航天器表面电荷激发空间静电场规律研究

从带电表面微元出发，通过求解泊松方程，得到带电介质平板表面邻近空间静电势的解析表达式，建立介质表面电位-介电常数模型，求得了带电介质平板表面电位、表面带电量和介质介电常数三者之间的关系式。结合典型的航天器表面介质材料带电案例，对此类圆盘结构介质平板带电问题进行了仿真分析，结果表明，在介质材料表面电位一定的情况下，表面电荷激发的空间静电势值随距离的增大而减小，并且距离介质表面越近，电势的空间变化率越大；在介质材料带电量相等的情况下，介质表面电位随着介质介电常数的增大而减小，并逐渐趋于一个稳定值，所以在一定范围内选择介电常数较大的介质材料可以降低介质的表面电位，减小介质间发生静电放电的几率。     

Stability of relative equilibria of the full spacecraft dynamics around an asteroid with orbit–attitude coupling

The full dynamics of spacecraft around an asteroid, in which the spacecraft is considered as a rigid body and the gravitational orbit–attitude coupling is taken into account, is of great value and interest in the precise theories of the motion. The spectral stability of the classical relative equilibria of the full spacecraft dynamics around an asteroid is studied with the method of geometric mechanics. The stability conditions are given explicitly based on the characteristic equation of the linear system matrix. It is found that the linearized system decouples into two entirely independent subsystems, which correspond to the motions within and outside the equatorial plane of the asteroid respectively. The system parameters are divided into three groups that describe the traditional stationary orbit stability, the significance of the orbit–attitude coupling and the mass distribution of the spacecraft respectively. The spectral stability of the relative equilibria is investigated numerically with respect to the three groups of system parameters. The relations between the full spacecraft dynamics and the traditional spacecraft dynamics, as well as the effect of the orbit–attitude coupling, are assessed. We find that when the orbit–attitude coupling is strong, the mass distribution of the spacecraft dominates the stability of the relative equilibria; whereas when the orbit–attitude coupling is weak, both the mass distribution and the traditional stationary orbit stability have significant effects on the stability. We also give a criterion to determine whether the orbit–attitude coupling needs to be considered.     

The Kumtag meteorite strewn field

The Kumtag meteorite strewn field was found in the Kumtag desert, 132 km south of Hami city in the Xinjiang province, China. It is an ellipse of 2.5 × 7.9 km, with a long axis extending along the northeast-southwest direction. The largest individual meteorite of the strewn field weighs about 10 kg; the smallest individual has a mass of only 27 g. In total, more than 100 individuals with a total mass of more than 180 kg were collected. The location and the distribution of the fragments suggest that the Kumtag meteoroid entered the atmosphere in the direction Northeast-Southwest. All meteorites collected in this strewn field are samples from the same unique meteorite shower. The Kumtag meteorite is an H5 ordinary chondrite with a shock stage S2, and a weathering grade W2. The cosmic ray exposure age of Kumtag is 6.7 ± 0.8 Ma, which is rather typical for H chondrites and which indicates that Kumtag was derived from the massive impact event on its parent body ~7 Ma ago. A significant amount of He has been lost during certain unknown processe(s) before the Kumtag meteorite was ejected from its parent body.     

A boundary vector cell model of place field repetition

Hippocampal place cells are thought to form the neural substrate of a global cognitive map. However, in multicompartment mazes, these cells exhibit locally repeating representations, undermining the global cognitive map view of place cells. This phenomenon appears to be related to the repetitive layout of these mazes, but still no hypothesis adequately explains it. Here, we use a boundary vector cell (BVC) model of place cell firing to model the activity of place cells in numerous multicompartment environments. The activity of modeled place cells bears a striking resemblance to experimental data, replicating virtually every major experimental result. Our results support the BVC model and indicate that locally repeating place cell firing could result purely from local geometry.     

