高超声速化学非平衡粘性激波层方程的数值解

本文讨论了高超声速粘性激波层方程数值计算时差分格式引起的物理失真问题。具体分析了全隐格式格式粘性的影响,并作了数值试验。为了验证隐式结果的可靠性。在超声速激波风洞中测量了钝锥的表面压力分布,并与计算结果作了比较,两者基本一致。 本文采用隐式有限差分法数值计算了高超声速化学非平衡粘性激波层绕细长球锥的流动。计算时采用连续方程和法向动量方程耦合求解的方法以解决细长体远后身区计算中的问题。应用网格技术和加强系数矩阵主对角元素优势的方法提高了化学非平衡流计算的雷诺数范围。文中给出了高超声速化学非平衡流的计算结果,并与其它文献的结果作了比较。     

近空间高超声速流场通量分裂型DSMC-IP方法

针对近空间高超声速流场的特点,采用Van Leer格式对直接模拟蒙特卡洛-信息保存(DSMC-IP)方法质量守恒方程中的计算格式进行改进.将局部马赫数作为分裂通量的标准,并重构单元分界面两侧的左右输运通量,使得计算格式具有通量分裂的特点,解决了DSMC-IP方法在高超声速流场计算中的应用问题.将改进后的通量分裂型DSMC-IP方法引入非结构网格中,对二维近空间高超声速流场进行数值模拟.计算结果表明:通量分裂型DSMC-IP方法所得出的数值结果与实验值及参考值符合较好,明显降低了直接模拟蒙特卡洛(DSMC)方法所带来的统计耗散.当来流气体的稀薄程度增加时,其非平衡效应也更加明显,而通量分裂型DSMC-IP方法的计算结果与参考值相差均在10%以内,良好地反映了非平衡条件下的流场特征,验证了通量分裂型DSMC-IP方法的可行性和有效性.      

任意单元间断Galerkin有限元计算方法研究

基于龙格库塔间断Galerkin(RKDG)有限元法的构造思想,通过局部坐标变换,发展了非正交单元DG有限元计算方法;借鉴非结构网格有限体积隐式计算方法,发展了适应于DG有限元方法的隐式计算方法;借鉴一维和二维(三角形单元)DG有限元限制器构造方法,提出了非正交三棱柱单元限制器方法;利用上述方法数值模拟了球头和双椭球的高超声速粘性绕流,得到了清晰的流场结构,并得到了较好的压力和热流分布,表明该方法在复杂高超声速流动的数值模拟方面具有广阔的应用前景。     

三阶HWCNS的构造及其在高超声速流动中的应用

对网格质量要求高、计算稳定性差和计算效率低是制约高阶精度格式应用于高超声速复杂流动模拟的重要因素。针对这些问题,发展了三阶精度的混合节点半节点加权紧致非线性格式(HWCNS3),改进其光滑测试因子和非线性权得到了HWCNS3-OP,并给出了它们的频谱特性。利用Lax和Osher-Shu算例测试了格式对间断和高频波的捕捉能力;通过钝锥和航天飞机的高超声速绕流算例,考察了HWCNS3-OP在真实流动模拟中热流和气动力的预测精度及其计算效率。研究结果表明:HWCNS3-OP具有较高的分辨率和良好的间断捕捉能力,高频波捕捉能力相对HWCNS3提高了约3倍,相对守恒律的单调迎风中心格式(MUSCL)提高了约4倍;HWCNS3-OP计算稳定性较好,计算效率相对五阶HWCNS提高了2~3倍,HWCNS3-OP是一种较适合高超声速复杂流动模拟的高阶精度格式。     

高超声速湍流直接数值模拟技术

概述了近年来国内外高超声速湍流直接数值模拟(DNS)技术方面最新的研究进展,主要集中在高精度、高鲁棒性数值方法方面,同时也介绍了近年来典型的高超声速湍流DNS算例。在数值方法方面,主要介绍了高精度激波捕捉格式以及保持计算稳定的数值技术,重点是WENO格式及高阶保单调格式的最新进展。在高超声速湍流DNS算例方面,介绍了压缩性影响、壁温影响、真实气体效应以及高超声速转捩等方面的DNS研究。此外,还简要介绍了作者开发的可压缩高精度计算流体力学软件OpenCFD。     

一种适用于热流计算的改进WENO格式

数值格式是影响高超声速热流数值计算准确度的主要因素之一.根据高超声速流场的特性合理的控制了数值黏性,对WENO(weighted essentially non-oscillatory)格式进行了改进,使其适用于高超声速热流计算.研究结果表明:改进后的格式在捕捉激波时具有良好的激波辨率,在壁面附近尽量减小了数值黏性,提高了格式的黏性分辨率.数值试验也表明了这种改进算法的有效性.      

