农民工权利法律保护的回顾与基本思路

农民工是我国城乡二元社会经济体制下,改革开放政策推动产生的一个特殊的社会群体。文章回顾了我国农民工权利法律保护的演变历程,对农民工权利缺损进行了实证分析,提出了农民工权利法律保护的基本思路,农民工权利法律保护是一个系统工程,应当遵循一个基本理念,坚持两个基本原则,从立法、执法和司法环节上构建有机的农民工权利法律保护体系。     

航空器权利研究

航空器权利是航空法学的重要内容。着重分析、阐释了航空器权利的法律基础、权利客体、权利种类以及航空器权利的登记制度，建议完善航空器权利法律制度。     

论农民金融权益的法律保障与实现

保护农民的金融权益是推进新农村发展的关键,构造农民金融权利是保护农民金融利益的基础.给予农民正当的金融权利,制定保护农民金融权利的法律制度,能够进一步缩小城乡差距,实现社会正义.在制度层面上,应该从农村金融市场相关的法律制度、农民贷款抵押担保制度、农业保险制度以及非正规金融制度来寻求农民金融权益的法律保障.     

农村土地承包中若干二元研究

农村土地承包中存在诸多二元。对农村土地承包方式二元、土地承包经营权性质二元、土地承包经营权登记二元、土地承包流转权利二元等若干二元进行深入剖析，有利于正确适用不同性质的法律规范，依法实施不同性质的法律保护，达到切实维护农村土地承包当事人的合法权益。     

论权利贫困的社会认知

权利贫困是指由于制度因素所造成的对社会部分人群在政治、经济、社会和文化权利等方面的享有不足的状态，它具有客观性与必发性以及社会性和普遍性的特点。人们对贫困的认识已从狭隘的收入（经济）视角逐步扩大到政治、文化、社会等层面。学者们从社会剥夺与社会排斥理论、能力贫困理论以及一些经典的公民权利理论得到启发，逐步形成了权利贫困的观念，这是在学术界层面形成的对权利贫困的社会认知。此外，政治家对贫困问题的关注以及媒体对贫困问题的宣传和报道，将推动权利贫困的社会认知不断加深。     

民航总局发出通知要求进一步加强航班正常工作

为保护航空乘客的利益，欧盟2月17日正式实施了加强乘客索赔权利和提高赔偿金额的新法律。根据新的规定，如果因为航班座位订满、航班被取消或推迟使乘客无法登机，航空公司必须对乘客进行赔偿。至于赔偿的金额，则视航班飞行距离或延误时间的长短而定，最低为250欧元，最高为600欧元。     

航天技术转让中的国际法问题

对航天技术转让中国际法调节的对象,发展中国家的权利,关于“人类共有财产”的观点的分歧,航天技术的特征对航天技术转让国际立法的影响作了较全面的叙述。     

浅议平等的实质与含义

每个人的生理、身体、心理、能力等有着先天差异，不可能消灭这种差异，实现人的绝对平等。但每个人都有人的尊严，在自由人格的形成上必须享有平等的权利，这就是平等观念产生的缘由。平等在法的价值体系中具有非常重要的意义。平等指导着法律对权利、义务的公正分配，“法律面前人人平等”是法律的基本原则；平等引导着法律的进步和发展，人类法制水平的不断提高，实际上反映了人类平等在形式和实质方面的深化发展。     

借QC活动促企业和谐发展

肯尼迪在就任美国总统时发表了一篇就职演说，其中有这样一句话：“不要问你们的国家能为你们做些什么，而要问你们能为国家做些什么”。从法律和利益的角度讲，国家与人民的关系应该是权利与义务的辨证统一，企业亦如此，企业与员工之间的关系，应该是企业与员工双方共同努力，建立和谐合作，相互配合的良好组合关系，这样才能构建和谐的企业。     

论弱势群体权益的法律保护

社会弱势群体的存在是任何社会都不可避免的,因而如何对待社会弱势群体也就成了任何社会都不能回避的重大课题.保护与救济社会弱势群体是实现社会公正和法律实质正义的基本要求,因而如何通过立法来加强对弱势群体权益的保护,业已成为一个亟待解决的问题.弱势群体权益保护工作已逐步纳入我国法制建设的轨道,但是我国对于弱势群体权益保护的立法还有许多不足之处.社会弱势群体法律保护的基本内容应该围绕权利确认和权利保障展开,核心问题应该是在制度的构建方面努力.     

有翼高超声速再入飞行器气动设计难点问题

有翼高超声速再入飞行器是近年来的研究热点,气动设计是飞行器设计的关键。为了更清楚地认识有翼高超声速再入飞行器气动设计的难点问题,对有翼高超声速再入飞行器的发展、优势及总体任务剖面进行了介绍,从5个方面详细介绍了该类飞行器气动设计的难点问题,包括多约束复杂面对称气动布局设计、高温真实气体效应对气动特性影响、天地差异与天地换算方法、反作用控制系统(RCS)喷流干扰对气动特性的影响以及气动数据不确定度等,简要阐明了这些难点问题对总体设计的重要性以及初步的解决思路,为有翼高超声速再入飞行器气动设计提供了一些参考。     

Simulation and Analysis of Crashworthiness of Fuel Tank for Helicopters

Crashworthiness requirement of fuel tanks is one of the important requirements in helicopter designs. The relations among the protection frame, textile layer and rubber layer of the fuel tank are introduced. Two appropriate FE models are established, one is for an uncovered helicopter fuel tank without protection frame, and the other is for fuel tank with protection frame. The dynamic responses of the two types of fuel tanks impinging on the ground with velocities of 17.3 m/s are numerically simulated for the purpose of analyzing energy-absorbing capabilities of the textile layer and protection frame. The feasibility of the current crashworthiness design of the fuel tank is examined though comparing the dynamic response behaviors of the two fuel tanks.     

