Experimental investigation on silica dust lofting due to charging within micro-cavities and surface electric field in the vacuum chamber

The charged dust particles can be mobilized electrostatically by the repulsion between the adjacent grains and the surface electric field due to the incoming electron current and the charge accumulation within the micro-cavities. In this study, the experimental results of the initial vertical launching velocities and the maximum dust heights are compared with the estimated values for the lofted spherical dust grains by the patch surface charging equations. Silica particles with the sizes between <6 and 45?µm in radius are loaded on a graphite plate, and they are exposed to the electron beam with 450?eV energy under 4?×?10^?3?Pa vacuum chamber pressure. During the first set of the experiments, the dust samples are tested without an initial compression process and an additional horizontal electric field. Second, the dust samples are compressed by two different weights in order to increase the packing density under approximately 780.7?Pa and 3780?Pa. Finally, the dust grains are placed between the two parallel aluminum plates to apply approximately 2000?V/m and 4800?V/m horizontal electric field. A high-speed camera is used to record the transportation of the dust grains together with a microscopic telescope, and the results point out that the patch surface dust-charging model estimations are in agreement with the first experiments. On the other hand, the dust particles from the compressed samples are lofted with higher velocities than the estimations, and the number of the dust lofting observations decreases significantly, which demonstrates the importance of the micro-cavities and the increased charging requirement to overcome the contact forces. When the horizontal electric field is present, the initial vertical launching velocities are measured to be lower than the other experiments, which can be attributed to the decreased charging requirement for the dust lofting as a result of inter-particle collisions and rolling motion. According to the experimental results, the electrostatic dust transportation can be controlled not only by the ambient plasma and the solar irradiation on the airless planetary bodies, but also by the surface properties such as the contact surfaces between the dust grains, the number of the micro-cavities related to the packing density, and the presence of the horizontal electric field contributing to the external forces by other particle motions.     

尖侧缘机身布局的俯仰力矩特性及扰流板控制

针对尖侧缘机身布局在大迎角下存在的正俯仰力矩（抬头力矩）问题，通过风洞试验，首先研究了俯仰力矩的迎角分区特性及流动演化规律：线性增长区（迎角为0°~15°），俯仰力矩线性增加，全机从附着流到形成进气道前缘涡和机翼涡；非线性增长区（迎角为17.5°~32.5°），俯仰力矩非线性增加，机头涡出现，机头涡和进气道前缘涡逐渐增强，机翼涡增强后破裂；衰减区（迎角为35°~65°），俯仰力矩逐渐减小，机头涡增强后破裂，进气道前缘涡破裂发展，机翼涡完全破裂。其次，发现了机身前体是产生正俯仰力矩的主要来源，机头涡是导致大迎角下正俯仰力矩的主控流动。当迎角为40°时，前体各截面正俯仰力矩在进气道前缘处达到最大，主要是由于该处机头涡诱导产生了较强的法向力。最后，提出了大迎角机身扰流板控制技术，产生了较好的控制效果。当迎角为40°时，扰流板可使正俯仰力矩减少62%，其原因是扰流板降低了机头涡涡量及其诱导产生的法向力，减少了机身前体对正俯仰力矩的贡献。该控制技术的缺点是扰流板会带来一些升力损失和附加阻力。基于尖侧缘机身参考宽度的雷诺数为2.59×10⁵。     

背压对撞击式喷嘴雾化特性影响研究

为研究背压对撞击式喷嘴雾化特性的影响,将压力的变化等效为气体密度的变化,基于一种树形自适应加密算法,通过直接数值求解不可压Navier-Stokes方程组实现了不同背压条件下射流撞击雾化的数值模拟。首先将数值模拟结果与试验数据进行对比,验证数值模拟的有效性,在此基础上开展了高背压条件下雾化过程的数值模拟。结果表明,随着背压的提高,气动力相应增强,液膜的破碎更加剧烈,一次雾化区域的液滴数密度增大,雾场由稀疏向稠密发展;液膜在向下游运动过程中波动速度的幅值逐渐增大,并且随着背压的提高,液膜的波动由线性向非线性转变;背压增大导致破碎长度减小,经过参数修正得到了液膜破碎长度的经验公式,并与试验数据进行了对比;背压对液滴尺寸分布规律没有显著影响,但随着背压的提高,同一时刻大液滴所占的比例提高,整个雾场的Sauter平均直径有增加的趋势,当背压从0.1MPa增大到1MPa时,雾场的Sauter平均直径由155.5μm增大到166.9μm;背压增大,液滴粒径分布的均匀度指数减小,液滴尺寸分布更加不均匀。     

凝胶推进剂模拟液撞击雾化特性研究

为了寻求凝胶推进剂雾化机理、提高其雾化效果,开展幂律流体双股圆柱射流撞击的理论和实验研究。首先推导了幂律型流体射流撞击形成液膜的理论模型,在其中引入粘性力和能量损失。进而通过设计凝胶模拟液射流撞击实验,使用高速摄像机拍摄图像的方法进行了相关的实验研究,以验证理论的正确性。在此基础上,对撞击角度、射流速度分布及液体部分物性参数对液膜形状、厚度及速度分布的影响进行了分析,得到了相关参数的影响规律。研究结果表明,射流撞击角、速度型、液体表面张力系数、流变特性等均对液膜特性有明显影响,且流体本身的物理性质对撞击形成的液膜的影响更甚。     

