日本的数据中继试验卫星系统（DRTSS）

日本国家航天开发局（ＮＡＳＤＡ）已经在１９９５年使用工程试验卫星（ＥＴＳ）－ＶＩ进行了轨道间通信的基础实验，在ＥＴＳ－ＶＩ实验的基础上，于１９９７年发射通信与广播工程试验卫星（ＣＯＭＴＥＳ）。继ＥＴＳ－ＶＩ和ＣＯＭＥＴＳ之后，ＮＡＳＤＡ计划用两颗数据中继试验卫星（ＤＲＴＳ）进行高速率数传网络操作实验。ＤＲＴＳ预计于２０００年前后由Ｈ－Ⅱ火箭发动射升空，本次实验的目的是为地球观测国际空间站等日本航天     

机械零件图纸管理系统的设计与实现

本文介绍了基于ＯＲＡＣＬＥ关系数据库的叉车机械零件图纸管理系统ＭＤＭＳ（ＭａｃｈｉｎｅＤｒａｗｉｎｇＭａｎａｇｅｍｅｎｔＳｙｓｔｅｍ）该系统是一个集图纸的图形管理和图号（文本数据）管理为一体的图文数据库系统，该系统建立了与ＡＵＴＯＣＡＤ连接的接口，实现了在ＯＲＡＣＬＥ环境下显示ＡＵＴＯＣＡＤ图形的功能。     

SMALL TARGET TRACKING TECHNIQUE WITH DATA FUSION OF DISTRIBUTED SENSOR NET

ＳＭＡＬＬＴＡＲＧＥＴＴＲＡＣＫＩＮＧＴＥＣＨＮＩＱＵＥＷＩＴＨＤＡＴＡＦＵＳＩＯＮＯＦＤＩＳＴＲＩＢＵＴＥＤＳＥＮＳＯＲＮＥＴＣＨＥＮＧＨｏｎｇｗｅｉ（程洪玮）,ＺＨＯＵＹｉｙｕ（周一宇）,ＳＵＮＺｈｏｎｇｋａｎｇ（孙仲康）（Ｆａｃｕｌｔｙ４０６,...     

NUMERICAL STUDY OF TOPOLOGICAL STRUCTURE OF 3-D TRANSONIC VISCOUS FLOW FIELD (TVFF) INSIDE TURBINE CASCADE

ＮＵＭＥＲＩＣＡＬＳＴＵＤＹＯＦＴＯＰＯＬＯＧＩＣＡＬＳＴＲＵＣＴＵＲＥＯＦ３ＤＴＲＡＮＳＯＮＩＣＶＩＳＣＯＵＳＦＬＯＷＦＩＥＬＤ（ＴＶＦＦ）ＩＮＳＩＤＥＴＵＲＢＩＮＥＣＡＳＣＡＤＥＧｕｏＹａｎｈｕ，ＳｈｅｎＭｅｎｇｙｕ，ＷａｎｇＢａｏｇｕｏ（Ｄｅ...     

诊断专家系统基于故障树的知识获取

近年来，诊断专家系统（ＦＤＥＳ）得到了广泛的应用和发展，而知识获取被公认为是建造ＦＤＥＳ的一个瓶颈问题。本文提出了一种简捷、通用的知识获取方法：利用系统故障树（ＦＴ）进行知识获取。该法在给故障树增加诊断信息的基础上，通过求解故障树的割集自动生成ＦＤＥＳ的知识库。     

多通道动态测试分析系统

多通道动态测试分析系统张令弥,张春宁（南京航空航天大学振动所,南京,２１００１６）ＤＥＶＥＬＯＰＭＥＮＴＡＮＤＡＰＰＬＩＣＡＴＩＯＮＳＯＦＭＵＬＴＩ－ＣＨＡＮＮＥＬＤＹＮＡＭＩＣＴＥＳＴ＆ＡＮＡＬＹＳＩＳＳＹＳＴＥＭ（ＤＴＡＳ）ＺｈａｎｇＬｉｎｇｍｉ...     

ANALYSIS OF SHEAR STRESS DISTRIBUTION IN HONEYCOMB AIRCRAFT WING STRUCTURE SUBJECTED TO (S.T.) TORQUE

ＡＮＡＬＹＳＩＳＯＦＳＨＥＡＲＳＴＲＥＳＳＤＩＳＴＲＩＢＵＴＩＯＮＩＮＨＯＮＥＹＣＯＭＢＡＩＲＣＲＡＦＴＷＩＮＧＳＴＲＵＣＴＵＲＥＳＵＢＪＥＣＴＥＤＴＯ（Ｓ．Ｔ．）ＴＯＲＱＵＥＫｈａｌｉｄＭ．Ｔａｈｉｒ，ＺｈａｎｇＸｉｎｇ（ＤｅｐａｒｔｍｅｎｔｏｆＦ...     

DENDRITE REFINING AND EUTECTIC TRANSFORMATION BEHAVIOR OF NICKEL-BASE SINGLE CRYSTAL (NBSC) SUPERALLOY

ＤＥＮＤＲＩＴＥＲＥＦＩＮＩＮＧＡＮＤＥＵＴＥＣＴＩＣＴＲＡＮＳＦＯＲＭＡＴＩＯＮＢＥＨＡＶＩＯＲＯＦＮＩＣＫＥＬ┐ＢＡＳＥＳＩＮＧＬＥＣＲＹＳＴＡＬ（ＮＢＳＣ）ＳＵＰＥＲＡＬＬＯＹＤｕＷｅｉ（杜炜），ＬｉＪｉｎｓｈａｎ（李金山），ＬｉＪｉａｎｇｕｏ...     

ANALYSIS OF LOCATION ACCURACY FOR AN EMITTER USING SATELLITE- MOUNTED INTERFEROMETER

ＡＮＡＬＹＳＩＳＯＦＬＯＣＡＴＩＯＮＡＣＣＵＲＡＣＹＦＯＲＡＮＥＭＩＴＴＥＲＵＳＩＮＧＳＡＴＥＬＬＩＴＥ┐ＭＯＵＮＴＥＤＩＮＴＥＲＦＥＲＯＭＥＴＥＲＺｈｏｕＹｉｙｕ（周一宇）,ＧｕｏＺｈｉｇａｎｇ（郭志刚）（ＮａｔｉｏｎａｌＵｎｉｖｅｒｓｉｔｙｏｆＤ...     

RESEARCH ON KINEMATIC DEXTERITY OF REDUNDANT MANIPULATORS

ＲＥＳＥＡＲＣＨＯＮＫＩＮＥＭＡＴＩＣＤＥＸＴＥＲＩＴＹＯＦＲＥＤＵＮＤＡＮＴＭＡＮＩＰＵＬＡＴＯＲＳＣＨＥＮＷｅｉｈａｉ（陈伟海）,ＺＨＡＮＧＱｉｘｉａｎ（张启先）,ＹＡＮＧＺｏｎｇｘｕ（杨宗煦）,ＬＩＪｉａｎ（李健）（ＩｎｓｔｉｔｕｔｅｏｆＲｏｂ...     

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。     

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。     

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。     

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.     

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.     

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。     

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）。     

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。     

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.      

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。