失重模拟技术的发展及其比较研究

失重或称微重力环境是载人航天轨道飞行中的重要环境因素,地面上失重模拟实验是航天前的重要准备工作之一。失重模拟方法及其设备多种多样,要依其目的不同而进行选择。文章对上述问题进行了充分的比较研究,并在此基础上指出了中性浮力水槽和失重飞机是失重模拟设备中最常用和最有效的工具。建议从我国的实际情况出发,适时的加以建造。     

旋转衍生力在旋转受限层板中的分布规律

采用数值模拟的方法,研究了旋转衍生力在旋转受限层板中的分布规律.研究表明:由于冷却流体被加热,离心力随着旋转半径的增加而降低,近壁面处离心力较低,远离壁面区域离心力较高.y方向哥氏力在进出口区域影响较大,中间区域可以忽略.z方向哥氏力在进出口区域影响较大,中间段随转速和旋转半径的增加而缓慢增加.离心力衍生的浮升力在冲击区域附近加速流体流动,在其他区域的近壁面处,离心力衍生的浮升力阻碍流体流动,在远离壁面区域,离心力衍生的浮升力加速流体流动.在中间段,离心力和离心力衍生的浮升力起主导作用.      

层板与旋转轴所成角度对受限层板换热能力的影响

采用数值模拟的方法对旋转状态下受限层板在不同层板与旋转轴所成角度条件下的换热特性进行研究,得出了层板与旋转轴所成角度对层板换热能力的影响规律.结果表明:层板与旋转轴所成角度不同时,表面传热系数呈现一定的相似性;层板与旋转轴所成角为90°和270°时表面传热系数最高,浮升力的影响最小,层板与旋转轴所成角度为0°和180°时,表面传热系数最低,浮升力的影响最大;将科氏力和浮升力对换热能力的影响单独研究,平行于层板的科氏力比垂直于层板的科氏力对流体的影响强烈.      

竖直圆管内超临界碳氢燃料换热恶化的直径效应

利用Fluent对超临界压力下直径对碳氢燃料换热恶化的影响进行数值研究,湍流模化采用Launder-Sharma（LS）低雷诺数模型,物性采用广义对应态法则对RP-3替代燃料计算。计算条件：系统压力为3 MPa,进口温度为573 K,热流密度为500 kW/m²,质量流量为0.001 5和0.003 0 kg/s,直径范围为1~10 mm。正常换热条件下的计算壁温和实验结果基本吻合,证明了计算方法的准确度。结果表明：强制对流下小质量流量时直径越大,换热恶化程度更高且更提前发生,换热恶化是由定压比热容处于极大值后的急剧下降区导致的,大质量流量时直径与壁温成正比,无换热恶化发生;浮升力效应仅在小质量流量下起作用,随着直径增大而加强,给出RP-3流动换热时浮升力起作用的判据和不同直径下换热恶化的边界。     

Analysis of the buoyancy-induced heat transfer in a rotating cavity

In order to get a better knowledge of the heat transfer in compressor cavities of aero-engines, the simplified rotating cavity with two-plane discs, a shaft and a cylindrical rim has been investigated numerically and compared with the available measurements. The numerical results in agreement with the available experiments show large-scale instabilities. The disk local Nusselt numbers show mainly radial rising distributions for the heated disks with radial rising temperature profiles. In the present work, at the Reynolds number of 20000, the disk local Nusselt numbers are the correlations of the local Grashof number to the power of 1.89~2.6, and the value of the power is increased as the rotational Reynolds number goes up. At the rotational Reynolds number of 800000, the local Nusselt numbers are the correlations of the local Grashof number to the power of 0.68~2.6, and the value of the power is decreased as Reynolds number goes up. The area-averaged disk Nusselt number is the correlation of the Reynolds number to the power of 0.479 and the rotational Grashof number to the power of 0.12.      

