Two-stream instability generation in the lunar ionosphere

The Two-stream Instability (TSI) generation is studied analytically in the lunar ionosphere. The TSI is a tiny perturbation in the electron plasma density, due to which an electric field grows with time and this growth is facilitated by the electron plasma in the background. In lunar ionosphere, the TSI comes into existence when the solar wind interacts unhindered with the tenuous lunar electron plasma in the surface bound exosphere. In this study, the conditions which allow the TSI to form and the subsequent instability growth with time i.e. the growth factor, is estimated. Initially, the threshold condition for the TSI to take place is determined. Thereafter, the solar wind and lunar plasma parameter contribution to trigger TSI is investigated along with the effect of these parameters in the evolution of TSI. The plasma TSI evolution with the passage of time is also depicted in phase space diagram with Particle-In-Cell simulations.     

部分球壳分布离子流激发的电磁不稳定性

在离子环束流和低频电磁波相互作用的过程中廓了环束流将演化成具有投掷角展宽的部分球壳速度分布离子流,其投掷角展宽随时间增大,低频右旋电磁不稳定性增长率峰值,总的说来也逐渐增大,并向高频短波方向移动,与此相反,低频左旋电磁不稳定性增长率峰值,当投掷 角展宽等于０时,大于右旋不稳定性峰值,但随着投掷角展宽增加而迅速低于右 性增长率峰值,并向工波方向移动。     

Reliability-based trajectory optimization using nonintrusive polynomial chaos for Mars entry mission

This paper presents the reliability-based sequential optimization (RBSO) method to settle the trajectory optimization problem with parametric uncertainties in entry dynamics for Mars entry mission. First, the deterministic entry trajectory optimization model is reviewed, and then the reliability-based optimization model is formulated. In addition, the modified sequential optimization method, in which the nonintrusive polynomial chaos expansion (PCE) method and the most probable point (MPP) searching method are employed, is proposed to solve the reliability-based optimization problem efficiently. The nonintrusive PCE method contributes to the transformation between the stochastic optimization (SO) and the deterministic optimization (DO) and to the approximation of trajectory solution efficiently. The MPP method, which is used for assessing the reliability of constraints satisfaction only up to the necessary level, is employed to further improve the computational efficiency. The cycle including SO, reliability assessment and constraints update is repeated in the RBSO until the reliability requirements of constraints satisfaction are satisfied. Finally, the RBSO is compared with the traditional DO and the traditional sequential optimization based on Monte Carlo (MC) simulation in a specific Mars entry mission to demonstrate the effectiveness and the efficiency of the proposed method.     

Dynamic parametric modeling-based model updating strategy of aeroengine casings

For accurate Finite Element (FE) modeling for the structural dynamics of aeroengine casings, Parametric Modeling-based Model Updating Strategy (PM-MUS) is proposed based on efficient FE parametric modeling and model updating techniques regarding uncorrelated/correlated mode shapes. Casings structure is parametrically modeled by simplifying initial structural FE model and equivalently simulating mechanical characteristics. Uncorrelated modes between FE model and experiment are reasonably handled by adopting an objective function to recognize correct correlated modes pairs. The parametrized FE model is updated to effectively describe structural dynamic characteristics in respect of testing data. The model updating technology is firstly validated by the detailed FE model updating of one fixed–fixed beam structure in light of correlated/uncorrelated mode shapes and measured mode data. The PM-MUS is applied to the FE parametrized model updating of an aeroengine stator system (casings) which is constructed by the proposed parametric modeling approach. As revealed in this study, (A) the updated models by the proposed updating strategy and dynamic test data is accurate, and (B) the uncorrelated modes like close modes can be effectively handled and precisely identify the FE model mode associated the corresponding experimental mode, and (C) parametric modeling can enhance the dynamic modeling updating of complex structure in the accuracy of mode matching. The efforts of this study provide an efficient dynamic model updating strategy (PM-MUS) for aeroengine casings by parametric modeling and experimental test data regarding uncorrelated modes.     