二维Euler方程的自适应网格矢通量算法

给出了二维轴对称欧拉方程的自适应网格隐式矢通量分裂差分格式和模拟结果,隐式矢通量分裂格式不需人工粘性项与人工耗散项,可以计算跨声速流场,也可以较准确地捕获激波,利用流场解的梯度信息对网格进行调整,可以提高激波的捕获精度,算例表明,该方法精度高稳定性好,不依赖于初始条件。     

低耗散高可信度格式及其在气动力热计算中的应用

本文简要介绍了TVD类型格式中近似黎曼解的耗散机理,该耗散机制对于粘性问题的计算有较大的负面影响.通过引入低耗散的格式,所发展的数值方法对粘性流场的气动力热问题的计算具有较高的精度.以该数值方法为基础发展的软件系统,在亚跨超和高超声速领域中的气动力热问题上均得到了验证,计算结果与实验进行了对比验证,表明该计算软件系统具有较高的可信性.     

烧蚀对再入体绕流电子数密度影响的数值研究

从化学非平衡NS方程或其简化形式(粘性激波层方程、PNS方程)出发,采用分区求解的方法数值模拟含泰氟隆烧蚀产物的高超声速再入体流场.首先计算分析了RAM-C飞行试验状态和一个考核算例,对计算方法和程序作了初步验证.其次耦合烧蚀壁面边界条件和流体控制方程,采用19组分28个反应的化学反应模型,对有、无烧蚀情况下高超声速钝锥体再入绕流及底部流场进行了数值模拟,深入分析了烧蚀产物对再入流场电子数密度及温度分布的影响.     

高超声速热化学非平衡钝体绕流数值模拟

对高超声速热化学非平衡钝体绕流进行研究,发展了高温热化学非平衡条件下的高超声速气动热数值模拟方法。采用二阶精度迎风TVD格式的N-S方程有限体积法多块结构网格求解器,考虑了空气5组分及化学非平衡效应的影响,对组分生成源项及振动能源项采用了点隐式的处理,提高了计算效率。对球锥模型和RAM-CII飞行实验等算例进行了数值气动热模拟,分析了不同非平衡模型在热化学非平衡条件下流场的影响。计算结果表明建立的数值模拟方法具有较高的精度。     

The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow

This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation.      

Research on Auto-detection for Remainder Particles of Aerospace Relay Based on Wavelet Analysis

Aerospace relay is one kind of electronic components which is used widely in national defense system and aerospace system. The existence of remainder particles induces the reliability declining, which has become a severe problem in the development of aerospace relay. Traditional particle impact noise detection (PIND) method for remainder detection is ineffective for small particles, due to its low precision and involvement of subjective factors. An auto-detection method for PIND output signals is proposed in this paper, which is based on direct wavelet de-noising (DWD), cross-correlation analysis (CCA) and homo-filtering (HF), the method enhances the affectiv-ity of PIND test about the small particles. In the end, some practical PIND output signals are analysed, and the validity of this new method is proved.     

Preparation of Highly Dispersed Antimony-doped Tin Oxide Nano-powder via Ion-exchange Hydrolysis of SnCl4 and SbCl3 and Azeotropic Drying

Antimony-doped tin hydroxide colloid precipitates have been synthesized by hydrolysis of SnCl4 and SbCl3 using: (1) an ion-exchange hydrolysis to remove chlorine ions, and (2) isoamyl acetate as an azeotropic solvent to obviate water. The obtained dried powder is of high dispersivity without any need for further grinding. The size and dispersivity of the final particles are investigated with the aid of TG-DTA, BET, XRD and TEM. After having calcined, the antimony-doped tin oxide nanopowder possesses a tetragonal rutile structure with high dispersivity, uniform particles and low hard agglomeration.     

Effects of Mo on the Microstructure and Hydrogen Sorption Properties of Ti-Mo Getters

The effects of Mo on the microstructure evolution, porosity and hydrogen sorption properties of Ti-Mo getters are investigated in this work. The results show that the addition of Mo prolongs the densification process of Ti-Mo getters and results in a significant amount of sintered pores. With the Mo content increasing, the porosity of getters firstly increases reaching the maximum value as it at- tains about 7.5wt.%, and then drops. At the room temperature, the hydrogen sorption property of getters increases progressively with the Mo content increasing, but the tendency is not very clear before its content lies below 2.5wt.%. When the Mo content achieves about 7.5wt.%, the hydrogen sorption property proves to be the best. The discussion is made about the above mentioned phenomena inclusive of hydrogen sorption properties of getters under different activation conditions (from 500-750 ℃).     