临近空间飞艇排翼式艇翼气动干扰实验研究

临近空间排翼式升浮一体飞艇是运行在临近空间环境,由水平、垂直方向具有一定几何间隔的两个艇翼连接两个囊体构成的新型低速飞行器。本文通过研制附加支架,使用一种低雷诺数风洞测量了两个对称翼型在水平、垂直方向相对位置、雷诺数、迎角等参数变化的情况下,前翼型模型对后翼型模型的升力和阻力系数于扰值的定量结果;对其变化规律进行了总结,并通过自由飞模型对由实验数据推导出的前、后机翼间的气动干扰进行验证,得出一些对排翼式布局飞行器总体设计有指导意义的经验数据与结论。     

浮力修正湍流模型在航空发动机火灾模拟中的应用

由于发动机舱的火灾是典型的热驱动的浮力羽流,从探索浮力羽流的模拟方法出发,针对热羽流的基准试验,比较验证了3种基于浮力修正的2个方程湍流模型;利用pre PDF燃烧模型,模拟验证了Purdue甲烷火燃烧试验;以RR公司Trent 800发动机的1/2缩比短舱着火试验器为原型,采用RANS方法对由燃油泄漏引起的油池火进行了模拟计算,重现了短舱火灾的主要物理过程,并与试验测量的速度及温度结果进行了对比,验证了计算方法的准确性,并进一步分析了影响模拟结果的主要原因:湍流模型与燃烧模型能否准确计算近火源区域的火焰锋面状态,直接影响空气卷吸及下游火羽流的温度与速度。应用CFD技术,可以从防火设计的角度优化通风系统及短舱附件的布局。     

斜孔式等离子体合成射流激励器静特性的实验

设计了斜孔式等离子体合成射流激励器，采用电参数测量和高速纹影技术研究了其放电特性及瞬态流场特性。实验表明:相较直孔式等离子体合成射流激励器，斜孔式等离子体合成射流激励器的射流流动表现出明显的附壁效应和非对称性，这有利于提高射流对流动分离的控制能力。同时，实验中还观察到了浮力对等离子体高温射流流场演化的影响，特别是在射流演化的末期，其诱导的垂向速度分量显著地改变了射流的最终运动方向。      

Nightside 135.6 nm emission enhancements of mid/low latitudes during geomagnetic storms as observed by the ionosphere PhotoMeter (IPM) on the Chinese meteorological satellite FY-3D

IPM has detected nightside 135.6 nm emission enhancements over a wide latitude range, from the sub-auroral latitudes to the equatorial regions during geomagnetic storms. Our work, presented in this paper, uses the data of IPM to understand these 135.6 nm emission enhancements during of geomagnetic storms and studies the variations of total electron content (TEC) and the F₂ layer peak electron density (NmF2) in the region of enhanced emissions. Middle and low latitude emission enhancements are presented during several medium storms in 2018. The variations of both the integrated electron content (IEC) derived from the nighttime OI 135.6 nm emission by IPM and TEC from the International GNSS Service (IGS) relative to the daily mean of magnetically quiet days of per each latitude bin (30°≦geographic latitude < 40°, 15°≦geographic latitude < 30°, 0°≦geographic latitude < 15°, ?15°≦geographic latitude < 0°, ?30°≦geographic latitude < -15°, ?40°≦geographic latitude < -30°) are investigated and show that on magnetically storm day, IEC by IPM always increases, while TEC from IGC may increase or decrease. Even if both increase, the increase of IEC is greater than that of TEC. From the comparison of IEC and TEC during magnetic storms, it can be seen that the enhancement of the nighttime 135.6 nm emissions is not entirely due to the ionospheric change. The time of IEC enhancements at each latitude bin is in good agreement, which mainly corresponds to the main phase time of the geomagnetic storm event and lasts until the recovery phase. The available ground-based ionosonde stations provide the values of NmF2 which match the 135.6 nm emissions measured by IPM in space and time. The variations of NmF2 squared can characterize the variations of the OI 135.6 nm emissions caused by O⁺ ions and electrons radiative recombination. The study results show that the OI 135.6 nm emission enhancements caused by O⁺ ions and electrons radiative recombination (where NmF2 squared increases) are obviously a contribution to the measured 135.6 nm emission enhancements by IPM. The contribution accounts for at least one of all contributions to the measured 135.6 nm emission enhancements by IPM. However, where the NmF2 squared provided by ionosonde decrease or change little (where the OI 135.6 nm emissions cause by O⁺ ions and electrons radiative recombination also decrease or change little), the emission enhancements measured by IPM at storm-time appear to come from the contributions of other mechanisms, such as energetic neutral atoms precipitation, or the mutual neutralization emission (O+ + O-→2O + h? (135.6 nm)) which also occupies a certain proportion in 135.6 nm airglow emission at night.