基于动网格技术的飞机舱弹分离过程 CFD/ RBD耦合数值仿真

飞机舱弹分离瞬间特性严重影响导弹/炸弹的打击精度。采用计算流体动力学(CFD)和刚体动力学(RBD)模型耦合求解的数值仿真方法,应用网格弹性光顺和局部重构相结合的动网格技术,有效地避免了刚体运动而引起的网格畸变,仿真计算了炸弹舱弹分离后俯仰角度变化过程 .仿真结果表明,舱弹分离时向炸弹施加 1个合适的抛 射力矩,有助于炸弹在下降过程中快速地调整其打击姿态。     

水下超声速过膨胀燃气射流的流场特性

为研究水下超声速过膨胀燃气射流的流场特性,在压力水筒中开展了大扩张比锥形喷管的固体火箭发动机水下点火实验,并基于雷诺时均Navier-Stokes（RANS）方法和流体体积（VOF）模型进行数值求解,分析了过膨胀燃气射流与水介质的相互作用过程。研究表明：超声速过膨胀燃气建立射流通道后,射流核心区长度随喷管落压比的减少而减少;射流核心区剧烈振荡,表现为高频的膨胀和收缩,振荡频率随喷管落压比的减小而增加,范围为100~200 Hz;射流边界不断振荡,并伴随波系结构变化,当过膨胀程度较大时,激波进入喷管使其发生流动分离现象,流动分离点周期性往复移动;分离区内压力脉动没有显著的特征频率,主要集中在100~600 Hz的宽频带,锥形喷管水下流动分离的简易判据为喷管出口压力不低于环境背压的0.44倍。     

高超声速风洞流场非均匀性对气动力试验影响研究

高超声速风洞流场品质是气动力试验主要误差的决定因素,常规高超声速风洞流场均匀性虽然满足国军标GJB4399-2002《高超声速风洞气动力试验方法》对风洞流场品质的要求,但其风洞流场严格意义上说是“非均匀”的,这种流场非均匀性会对模型气动力特性存在不同程度的影响。为此,在CARDC常规高超声速风洞中开展了某升力体模型和某通气模型“多位置试验”,验证了风洞流场的非均匀性对飞行器气动力(特别是力矩特性)试验结果有显著影响,这种影响量已远超过常规的风洞重复性试验误差,甚至大于国内现有的在AIAA-S071A-1999标准上建立的不确定度评估方法所获取的“不确定度”。     

中心锥对旋转爆轰发动机内外流场影响的三维数值模拟研究

为探究中心锥对旋转爆轰发动机(Rotating Detonation Engine,简称RDE)内外流场结构与推进性能的影响,本文设计了90°、60°、45°、30°、20°、14°锥角与无中心锥7种构型,对燃烧室内径为78mm、外径为88mm、长度为100mm的RDE进行三维数值模拟,推导了适用于带中心锥RDE的推力公式,获得了各构型下详尽的流场参数。结果表明：在本文构型下中心锥对内流场影响很小,各构型的内流场参数与结构基本一致;中心锥对外流场的爆轰产物有轴向加速与径向吸附作用,能够调控尾部区域的流场特性;中心锥对由压差项产生的推力具有显著的提升效果,最佳推力性能出现在20°中心锥构型中,RDE总推力增益达22.8%。研究结果揭示了中心锥对RDE推力影响的作用机理,阐明了锥角对推进性能的影响规律,对带锥形构型的尾喷管设计工作提供了参考。     

Coronal Heating by Magnetic Explosions

From magnetic fields and coronal heating observed in flares, active regions, quiet regions, and coronal holes, we propose that exploding sheared core magnetic fields are the drivers of most of the dynamics and heating of the solar atmosphere, ranging from the largest and most powerful coronal mass ejections and flares, to the vigorous microflaring and coronal heating in active regions, to a multitude of fine-scale explosive events in the magnetic network, driving microflares, spicules, global coronal heating, and, consequently, the solar wind. This revised version was published online in June 2006 with corrections to the Cover Date.     

航空发动机轴承腔热状态分析模型及温度场计算

分析了轴承腔的主要热源。建立了轴承及石墨密封摩擦热的计算模型、密封热泄漏量的计算模型、对流换热系数的计算模型及温度场的计算模型。用热网络法建立了轴承腔的热平衡方程组,并采用拟牛顿法求解了该方程组。获得了10种不同工况下的温度场计算结果,该结果与本文的测试结果基本吻合。