陕西高职高专院校评估工作分析与研究

通过分析陕西省高职高专院校人才培养工作的基本情况，总结了陕西高职高专评估工作的基本经验，指出了高职高专院校评估中存在的问题及解决对策。     

推进新时期科技工作的一些举措

迭起的世界科技革命的浪潮，促使全社会对科技工作愈来愈重视，新时期作好科技工作显得尤为重要。笔者从科技工作布局、青年人才培养、经费管理、成果推广等方面，对高校进一步做好科研工作进行了探讨。     

民航院校教材建设刍议

教材建设是一个系统工程，是学校基本建设之一，是整个教学工作的重要组成部分。民航的发展不仅为民航院校的教材工作带来了机遇和动力，同时也带来了挑战。本文通过对教材在教育工作中的地位和作用的论述，阐述了民航院校教材工作的重要性；并通过对当前民航院校教材工作中存在的问题的细致分析，提出了解决问题的具体措施，论证了民航院校在民航发展的新形势下，加强教材建设，推动民航教育的发展，是实现民航人才培养目标的重要途径。     

抓住机遇 不断进取 办出高等职业教育特色

高职高专学校的教育改革是一个系统工程，近些年来，我校按照重在改革，重在建设，重在质量，重在办出特色，全面提高的原则，以探索和建立具有时代特色、行业特色、高职特色和学校特色的人才培养模式为核心，以专业教学改革和试点专业建设为龙头，以全面提高人才培养质量为宗旨，确立了学校教育改革与发展总纲，对学校的教育教学工作进行了全面深入的改革。     

修订人才培养方案提高人才培养质量

为提高人才培养质量，根据形势不断发展的需要，对人才培养方案适时进行修订，制订出科学、可行和完善的人才培养方案至关重要。本文提出了在人才培养方案中加强基础教学、拓宽专业口径、整体优化知识结构和课程体系、压缩总学时和科学合理设置课程各模块比例、加强实践教学环节、加强计算机能力和外语能力的培养、辅修第二专业、实施课外人才培养方案等方面的研究方案和实践成果。     

加强产学合作搞好专业建设

以西安航专机械工程系在产学合作方面的实践为依据，探索了多种形式的高职教育校企产学合作的方式，构建了产学合作的人才培养机制，证明了开展产学合作是高职教育发展的必由之路，成功之路，对提高人才培养质量起到了积极作用。     

构建民航特色干部管理信息系统的探索与研究

<正>党的十八大以来，习近平总书记对于干部队伍建设发表了一系列重要讲话，对干部育选管用工作提出了新要求新标准。干部成长具有一定阶段性和规律性，早在上世纪九十年代初期，民航局就提出“跨世纪管理人才培养计划”，注重从源头培养抓起。经过几十年的发展，民航局在干部“选、育、评、用、督、退”全过程管理上积累了大量数据。     

培养优秀人才 促进民航发展--中国民用航空学院五十周年校庆采访录

５０年来，中国民航学院共为民航和社会培养输送了各类人才３万余名，在民航工作的毕业生占全行业职工总数的１／６，占民航工程技术和管理人员的１／２，被誉为“中国民航人才培养的摇篮”。面对未来民航发展对人才的需求，他们正在探索新的办学模式，培养出更多行业急需的系统人才     

论现代企业制度下的职工教育对策

本文阐述了职工教育适应现代企业制度要求的初步对策，认为要提高现代职教工作的水平，要继续巩固和发展岗位培训制度，要完善和加强在岗职工的学历教育和继续工程教育，要建立和健全“三高”人才培养制度，这样，企业驾驭市场竞争的能力才能得到足够的加强。     

浅谈事业发展与人才培养——访问加拿大观后感

介绍了加拿大人才培养、人事劳资管理概况，结合我所情况谈管理人才，专业队伍和人才培养等方面的几点体会。     

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。     

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.     

基于飞机油箱模型形状特征油量测量切片步长选择方法研究

 在分析飞机数字式油量测量过程中目前广泛使用的切片法油量测量原理的基础上,针对现有的定步长切片法无法得到准确、可靠的燃油质量特性数据库的缺陷,结合对飞机油箱模型形状特征的分析,提出了基于飞机油箱模型形状特征的油量测量切片步长选择方法。此方法包括切片步长整体和局部选择两个过程,整体选择以实现相邻两切片平面所夹油箱模型体积近似相等为目的来确定切片步长,以体现油箱模型截面整体变化规律;局部选择以设计切片平面与截面突变平面重合或尽可能接近的方式,突出油箱截面的局部变化特征。实验结果表明：该切片步长选择方法较定步长方法能够建立更为合理、可靠的燃油质量特性数据库,从而提高了油量测量精度。     

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.      

