Thermocapillary simulation of single bubble dynamics in zero gravity

The lack of significant buoyancy effects in zero gravity conditions poses an issue with fluid transfer in a stagnant liquid. In this paper bubble movement in a stagnant liquid is analysed and presented numerically using a computational fluid dynamics (CFD) approach. The governing continuum conservation equations for two phase flow are solved using the commercial software package Ansys-Fluent v.13 and the Volume of Fluid (VOF) method is used to track the liquid/gas interface in 2D and 3D domains. The simulation results are in reasonable agreement with the earlier experimental observations, the VOF algorithm is found to be a valuable tool for studying the phenomena of gas–liquid interaction. The flow is driven via Marangoni influence induced by the temperature difference which in turn drives the bubble from the cold to the hot region. A range of thermal Reynolds (Re_T) and Marangoni numbers (Ma_T) are selected for the numerical simulations, specifically Re_T=13–658 and Ma_T=214–10,721 respectively. The results indicate that the inherent velocity of bubbles decreases with an increase of the Marangoni number, a result that is line with the results of previous space experiments (Kang et al., 2008) [1]. An expression for predicting the scaled velocity of bubble has been derived based on the data obtained in the present numerical study. Some three-dimensional simulations are also performed to compare and examine the results with two-dimensional simulations.     

凹槽参数对通气空泡融合的影响

水下航行体通气技术形成的空泡能够有效降低航行阻力并调节运动姿态,但通气空泡在航行体表面不易融合,空泡形态不稳定,因此开展通气空泡的融合控制具有重要工程应用价值。采用有限体积法进行数值计算,研究了航行体孔后开槽对通气空泡融合的控制作用,并探究了不同凹槽参数对通气空泡融合的影响。研究发现,凹槽改变了空泡的流场特性,槽内产生的旋涡卷吸流经凹槽的气体,使槽内气体向航行体周向发展并融合;当槽宽取0.125D,孔槽间距取0.075D时,对空泡融合的促进以及稳压效果最佳。     

Ignition of fuel sprays by shock wave mathematical modeling and numerical simulation

The paper presents the results of developing of physical and mathematical model making it possible to take into account the effect of droplets non-uniformity in space and size distribution on ignition conditions for fuel sprays. The influence of condensed phase volume fraction on ignition and combustion of sprays was studied, physical and mathematical models for multi-phase flows, mixture formation and combustion of liquid fuels based on solving Navier–Stokes equations for gas phase accounting for thermal and mechanical interaction with poly-dispersed droplets array. The problems of particulate phase dynamics are regarded accounting for the interaction with gas phase atomization, evaporation and combustion.It was shown that depending on droplet size distribution and aerosol cloud density different flow scenarios were possible.Several ignition zones could be formed behind incident shock wave depending on mixture properties and initiation parameters. The possibility of numerical simulation permitting variation of definite parameters only made it possible to explain this fact.     

超声速横向气流中喷雾的数值模拟

对超声速横向气流中的喷雾过程进行了数值模拟,采用二维N-S方程计算气相,应用一次雾化模型和二次雾化模型模拟了喷雾雾化过程,并与实验测量结果进行了对比。研究了湍流度和附面层厚度对液雾穿透深度的影响,发现湍流度和附面层厚度并不是主要的影响因素,认为雾化模型是影响液雾穿透深度的关键因素。     

卫星液体晃动气浮台仿真试验系统的运动分析

本文通过边界元数值法求解了部分充液自旋球腔内的液体晃动问题。以流体运动的基本方程和系统运动的Ｅｕｌｅｒ动力学方程为基础，考虑了贮箱偏置、涡旋、重力及Ｃｏｒｉｏｌｉｓ力等因素对流体晃动和系统运动状态的影响，求解出液体的速度场，并在此基础上估算液体的能量耗散率和系统的章动时间常数     

Application of the mechanical oscillator technique to the investigation of EVA decompression

The ultrasonic bubble detection technique has been used as a versatile tool in the investigation of hypobaric decompression procedures for the last two decades. However, this method can only detect relatively large bubbles > 30-50 micrometers (usually in venous blood) and not the very first stages of bubble formation. Recently, the mechanical oscillator technique has been applied in air diving trials in order to detect small blood density changes due to hypothetical fluid shifts. However, sharp density drops were found in the decompression process, and these have been attributed to gas bubble formation. In this study, this method was applied together with Doppler controls to a series of altitude decompressions to 300 and 500 hPa, which represents the range of EVA operational pressures currently used or planned. Six subjects participated in both series; the oscillator sample tube could be pressurized. By the application of pressure on a blood sample containing questionable gas bubbles, these are reduced in volume, like in recompression therapy, and thus the density of the sample is increased. This effect has been shown in all 6 subjects undergoing decompression to 300 hPa, whereas in the 500 hPa series only 3 out of 6 subjects corresponded with gas phase formation immediately after decompression. Typically, Doppler bubbles appeared only after some latency time between 20 and 60 min; after this time, the density effect had nearly vanished. It is concluded that the mechanical oscillator technique represents a complementary research instrument to the Doppler method, because it is able to deliver a quantitative resolution of the early stage of gas phase formation.     

