达中的应用问题,并建立基于完全互补序列的MIMO雷达信号模型,结果表明:完全互补序列在MIMO雷达中具有很好的应用前景,同时验证了完全互补序列在MIMO雷达应用中的合理性和正确性.     

空间次生环境研究及探测方法概述

文章基于空间次生环境及其效应定义,分别结合不同次生环境阐述了国内外在磁场作用下带电粒子对航天器的影响、航天器非金属材料出气的影响、航天器与空间等离子体相互作用影响、航天器发动机羽流效应和航天器舱内电子环境及效应等的研究状况,并有针对性地开展了典型的发动机羽流效应、放电监测系统和航天器自身磁场分布探测研究。     

航空锂电池的原理及容量测试方法

鉴于锂电池与传统的碱性或酸性电瓶的地面维护不同,本文在说明锂电池原理的基础上,论述了航空锂电池在地面充放电和容量检测的要求和方法,供维护人员参考.     

Trajectory optimisation in electrical discharge machining of three-dimensional curved and twisted channels

Numerical control electrical discharge machining(NC EDM) is one of the most widely used machining technologies for manufacturing a closed blisk flow path, particularly for three-dimensional(3D) curved and twisted flow channels. In this process, tool electrode design and machining trajectory planning are the key factors affecting machining accessibility and efficiency. Herein, to reduce the difficulty in designing the electrode and its motion path in the closed curved and twisted channels, a heur...