二维翼段颤振的μ控制

 采用超声电机作为作动器来实现含控制面的翼段颤振鲁棒抑制。针对作者设计的二维翼段颤振主动抑制系统，通过理论与实验相结合的方法，建立了考虑沉浮方向阻尼和作动器模型参数不确定性的控制系统模型，设计了μ控制器，并对控制器做了降阶处理。数值仿真和风洞试验表明，μ控制器可有效地抑制颤振的发生，将颤振临界速度提高23.4%。相对于H_∞控制器，μ控制器的控制效果和鲁棒性更好。     

航空发动机管路测量数据分割方法

 为了提高航空发动机管路测量数据的反求建模效率,提出了一种区域增长分割算法。该方法主要是利用管路表面在曲面索引系数映射、主曲率映射、高斯映射上的特性,并基于均值漂移算法和遗传算法提出了区域分割算法中种子区域的选择策略。然后利用区域增长分割方法实现了对管路测量数据的分割。经过仿真和实测数据验证,所提管路分割算法具有较好的分割质量和效率。     

Abnormal Shape Mould Winding

为解决网格化芯模的缠绕问题,本文提出了复合材料面片缠绕机理;接着详细分析了面片缠绕过程中的芯模凹曲面上纤维滑线和架空现象,应用微分几何曲面理论和空间几何理论,提出判据及其解决方案;最后,针对飞机发动机进气道的缠绕成型,编制缠绕控制程序并进行相应的实验,验证了面片缠绕方法的可行性。     

Interfacial Properties Modification of Carbon Fiber/ Polyarylacetylene Composites

This work was dedicated to performing surface oxidation and coating treatments on carbon fibers (CF) and investigating the changes of fiber surface properties after these treatments, including surface composition, relative volume of functional groups, and sur- face topography with X-ray photoelectron spectroscopy (XPS) and atom force microscopy (AFM) technology. The results show that, after oxidation treatments, interfacial properties between CF and non-polar polyarylacetylene (PAA) resin are remarkably modified by removing weak surface layers and increasing fiber surface roughness. Coating treatment by high char phenolic resin solution after oxida- tion makes interface of CF/PAA composites to be upgraded and the interfacial properties further bettered.     

Thermal Stresses and Cracks During the Growth of Large-sized Sapphire with SAPMAC Method

本文利用有限元法对冷心放肩微量提拉法(SAPMAC)生长大尺寸蓝宝石单晶过程中的热应力进行了模拟计算,应用临界缺陷理论解释了裂纹的萌生与扩展机理。研究表明,晶体内的热应力主要与晶体生长速率,环境温度和结晶取向有关;较大热应力多出现在结晶界面,放肩、收尾以及直径急剧变化等位置;最大热应力总是出现在籽晶与新生晶体的界面附近。裂纹将在临界缺陷位置产生,并在应力作用下沿a或m面扩展。计算结果与实验结果基本吻合,通过晶体生长系统和生长工艺的改进,对晶体的开裂问题得到了有效的抑制。     

Optimization Design System for Composite Structures Based on Grid Technology

To solve the topology optimization of complicated multi-objective continuous/discrete design variables in aircmit structure design, a Parallel Pareto Genetic Algorithm （PPGA） is presented based on grid platform in this paper. In the algorithm, the commercial finite element analysis （FEA） software is integrated as the calculating tool for analyzing the objective functions and the filter of Pareto solution set based on weight information is introduced to deal with the relationships among all objectives. Grid technology is utilized in PPGA to realize the distributed computations and the user interface is developed to realize the job submission and job management locally/remotely. Taking the aero-elastic tailoring of a composite wing for optimization as an example, a set of Pareto solutions are obtained for the decision-maker. The numerical results show that the aileron reversal problem can be solved by adding the limited skin weight in this system. The algorithm can be used to solve complicated topology optimization for composite structures in engineering and the computation efficiency can be improved greatly by using the grid platform that aggregates numerous idle resources.