低重力环境下三维液体非线性晃动的数值模拟

本文讨论低重力环境下三维液体非线性晃动问题。采用ＡＬＥ（任意的拉格朗日－欧拉）运动学描述跟踪自由液面；对于ＡＬＥ描述的Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程，在时间域上采用分步离散方法中的速度修正格式进行数值离散，在空间域上利用有限元方法进行了数值离散；推导了考虑表面引力效应时有限元边界条件的弱积分形式；给出了表面张力的数值计算公式。模拟了考虑表面张力情况下圆筒型贮腔中液体的非线性晃动，并得到了贮腔壁面处     

稀疏拟谱最优控制法求解Goddard火箭问题

提出了一种新的基于直接转化法的求解基于常微分方程(ODE)和微分代数方程(DAE)的最优控制问题的数值方法.该方法通过Legendre-Gauss拟谱法同时离散化状态变量和控制变量,把最优控制问题转化为一个非线性规划问题,并利用改进的多相处理方法避免优化无控段,同时基于稀疏矩阵探索其一阶导数信息.数值结果表明,与传统的直接转换法相比,该方法是一种通用高效的精度较高的ODE/DAE最优控制直接数值求解法.最后,从工程观点出发,应用该方法成功求解了终端自由有路径约束的奇异最优控制问题Goddard火箭问题.     

含板类柔性附件的充液航天器动力学研究

对含有板类柔性附件和曲壁轴对称充液储腔的复杂航天器系统进行动力学建模和耦合机理研究。首先,采用Kirchhoff-Love薄板理论对航天器的板类柔性附件进行研究,通过D’Alembert原理得到柔性附件的振动方程,运用模态假设法将混合方程转换为常微分方程。其次,通过推导充液航天器储腔内任意点的运动,得到储腔液体的牵连速度势函数,采用Gauss超几何级数得到液体相对速度势函数的解析形式,通过Hamilton变分原理推导液体晃动的运动方程,以及液体速度势函数模态系数的控制方程。最后采用准坐标Lagrange方程得到耦合航天器系统的状态方程,通过数值仿真校验系统动力学模型的有效性。研究结果表明,刚性平台、液体、柔性附件的相互耦合效应使得航天器系统存在复杂动力学行为,在复杂航天器系统动力学建模过程中需要充分考虑液体晃动和柔性附件振动的影响,柔性附件的安装位置对于耦合航天器系统的动力学行为也有着重要影响。     

线圈炮——电磁同轴发射器及其系统分析

线圈炮在宇航与国防中有重要应用前景。本文先简述其分析模型与方程。方程为非线性变系数常微分方程的初值问题，有时呈刚性。用Ｔｒｅａｎｏｒ方法求解，所得结果与国外已有装置的试验数据符合良好。并对一个小炮做了初步的原理设计。     

Modeling of combustor swirl flows

Swirl is used extensively in gas turbine combustors, principally as a means of controlling flame size, shape, stability and combustion intensity. Rapid progress has been made in recent years in the development of mathematical models of combustor swirl flows which simulate the processes of turbulence, combustion, fuel droplet sprays, radiation and pollutant formation, and solve the resulting equations via a computational procedure, which seeks an optimum path to the solution of the governing set of several simultaneous nonlinear partial differential equations. This paper looks at recent advances in the modeling of combustor swirl flows, its aim being to review the difficulties, discuss developments, demonstrate that useful predictions are already being made, and indicate in what areas further research may be useful.     

外流干扰对气动塞式喷管性能影响的数值模拟研究

本文首先对气动塞式喷管内外流干扰的机理进行了分析，在此基础上对流干扰对气动塞式喷管性能的影响进行了数值模拟研究，数值方法采用NND格式求解二维NS方程，对于不同的背压和来流马赫数条件进行量的数值实验，通过计算揭示了不同外流条件下气动塞式喷管的流动特征以及外流干扰对喷管性能的影响规律，本文的计算结果可以为气动塞式喷管的设计和性能预后提供参考。     

液体火箭发动机涡轮泵转子弯扭耦合振动研究

为获得转子振动特性,针对液体火箭发动机涡轮泵转子系统建立了其在密封流体激振作用下的弯扭耦合动力学模型。通过数值仿真和试验研究了涡轮泵转子系统弯扭耦合振动的动力学特性,结果显示在密封流体激励作用下弯扭耦合振动的非线性特性显著。还研究了偏心距对涡轮泵转子系统弯扭耦合振动的影响。本研究可为液体火箭发动机涡轮泵转子的结构设计、诊断与维护提供可靠信息。     