The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow

This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation.      

突破技术趋同，波音再现竞争优势

 波音公司面临着来自空客公司的巨大挑战,企业战略性创新才是公司成功的关键。为此波音公司的全部战略性研究集中在扩大产品的差异性上,体现在3个方面：电子化（e-Enabled）运营环境、整体复合材料机身部件的制造技术和支持波音787客机的全球协同环境（GCE）。     

临近空间飞行器测控与信息传输系统频段选择

 临近空间飞行器是高性能信息化武器平台,测控（TT&;C）与信息传输系统是其信息保障的核心,而选择合理、可行的频段是展开系统设计的前提和基础。频段选择影响到整个技术方案的制定,是一个需综合考虑、影响深远并具有战略意义的关键问题,从国际电联（ITU）国际标准、高速数传、接收信噪比（SNR）、“三抗”、超视距中继、黑障、雨衰以及设备研制成熟度8个方面全面、细致论证了近空间平台测控系统的频段选择问题,最终得出在视距链路中以Ka频段为宜,在超视距链路中以Ku/Ka双频段为宜的结论。     

基于弯曲激波压缩系统的高超声速进气道反设计研究进展

总结了近十年来弯曲激波压缩研究的主要成果。提出了弯曲激波压缩系统的新概念,即利用特殊设计的楔形弯曲压缩面或空间弯曲压缩面,产生一系列与前缘弱激波相互交汇或叠加的压缩波系,从而使前缘激波弯曲,形成特殊的弯曲激波,它与波后的等熵压缩波来共同完成对气流的压缩。在此基础上,实现了由给定出口气动参数的超声速内流道反设计,实现了由给定压缩面压力分布和给定压缩面马赫数分布要求的型面反设计,实现了由给定激波波面的压缩型面反设计。研究证明,弯曲压缩面-弯曲激波压缩系统具有良好的综合气动性能,为高性能高超声速进气系统的气动设计提供了一种全新的设计方法。     

Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance

In order to investigate the effects of fuel injection distribution on the scramjet combustor performance, there are conducted three sets of test on a hydrocarbon fueled direct-connect scramjet test facility. The results of Test A, whose fuel injection is carried out with injectors located on the top-wall and the bottom-wall, show that the fuel injection with an appropriate close-front and centralized distribution would be of much help to optimize combustor performances. The results of Test B, whose fuel injection is performed at the optimal injection locations found in Test A, with a given equivalence ratio and different injection proportions for each injector, show that this injection mode is of little benefit to improve combustor performances. The results of Test C with a circumferential fuel injection distribution displaies the possibility of ameliorating combustor performance. By analyzing the effects of injection location parameters on combustor performances on the base of the data of Test C, it is clear that the injector location has strong coupled influences on combus- tor performances. In addition, an inner-force synthesis specific impulse is used to reduce the errors caused by the disturbance of fuel supply and working state of air heater while assessing combustor performances.     

(高)超声速流动试验技术及研究进展

近年来,与高速飞行器相关的(高)超声速流动受到了极大的关注。这类流动所具有的非定常性、强梯度和可压缩性对试验方法和风洞设计技术提出了挑战。超声速纳米示踪平面激光散射(NPLS)技术是由作者所在团队研发的非接触光学测试技术。它能够以较高的空间分辨率来揭示超声速三维流场的一个瞬态剖面的时间解析的流动结构。介绍了NPLS技术以及基于NPLS开发的密度场测量、雷诺应力测量和气动光学波前测量等方法,并回顾了这些技术在超声速边界层、超声速混合层、超声速压缩拐角、激波/边界层相互作用和光学头罩绕流等流动中的应用,清晰地再现了边界层、混合层、激波等典型流场结构及其时空演化特性。另外,为了模拟和研究高空大气条件下边界层自然转捩和超声速混合层的转捩特性,介绍了高超声速静风洞、超-超混合层风洞的设计技术以及层流化喷管的设计方法。     

Research on Auto-detection for Remainder Particles of Aerospace Relay Based on Wavelet Analysis

Aerospace relay is one kind of electronic components which is used widely in national defense system and aerospace system. The existence of remainder particles induces the reliability declining, which has become a severe problem in the development of aerospace relay. Traditional particle impact noise detection (PIND) method for remainder detection is ineffective for small particles, due to its low precision and involvement of subjective factors. An auto-detection method for PIND output signals is proposed in this paper, which is based on direct wavelet de-noising (DWD), cross-correlation analysis (CCA) and homo-filtering (HF), the method enhances the affectiv-ity of PIND test about the small particles. In the end, some practical PIND output signals are analysed, and the validity of this new method is proved.