Ground experiments of Chang’e-5 lunar regolith penetrating radar

The Lunar Regolith Penetrating Radar (LRPR) is an Ultra-Wideband (UWB) array-based Ground penetrating radar (GPR) onboard the lander of Chang’e-5 (CE-5) mission. The primary scientific objectives of the LRPR are to probe the thickness and structure of lunar regolith of the landing site, and support the drilling and sampling process. In order to evaluate the performance of the LRPR, a series of ground experiments are performed using the LRPR prototype mounted on a CE-5 lander model. The performance of the LRPR is evaluated by comparing the experimental data with the simulated data. Data processing and imaging method are verified, and the interferences from the lander and other aspects are analyzed. The results of the ground experiments and simulation demonstrate that the LRPR is able to meet the design requirement of 2-m detection depth. They also indicate that the upper and lower interfaces of the stratified structure in the lunar regolith can be well distinguished by the LRPR when the dielectric constant difference is greater than 0.3, and the imaging effect of the location under the dense antennas is better than that of other positions. However, the identification capability of the LRPR to the independent blocky objects is relatively poor mainly due to the clutters caused by the lander, the sparsity of the antenna elements compared to the size of the basalt block, the limited aperture of the antenna array, and the tail of the transmitted waveform.     

均匀流吹吸式通风实验研究

介绍了吹吸式通风气流的特点,并对吹吸风口间距3.5～3.8m时的低速流场的吹吸式通风气流流场的规律特性进行了实验研究。结果表明,当吹吸风口间距小于3.8m时,低速流场吹吸式通风的气流在射流起始段未结束时就进入了汇流段(吹吸气流流场中未出现射流主体段)。高速流场吹吸式通风的轴心速度经验公式与低速流场的吹吸式通风实验结果式对比分析,发现两者之间存在较大的偏差。高速流场吹吸式通风的轴心速度经验公式不适用于描述低速流场吹吸式通风轴心速度的规律特性。     

基于神经网络的飞行器总体优化设计

针对经验公式存在的精度低、适用范围受限的缺点,采用广义回归网络代替经验公式计算气动特性,并将其嵌入到优化设计流程之中,提出了一种基于神经网络的飞行器总体优化设计方法。神经网络的训练样本输入、输出数据通过试验设计和涡格法计算得到。以高空长航时无人机为例,选取航时与机翼结构重量系数作为目标函数,应用所提出的方法进行总体优化设计。计算结果表明,提出的方法是可行的,能够满足设计要求,同时降低优化过程的复杂程度,减少迭代次数。     

Periodic atomization characteristics of an impinging jet injector element modulated by Klystron effect

An experimental study on the Klystron effect of periodic injection modulated by pressure drop fluctuations on subsequent atomization is conducted. Time-resolved atomization backlit images and atomization Mie scatter images are captured by using the high speed camera. It is found that periodicity of forced atomization relies on pressure drop fluctuation amplitude and phase differences between atomization and pressure drop fluctuations relate to fluctuation frequencies. This feature of periodic atomization induced by Klystron effect corresponds to periodicities and high amplitudes of pressure fluctuations in unstable combustion chambers and chaos and low amplitudes of pressure fluctuations in stable combustions chambers. Drastically periodic varying of gross surface area of droplets with time was shown in Mie scatter images. The importance of periodic impinging jet atomization modulated by pressure drop fluctuations for acoustic liquid propellant combustion instabilities is illustrated.     

密集型空气雾化流场破碎特征数学模型研究

低速液体射流在高速湍流气体作用下的气液同轴射流雾化流场是瞬态密集型喷雾场,高速湍流中影响和控制雾化的因素很多。针对空气雾化流场液核分布与特征进行分析,开发了模拟液核的随机浸入体模型,结合大涡模拟方法对同轴射流空气雾化喷嘴下游流场进行数值模拟。模拟结果与实验结果对比表明：随机浸入体模型可快速捕捉液核的长度和位置信息。当气液动量比M为3~10000时,能够较准确地预测液核长度,当M>10时,其预测结果远优于唯象模型;该模型能够捕捉回流区、大尺度涡等流场结构。同时,可以准确地预测喷嘴附近的液滴粒径,特别是在气流速度较大（>60m/s）时,液滴平均直径预测误差<10%。     

Challenges and perspectives of transport cargo vehicles utilization for performing research in free flight

Russian Progress transport cargo vehicles have successfully been used in different space station programs since 1978. At present time, they play an important role in the International Space Station (ISS) project. Main tasks performed by the transport cargo vehicle (TCV) in the station program are the following: refueling of the station, delivery of consumables and equipment, waste removal, station attitude control and orbit correction maneuver execution.