航天器贮箱大幅液体晃动三维质心面等效模型研究

针对航天器贮箱内的大幅液体晃动建立了三维质心面等效模型,此模型将贮箱内液体等效为位于液体质心处的质点,该质心点可以在质心约束面内任意运动,同时利用质心点动力学方程及接触碰撞模型近似计算液体晃动对贮箱的作用力。质心面等效模型的数值仿真结果与基于VOF方法的流体动力学数值计算结果基本吻合,从而验证了质心面等效模型用于航天器贮箱大幅液体晃动分析的有效性。     

The feasibility of Doppler monitoring during EVA

During extravehicular activities (EVA) outside the spacecraft, astronauts have to work under reduced pressure in a space suit. This pressure reduction induces the risk of decompression sickness (DCS) by the formation of gas bubbles from excess nitrogen dissolved in the organism by breathing air at normal pressure. Under laboratory conditions the gas bubbles moving in the blood stream can be detected by the non-invasive ultrasonic Doppler method. By early detection of excessive bubble formation the development of DCS symptoms may be prevented by early application of preventative measures. The method could also be useful when applied in the space suit in order to compare the results of laboratory tests with operational results, because there is a discrepancy according to the DCS risk of laboratory experiments and actual EVA missions, where no symptoms have been reported yet. A prototype Doppler sensor has been developed and implemented in the Russian Orlan suit. To investigate the feasibility of this method under simulated space conditions, the equipment has been used in a series of 12 thermovacuum chamber tests with suited subjects, where intravenous bubble formation was compared to unsuited control experiments. In more than 50% of the suited tests good Doppler recordings could be achieved. In some cases with unsatisfying results the signal could be improved by breathholding. Although the results do not yet allow any conclusion about a possible difference between suited and unsuited subjects due to the small number of tests performed, the method proved its feasibility for use in EVA suits and should be further developed to enhance the safety of EVA procedures.     

基于时频域分析的轮控航天器姿态控制规律参数整定

研究了轮控航天器姿态控制规律的设计与参数整定问题。采用xyz转序欧拉角描述航天器姿态,建立了航天器动力学及运动学方程,并设计了非线性解耦控制律,使得各回路可独立设计PID控制器。以滚动回路为例,分析了PD控制参数与系统带宽、截止频率、相位裕度等多项频域指标的关系,从而设计有效的稳态控制器以应对挠性结构振动和系统时延等;接着根据姿态控制特性给出了积分参数选取及积分饱和处理策略;同时为快速完成姿态机动,结合时间最优控制特性分析了控制参数与机动角度的关系;此外,执行机构效率和系统干扰力矩等因素也被用于控制参数域的整定。最后利用整定策略设计了某型卫星的姿态控制器,并通过频域分析和数学仿真检验了该方法的有效性和实用性。     

A mechanism of formation of polar cyclones and possibility of their prediction using satellite observations

Using numerical simulation, a mechanism of formation of polar cyclones in the region of location of the arctic front in the winter troposphere of the Northern Hemisphere is studied. The simulation was performed with the help of the complete system of gas dynamics equations taking into account the transport of infrared radiation, phase transitions of water vapor into micro-drops of water and ice particles, and with allowance made for sedimentation of these drops and ice particles in the gravity field. In the initial and boundary conditions of the model, observational data on the structure of dominating air flows in the region of the arctic front over Norwegian Sea in January are used. Formation of large-scale cyclonic vortex flows in 15–20 hours at the presence of a bend of the central line of the shear flow in the arctic front 500–600 km long with northward or southward deviations by 100 km and more is obtained numerically. On the basis of the simulation results, a method of short-term forecast of formation and motion of polar cyclones is suggested.     

Solution to the problem of joint evaluation of the nonstationary model of GSP drift and the state vector of a navigation system

The solution to the problem of evaluation in real time of nonstationary coefficients of the polynomial model of drift of a gyro-stabilized platform (GSP) is considered. In order to solve this problem, the estimating equations for the state vector of the navigation system (NS) are derived taking into account correlations between the equations of the object and the observer. Evaluation of the coefficients of the model of the GSP drift is realized based on minimization of nonlinear probabilistic criteria.     

燃气推力矢量控制发动机内流场数值模拟

采用基于Favre平均的三维N-S方程,对燃气推力矢量控制发动机全内流场进行了数值仿真,研究了燃气引流、燃气二次喷射及与发动机内主流相互作用等复杂流动。研究结果表明,流场内包含复杂的涡系结构和波系结构,还存在着边界层与激波的相互干扰、自由剪切层、激波、膨胀波和大尺寸分离。通过数值模拟,对试验中的异常现象进行了定性分析,得出了与试验一致的结论。     

某试验台LH2贮箱气体置换过程数值模拟

首先应用C#软件编制贮箱气体置换计算程序,用该程序对不同N2、H2充气压力和放气终压对贮箱置换的影响进行分析,通过对比分析得出最优置换方案;其次利用FLU—ENT软件对某运载火箭发动机动力系统试验LH2贮箱气体置换过程进行数值计算,包括N2充气置换、H2充气置换和LH2贮箱缩比尺寸和全尺寸数值计算。对H2置换过程中不同...