Yaw attitude of eclipsing GPS satellites and its impact on solutions from precise point positioning

During the period when a GPS satellite, the Earth and the Sun are approximately collinear, the phenomenon of eclipsing the satellite occurs, when the satellite yaw attitude deviates from its nominal case, i.e. the body X-axis cannot point towards the Sun for Block II&IIA or away from it for Block IIR satellites. The yaw attitude of the eclipsing satellites has a significant influence on both the satellite clock estimation at each International GNSS Service (IGS) Analysis Center (AC) and for users of the precise point positioning (PPP) implementations. It is known that, during the eclipsing periods, inconsistent yaw attitude models among the ACs will contribute to the errors of the IGS combined clock products. As for the PPP user, the influence of the eclipsing satellite is two-fold. First, as the satellite clocks are always kept fixed during PPP implementation, the above-mentioned problematic IGS clocks will inevitably be passed on to the PPP estimates. Second, the improper yaw attitude modeling of the eclipsing satellite will cause a correction bias exceeding 1 dm for the two kinds of attitude-related systematic errors, namely the phase wind-up and satellite antenna phase center offset, which will further deteriorate the accuracy of the PPP solutions. A yaw attitude model is introduced in this paper with the aim of improving the reliability of PPP solutions during the satellite eclipsing period.     

基于区间值模糊集的聚类分析

对于区间数,提出了反映决策者心态的心态指标的概念,在此基础上,给出了基于区间值模糊集之聚类分析的两种方法心态分类法、数-区间分类法,对后一种分类法,引入了一种指标,并用它对其分类结果的可信度进行了定量分析.     

分子动力学模拟α-Fe拉伸与疲劳裂纹扩展机理

采用分子动力学模拟方法研究了含(010)[001]和(0-11)[100]型中心裂纹的金属α-Fe分别在拉伸与疲劳载荷作用下裂纹扩展的微观机制.研究发现,在拉伸载荷作用下,(010)[001]型裂纹在钝化的基础上沿着{110}滑移面塑性扩展;(0-11)[100]型裂纹尖端位错沿(011)面发射,裂纹沿(110)表面脆性解理扩展.在循环载荷作用下,(010)[001]型裂纹尖端位错沿着{111}110滑移系扩展,裂纹在裂尖应力集中作用下,沿之字形快速扩展;(0-11)[100]型裂纹扩展方式与拉伸失效时基本一致,裂纹在(110)面内发生快速的脆性解理扩展.两种裂纹扩展过程中都有层错和位错的共同作用.研究表明,(110)表面的表面能最低,是α-Fe的最优解理面.     

量子信道对纠缠鲁棒性的影响

考虑量子信道对多体纠缠鲁棒性的影响. 先根据可分态之集为一个凸闭集, 证明可以取到纠缠鲁棒性定义中的下确界, 再证明同一纠缠态ρ的两个最优态的凸组合仍是最优态, 纠缠鲁棒性作为定义态集合上函数是下半连续的; 最后, 分别给出一个量子信道不增加、 不减少[KG*8]及保持所有量子态的纠缠鲁棒性的充分必
要条件.     

考虑气流影响的直通穿孔管消声器声学性能

为了研究气流对消声器传递损失的影响,采用有限元法(finite element method,FEM)和计算流体力学法(computational fluid dynamics,CFD)相结合的方法来解决这种流声耦合问题.以直通穿孔管消声器为例,计算出它们存在气流时的传递损失,并与文献中的实验数据和预测结果进行对比,以验证计算结果的准确性.研究结果表明:当忽略消声器内部气流引起的湍流噪声时,随着气流速度的增加,除了共振峰值处的传递损失显著减小外,多数频率处的传递损失有所增加,尤其是在较高频段内变化较为明显;随着气流温度的增加,传递损失曲线向高频方向移动.     

基于计算流体力学的熔盐燃料电池电堆的仿真

基于计算流体力学技术，建立并仿真了10kW级顺流型熔融碳酸盐燃料电池（MCFC）电堆的三维模型，对电堆内部的物质、动量和能量守恒过程进行了理论分析，模型考虑了MCFC电堆的一个重要组成部分-波状板，并讨论了波状板尺寸对电堆性能的影响，结果表明，在采用较大尺寸波状板的电堆中，电化学反应进行得更加充分，所建模型对电堆内部流场的设计有一定意义。     

Translocation of polymer through nanopore: dissipative particle dynamics simulation

Dissipative particle dynamics simulations are performed to study the forced translocation of polymer through a nanopore inside which the polymer experiences a driving force F. Hydrodynamic interaction （HI） is taken into account for the polymer in good solvent. We find that the mean translocation time 〈t〉 scales with the polymer length N as 〈t〉 ~ N^a with α = 1.26 ± 0.03 close to a theoretical pre- diction, and the probability distribution of t can be described by a Gaussian function. Our results show that the dynamics of polymer translocation with the HI is different from that without the HI. However, the exponent 6 in the scaling 〈t〉 ~ F^-δ is found not to be affected by the HI effect.     

温度对质子交换膜扩散性能影响的分子动力学模拟

为了研究Nafion膜的微细观结构及其输运特性,针对目前广为采用的Nafion 117膜并基于Materials Studio软件平台构建了一种分子动力学计算模型,在温度分别为300、353 K时,对其实施了计算,得到了不同水含量下Nafion 117膜的元胞结构,并依据该模型计算了水分子和水合氢离子的扩散系数.模拟结果表明:质子交换膜元胞的密度随水含量的增加而下降,和实验值基本一致,最大偏差在8%以内(300 K);当温度升高时,膜元胞密度降低,这与温度升高、膜体积膨胀导致密度降低的宏观分析完全一致.同时,研究了膜水含量、温度对水分子和水合氢离子在膜内的扩散系数的影响,增加水含量可以提高膜的质子传导率,同一温度下水含量越大,水分子和水合氢离子的扩散系数越大,且同一水含量下温度越高,水分子和水合氢离子的扩散系数越大.     

纳米铜杆拉伸变形的分子动力学模拟和有限变形表征

用分子动力学方法模拟纳米铜杆的拉伸过程，用有限变形列式表征纳米杆单向拉伸屈服前的应力和应变．结果表明：铜单晶纳米杆屈服前的最大弹性应变约为0．11；用有限变形应力、应变表征变形过程和材料性质与通常名义应力、应变表征相比有明显不同；纳米杆泊松比随应变增加而减弱，并从物理上解释了这一现象的原因。     

大展弦比飞翼刚柔强耦合飞行动力学与控制

针对大展弦比飞翼布局柔性飞行器在刚体和弹性自由度动力学强耦合情况下的控制问题,对相应的强耦合动力学特性与相应的控制方法展开研究.采用自由-自由模态法表征飞翼刚柔运动之间的惯性耦合;采用偶极子网格法和有理函数近似法完成广义非定常气动力计算;应用线性二次型最优控制方法进行飞行机动与弹性变形的联合控制律设计.与无控情况相比,闭环控制可有效减缓飞行器俯仰方向的阵风扰动至原来的40%.研究结果表明,飞行器一阶弯曲模态短周期之间存在明显动力学耦合.设计的闭环控制律可使动态弹性变形量始终向有助于减缓扰动方向变化.