试析马克思理论体系的两个思想资源

除了常说的三大理论来源以外,马克思的理论体系的形成还有很多丰富的思想资源,其中,基督教和<圣经>传统、古希腊神话和西方文学作品对马克思科学世界观、人生观、价值观的形成产生了深刻影响,马克思对他们采取了批判的借鉴的态度,从中汲取了丰富的营养,成为马克思理论体系重要的思想资源.     

西部农村金融发展中存在的问题及对策

西部地区在新农村建设过程中普遍面临金融支农资金短缺、金融服务体系边缘化、民间金融缺乏保护、金融改革严重滞后、金融创新不足等问题，现存的城乡二元金融体制已经成为阻碍西部地区新农村建设的重要因素。文章提出我国农村金融体制的创新发展，关键在于通过制度创新重构欠发达区域农村金融体系，强化金融服务“三农”的功能，增强其对新农村建设的支持力度，辅之以创新“农业经营项目”贷款抵押、信用担保与信贷投放机制，多管齐下，全方位解决农村金融发展中遇到的各种问题，最终使我国金融体系真正发挥支持新农村建设的应有作用。     

GaAs的光学常数的计算

为深入认识GaAs的光学性质,采用从头算法计算其电子结构,并依据线性响应理论计算出它的复介电常数,进而得到复折射率,反射系数,吸收系数等光学常数。     

无网格方法中含参数指数权函数的研究

选择合适的权函数及相应的影响半径是无网格方法中很重要的问题,在引入数值紧支域概念的基础上分析了含参数的指数权函数中参数的选取范围,综合考虑计算效率和精度后给出了参数的选取原则,并讨论了在特定的参数下的最优半径以及不同参数对最优半径的影响.     

构筑内陆开放型人才高地的对策研究

建设内陆开放型人才高地是中原经济区建设的一个重要任务.先进城市的人才建设经验主要有:引进与培养相结合、培养机制多元化、发挥高校的核心作用和理论联系实际.河南省的人才高地建设应由政府主导,完善人才引进机制；扶持重点产业,鼓励企业培养和吸引创新人才；改革高等教育,着力培养大批高素质的开放型人才；联系实际,实现人才本土化和国际化相结合.     

我国企业债券信用评级存在的问题与对策

由于我国企业债券发展时间短,在发展过程中出现了许多问题.其中,企业债券信用评级的不完善是一个重要方面.文章分析了我国企业债券信用评级的现状和存在的问题,并借鉴美国发展企业债券信用评级的经验,进而提出规范发展我国企业债券信用评级问题的五点对策.     

电容式传感器在飞机燃油测量系统中的应用

叙述了电容式传感器在飞机燃油测量系统中应用。首先,分析了电容式传感器在飞机燃油测量系统中工作的基本原理:因燃油液面位置变化而使电容量产生变化,将其转化为实时电信号,可以实现对飞机油箱油量变化的实时测量。其次,分析了测量误差产生的原因,并提出了改进措施。     

Progress on Microgravity Sciences in China

The main progress of the research activities on microgravity fluid physics, combustion, biotechnology research and fundamental Physics in China are briefly summarized in the present paper. The major space missions and experimental results obtained on board the Chinese recoverable/nonrecoverable satellites and the Chinese manned spaceship named "Shen Zhou" are presented summarily. The recent main activities of the ground-based studies in China are introduced in brief.     

隐身飞行器电磁散射特性分析

为对隐身飞行器的探测手段进行研究和指导隐身飞行器的研制,研究其电磁散射特性。采用外形逆向建模、理论预估和散射测量、强散射源减缩相结合的手段,对隐身飞行器的隐身性能进行预估。该方法具有精度高、速度快的优点,适合在隐身飞行器研制方案设计阶段使用。     

Experimental investigation on aero-heating of rudder shaft within laminar/turbulent hypersonic boundary layers

The aero-heating of the rudder shaft region of a hypersonic vehicle is very harsh, as the peak heat flux in this region can be even higher than that at the stagnation point. Therefore, studying the aero-heating of the rudder shaft is of great significance for designing the thermal protection system of the hypersonic vehicle. In the wind tunnel test of the aero-heating effect, we find that with the increase of the angle of attack of the lifting body model, the increasement of the heat flux of the rudder shaft is larger under laminar flow conditions than that under turbulent flow conditions. To understand this, we design a wind tunnel experiment to study the effect of laminar/turbulent hypersonic boundary layers on the heat flux of the rudder shaft under the same wind tunnel freestream conditions. The experiment is carried out in the ?2 m shock tunnel(FD-14 A) affiliated to the China Aerodynamics Research and Development Center(CARDC). The laminar boundary layer on the model is triggered to a turbulent one by using vortex generators, which are 2 mm-high diamonds. The aero-heating of the rudder shaft(with the rudder) and the protuberance(without the rudder) are studied in both hypersonic laminar and turbulent boundary layers under the same freestream condition. The nominal Mach numbers are 10 and 12, and the unit Reynolds numbers are2.4 × 10~6 m~(-1) and 2.1 × 10~6 m-1. The angle of attack of the model is 20°, and the deflection angle of the rudder and the protuberance is 10°. The heat flux on the model surface is measured by thin film heat flux sensors, and the heat flux distribution along the center line of the lifting body model suggests that forced transition is achieved in the upstream of the rudder. The test results of the rudder shaft and the protuberance show that the heat flux of the rudder shaft is lower in the turbulent flow than that in the laminar flow, but the heat flux of the protuberance is the other way around,i.e., lower in the laminar flow than in the turbulent flow. The wind tunnel test results is also validated by numerical simulations. Our analysis suggests that this phenomenon is due to the difference of boundary layer velocities caused by different thickness of boundary layer between laminar and turbulent flows, as well as the restricted flow within the rudder gap. When the turbulent boundary layer is more than three times thicker than that of the laminar boundary layer, the heat flux of the rudder shaft under the laminar flow condition is higher than that under the turbulent flow condition. Discovery of this phenomenon has great importance for guiding the design of the thermal protection system for the rudder shaft of hypersonic vehicles.