愿景型领导力的影响因素及其作用机理

愿景型领导力对推动企业持续成长发挥着重要作用,其核心任务是实现从个人愿景到公司愿景的转化,据此提出该转化的五阶段模型,并阐述了愿景型领导力形成的四大关键影响因素:领导者素质、追随者心态、领导-部属交换关系以及企业文化.最后,将关键影响因素嵌入动态的五阶段模型中,揭示愿景型领导力的动态作用机理.     

SA烟草公司烟草商业物流绩效评价的实证分析

根据物流绩效评价指标体系,利用模糊综合评价法建立绩效评价模型,对SA烟草公司烟草商业物流绩效进行了综合评价,最后经过实际分析,验证了模型的可行性和实用性。     

模糊综合评价模型的R语言实现

利用R语言可跨平台操作以及对矩阵运算高速的特点,对改进的模糊综合评价模型进行了实现,并给出了实现各流程的实例,验证了R语言实现模糊综合评价模型在不同操作系统下运行的可靠性及有效性。     

航空高科技企业经营决策者胜任特征推导模型实证研究

 遵循社会科学的实证研究方法,在前期行为事件访谈基础上形成问题,自编胜任特征行为测量问卷,对104名航空高科技企业经营决策者进行测试,研究其胜任特征内涵,进而建立推导模型。研究结果表明,可以基于以下5个因子建立中国航空高科技企业经营决策者胜任特征推导模型,包括成就与创新、责任与激情、战略与执行、合作与沟通、正直与诚信。该推导模型对航空高科技企业乃至军工制造业经营决策者的选拔、领导力提升、评价与激励等人力资源管理方面具有理论指导与技术支持的价值。该研究期望通过对实际情况的研究,抽取供管理实践借鉴的特征模型,提升管理实践的科学性、规范性。     

基于人为因素的航空安全模糊综合评价研究

人为因素的控制是航空安全事故预防与控制的关键,通过分析人为因素对航空安全的影响,结合各方面专家的研究成果,建立了基于人为因素的航空安全综合评价体系,利用层次分析法确定了各评价指标权重,构建了模糊综合评价模型,并对人为因素对航空安全的影响进行了综合评价,得出了影响航空安全主要人为因素的综合评价等级。研究结果表明,航空安全状态良好,可以达到飞行安全的目的。     

基于AHP层次分析和模糊评判的教学质量评价

通过层次分析法建立评价体系的层次排序,以此建立教学质量评价的模糊综合评判模型,之后利用模糊评判法对教师教学质量进行综合得分评价,实现学院教学评价管理的科学性和合理性。     

灰色多层次综合评判模型在评价经济效益中的作用

目前,关于企业经济效益的综合评价方法莫衷一是,本文将关联度分析方法用于分析具有层次结构的复杂系统,建立了灰色多层次综合评判模型,应用该模型对某国营企业进行了实证分析,得到了较好的结果。     

用多元分析方法进行多指标综合评价

本文以多元分析为理论基础,以1986年29个省、市机械工业部门的经济效益评价为背景,利用主成份分析,建立了多指标综合评价的模型并得到了令人满意的评价结果,从而对多指标综合评价问题的研究进行了有益的尝试和探索。     

航空工业企业知识管理绩效评价研究

针对培养航空工业企业核心能力的问题,从知识管理的角度分析了基于运作层、战术层和战略层在评价知识管理绩效时应该考虑的因素,给出了评价指标体系并建立了模糊综合评价模型,最后对评价工作提出了若干建议.     

企业文化定量评价方法的研究

针对目前评价企业文化的方法在定量分析方面的不足，应用模糊数学理论建立了一个企业文化模糊综合评价模型是一个企业文化产例加以说明，为企业家决策提供科学依据。     

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.      

ν-gap度量及其在飞行控制律评估中的应用

 传统控制律评估方法主要用于单输入单输出（SISO）系统，且对模型参数摄动考虑不够全面,针对这些不足，研究了ν-gap度量方法。在介绍系统广义稳定裕度相关概念的基础上，给出了ν-gap度量的定义、特点和性质以及近似摄动模型的计算，提出ν-gap度量评估控制律的步骤。实例结果表明，该方法不仅克服了上述传统评估方法的缺陷，而且还有根据所求的各摄动影响情况忽略影响小的元素，以减少计算量及可以找到最坏情况下的参数摄动组合等优点。     

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。     

Integrated Entry Guidance for Reusable Launch Vehicle

A method for the implementation of integrated three-degree-of-freedom constrained entry guidance for reusable launch vehicle is presented. Given any feasible entry conditions, terminal area energy management interface conditions, and the reference trajectory generated onboard then, the method can generate a longitudinal guidance profile rapidly, featuring linear quadratic regular method and a proportional-integral-derivative tracking law with time-varying gains, which satisfies all the entry corridor constraints and meets the requirements with high precision. Afterwards, by utilizing special features of crossrange parameter, establishing bank-reversal corridor, and determining bank-reversals according to dynamically adjusted method, the algorithm enables the lateral entry guidance system to fly a wide range of missions and provides reliable and good performance in the presence of significant aerodynamic modeling uncertainty. Fast trajectory guidance profiles and simulations with a reusable launch vehicle model for various missions and aerodynamic uncertain-ties are presented to demonstrate the capacity and reliability of this method.     

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。