超声速燃烧数值模拟中的湍流与化学反应相互作用模型

高精度数值模拟有助于理解超声速湍流燃烧中湍流与化学反应的相互作用,可为发动机燃烧室等工程应用设计提供可靠的预测模型。除直接数值模拟外,目前在湍流燃烧应用中使用的大涡模拟和雷诺平均Navier-Stokes模拟均需要借助模型模化发生在湍流小尺度上的流动与化学反应过程对湍流大尺度运动的影响。现有的湍流与化学反应相互作用模型大致可分为:火焰面类模型和概率密度函数类模型,2类模型在不同的应用中各自具有优势和局限性。此外,现有模型大都基于低马赫数燃烧,而超声速燃烧中通常会伴随快速混合、局部熄火和再着火以及激波等复杂过程,这为发展其中的湍流与化学反应相互作用模型提出了更多的挑战。     

适于低轨卫星IP网络的单核共享树组播算法(英文)

为了解决低轨卫星IP网络中现有典型源组播算法的信道资源浪费问题,本文提出了一套单核共享树组播算法,即核心群合并共享树(CCST)和加权核心群合并共享树(w-CCST)算法。CCST 算法包括动态近似中心(DAC)选核方法和核心群合并组播路径构建方法。DAC方法专为周期、规律运动的低轨卫星网络提出,不需要复杂的星上计算。在核心群合并方法中,以核节点作为初始核心群,通过核心群和剩余组成员的最短路径方法逐步扩展直至整棵组播树构建完成,从而使得组播树的树代价最小,大大提高了网络的带宽利用率和组播传输效率。w-CCST 算法中所提出的加权因子可以调整树代价和端到端传播时延之间的折衷程度,因此,可以通过调整加权因子来适度增大树代价、降低端到端传播时延以支持某些端到端时延要求苛刻的实时组播业务。最后,与低轨卫星 IP 网络中典型算法进行了性能比较,仿真结果说明,CCST 算法的平均树代价比其它算法显著降低,w-CCST 算法的平均端到端传播时延小于 CCST 算法。     

Jet Vectoring Control Using a Novel Synthetic Jet Actuator

A primary air jet vectoring control system with a novel synthetic jet actuator (SJA) is presented and simulated numerically. The results show that, in comparison with an existing traditional synthetic jet actuator, which is able to perform the duty of either “push” or “pull”, one novel synthetic jet actuator can fulfill both “push” and “pull” functions to vector the primary jet by shifting a slide block inside it. Therefore, because the new actuator possesses greater efficiency, it has potentiality to replace the existing one in various appli- cations, such as thrust vectoring and the reduction of thermal signature. Moreover, as the novel actuator can fulfill those functions that the existing one can not, it may well be expected to popularize it into more flow control systems.     

Nonlinear Adaptive Slewing Motion Control of Spacecraft Truss Driven by Synchronous V-gimbaled CMG Precession

The slewing motion control of a truss arm driven by a V-gimbaled control-moment-gyro (CMG) is a nonlinear control problem. The V-gimbaled CMG consists of a pair of gyros that must precess synchronously. The moment of inertia of the system, the angular momentum of the gyros and the external disturbances are not exactly known. With the help of feedback linearization and recursive Lyapunov design method, an adaptive nonlinear controller is designed to deal with the unknown items. Performance of the proposed controller is verified by simulation.     

An SOR Implicit Time-accurate Scheme in Calculating Unsteady Flows

A new time-accurate marching scheme for unsteady flow calculations is proposed in the present work. This method is the combination of classical Successive Over-Relaxation (SOR) iteration method and Jacobian matrix diagonally dominant splitting method of LUSGS. One advantage of this algorithm is the second-order accuracy because of no factorization error. Another advantage is the low computational cost because the Jacobian matrices and fluxes are only calculated once in each physical time step. And, the SOR algorithm has better convergence property than Gauss-Seidel. To investigate its accuracy and convergency, several unsteady flow computa- tional tests are carried out by using the proposed SOR algorithm. Roe’s FDS scheme is used to discritize the inviscid flux terms. Un- steady computational results of SOR are compared with the experiment results and those of Gauss-Seidel. Results reveal that the numerical results agree well with the experimental data and the second-order accuracy can be obtained as the Gauss-Seidel for unsteady flow computations. The impact of SOR factor is investigated for unsteady computations by using different SOR factors in this algorithm to simulate each computational test. Different numbers of inner iterations are needed to converge to the same criterion for different SOR factors and optimal choice of SOR factor can improve the computational efficiency greatly.