基于涡系相交不稳定性的飞机尾流控制方法

在飞机飞行的过程中尾涡会伴随着升力产生,威胁后机的飞行安全.在简化机翼模型上添加扰流片,通过一个矩形翼以引入一个与主翼尾涡大小不同、方向相反的小涡,构建尾流自消散四涡系统,以期诱发尾涡的Rayleigh-Ludwig相交不稳定性.通过改变扰流片的大小形状,调整模型的攻角和拖曳速度,采用粒子图像速度场仪测量系统定量研究在低雷诺数下单主翼尾涡发展特性以及双涡相互作用特性.研究表明:在未添加扰流片时,尾涡环量在45个翼展内相对于初始环量基本保持不变;在添加扰流片的情况下尾涡的环量衰减可以达到35%~55%,而未添加的基本翼型的尾涡的环量则几乎保持不变,这说明添加适当的扰流片能诱发尾涡的Rayleigh-Ludwig相交不稳定性,加速尾涡的消散,当小涡和主涡的初始环量比为-0.489、初始距离比为0.5时,45个翼展范围内,尾涡环量衰减55.9%.本文系统性的实验结果可以为低尾流机翼的设计提供参考依据.      

轴向通流旋转盘腔内流动不稳定性研究

为了研究旋转腔内流动不稳定性问题,采用旋转坐标系稳态方程,用数值模拟的方法分析了轴向通流旋转盘腔内的流动,得到了旋转系下哥氏力和离心浮升力分别对流动不稳定的作用,以及这两个力的非线性综合作用对流动不稳定的影响.结果表明:哥氏力是恢复力,不影响流动稳定性;离心浮升力是造成流动不稳定的主要因素,盘腔内的流动是离心力场下的Rayleigh-Benard对流和强迫对流的混合流,随着浮升力的增强流动由稳态发展为非稳态;哥氏力与离心浮升力的综合作用加剧了流动不稳定性,盘腔内r-θ面出现了明显的旋向相反的对涡.     

磁暴对赤道地区L波段电离层闪烁的影响研究

利用赤道地区Vamimo站闪烁数据, 选取两次典型大磁暴时段重点分析, 对比磁暴发生前、发生时以及发生后连续几天电离层幅度闪烁强度和发生率的变化, 引入瑞利elax-elax泰勒不稳定性(Rayleigh-Taylor, R-T不稳定性)线性增长率γ₀, 对磁暴影响闪烁的机制进行初步探讨. 结果表明, 磁暴可能触发闪烁发生, 也可能抑制闪烁发生, 这既与观测季节有关, 也与磁暴不同发展阶段的地方时有关. 触发发生于闪烁少发季节磁暴主相所在的午夜至黎明时段, 可能是磁层穿透电离层的东向电场所致; 抑制发生于闪烁多发季节磁暴恢复相所在的午夜前时段, 可能是西向电场作用的结果. 磁暴发生时的电场变化可能是抑制或触发闪烁的主导因素, 但仍需进一步分析研究.      

基于虚拟仪器的数字式气动失稳仿真系统的研制与应用

设计了基于航空发动机动态压力失稳特征的数字式仿真系统,重点阐述了基于虚拟仪器技术仿真系统的优化搭建过程及其关键技术,并在某型涡扇发动机消喘系统研制过程中成功地进行了应用。结果表明,新的优化方案能对发动机的失稳特征进行有效控制,其实时性和适用性均有实质提高。     

初始扰动对于气液界面Rayleigh-Taylor不稳定性发展的影响

利用果冻实验技术研究几种不同初始扰动的气液界面Rayleigh-Taylor不稳定性发展过程。通过对不同波长和振幅的实验结果进行对比发现：波长是影响界面扰动发展的主要因素,并且在不同阶段影响的模式不同。在线性阶段,波长较短的扰动发展较快;在非线性阶段,则是波长较长的扰动发展较快。     

利用一种声学阀门对发动机燃烧不稳定性进行的被动控制(英文)

为了对发动机燃烧不稳定性进行被动控制,利用亥姆赫兹声学共振器原理,设计一种声学阀门,当一个管道侧面安装的亥姆赫兹共振器的空腔壁面是柔软的时候,声学阀门的性能与频率就没有很强的关系,从而实现由于热声学不稳定带来的压力和热释放导致的不稳定燃烧进行被动控制。阀门的功能是让声音通过,但它必须阻止时间平均意义上的流动。本文对带有这种装置的热声学特征根问题给出数值解。结果显示声学阀门对燃烧室内的驻波结构造成很大改变,进而可以消除不稳定的特征根模态。只要阀门具备足够的尺寸,这种效果可以在任意的线性火焰声学特性中广泛实现。