复杂异型零件小直径螺纹优质高效加工工艺研究与应用

复杂异型壳体类零件广泛应用于航空发动机控制附件,此类零件表面分布有大量小直径螺纹孔,螺纹孔加工是影响整个壳体生产加工效率和精度的核心工序。该类零件现有的加工工艺存在一致性差、加工效率低、专用夹具多、铣螺纹时易出现正锥现象等缺点。针对上述问题,提出并设计专用螺纹铣刀对小直径螺纹孔进行加工,通过宏程序编程解决刀具刃部缩短带来的编程问题,采用刃部长度为1～3个螺距的专用螺纹铣刀,同种刀具即可实现相同螺距不同规格的螺纹孔加工。通过对两个批次的零件进行实际加工验证,结果表明：工艺优化方案可使小直径螺纹孔加工质量及加工效率得到显著提升。     

浅谈空客适航限制项目(ALS)的管理

从空客适航限制项目(ALS)的定义和分类出发,介绍了适航限制项目各个部分项目的来源、内涵意义及控制要求,分享了ALS的管理方法,提出从文件接收到文件评估以及将文件纳入客户化维修方案进行管理控制的完整管理方案,最后结合案例分享了ALS管理的成功经验,为航空公司管理空客适航限制项目提供参考。     

基于增强型离散相模型和化学燃烧的红外诱饵弹建模方法

红外（IR）诱饵弹是一种主要的红外对抗武器,建立一种准确的红外诱饵弹模型将对红外制导算法的研究起重要作用。目前,针对红外诱饵弹的计算机流体仿真（CFD）建模方法中,通常不考虑红外药剂的燃烧对红外模型产生的影响,这将从机理上直接导致建模精度下降。针对这一不足,本文在增强型离散相模型（DPM）红外诱饵弹建模方法的基础上加入了化学燃烧相,建立了准确性更高的仿真模型。实验结果表明,与原有的模型相比,加入化学燃烧相后的新模型在图形特征的仿真精度上有明显提升。     

IMPROVEMENTS IN HIDDEN LINE REMOVAL ALGORITHM FOR BI PARAMETRIC SURFACES

近些年来,随着计算机图形学,计算几何和计算机辅助设计与制造技术的发展,双参数曲面的消隐算法变得越来越重要。而现有的一些消隐算法,它们在计算量,存贮量和精度上都不太令人满意。本文引入面积坐标进行包含性检验,提出移动包围盒技术,给出了一种通用性强,贮存量小,准确性高,简单快速且易于在微机上实现的消隐算法。本文还给出了由Ｄｘｙ－８８０绘图仪绘制的多个实例效果。     

国际空间站标准化研究进展综述

国际空间站是载人航天系统工程的典型范例,其标准化工作为国际空间站的研制、建造和实施过程提供了重要准则和依据,对我国载人空间站工程具有重要借鉴意义。本文针对国际空间站标准化研究进展进行了综述,总结了国际空间站标准体系的特点和分类架构,梳理了国际空间站标准化管理的流程。基于国际空间站标准体系的剖析,提出了对我国载人空间站标准化体系建设的启示和思考,进一步明确了标准体系架构、环境控制与生命保障要求以及多边关系协调是载人空间站标准化体系建设的重要内容。     

航天嵌入式软件静态分析技术

软件故障已成为航天系统失败的重要因素.源代码级程序错误仍是航天嵌入式软件中最突出的问题之一,数组越界、算术溢出、除以零、指针错误、数据竞争等问题仍经常发生.静态分析能够在编译时通过分析源代码来推断程序运行时性质,是提高航天嵌入式软件安全性与可靠性的一种重要技术.首先将分析航天嵌入式软件的代码特征及常见错误.在此基础上,...     

Convergence Analysis of the Numerical Solution for Cathode Design of Aero-engine Blades in Electrochemical Machining

As a main difficult problem encountered in electrochemical machining （ECM）, the cathode design is tackled, at present, with various numerical analysis methods such as finite difference, finite element and boundary element methods. Among them, the finite element method presents more flexibility to deal with the irregularly shaped workpieces. However, it is very difficult to ensure the convergence of finite element numerical approach. This paper proposes an accurate model and a finite element numerical approach of cathode design based on the potential distribution in inter-electrode gap. In order to ensure the convergence of finite element numerical approach and increase the accuracy in cathode design, the cathode shape should be iterated to eliminate the design errors in computational process. Several experiments are conducted to verify the machining accuracy of the designed cathode. The experimental results have proven perfect convergence and good computing accuracy of the proposed finite element numerical approach by the high surface quality and dimensional accuracy of the machined blades.     

Enhancing the efectiveness of film cooling

Advanced gas turbine stages are designed to operate at increasingly higher inlet temperatures to increase thermal efficiency and specific power output.To maintain durability and reasonable life,film cooling is needed in addition to internal cooling,especially for the first stage.Film cooling lowers material temperature by forced convection inside film-cooling holes and by forming a layer of coolant about component surfaces to insulate them from the hot gases.Unfortunately,each cooling jet forms a pair of counter-rotating vortices that entrains hot gas and causes the film-cooling jet to lift off from the surface that it is intended to protect.This paper gives an overview of efforts to enhance the effectiveness of film-cooling.This paper also describes two new design concepts.One design concept seeks to minimize the entrainment of hot gases underneath of film-cooling jets by using flow-aligned blockers.The other design concept shifts the interaction between the approaching hot gas and the cooling jet to occur further above the surface by using an upstream ramp.For both design concepts,computational fluid dynamics results are presented to examine their usefulness in enhancing film-cooling effectiveness.      

跨声速涡轮叶栅三维流场的数值模拟

以具有试验测量数据的一个高压涡轮动叶中截面平面叶栅和一个高压涡轮导向器环形叶栅为对象,采用计算流体动力学(CFD)软件CFX-TASCflow,对两个涡轮叶栅的跨声速三维粘性流场进行了数值计算,验证了CFX-TASCflow软件在航空燃气涡轮设计计算中的可靠性,并对所研究的跨声速涡轮叶栅粘性流场进行了分析.      

偏流板对发动机进口温升影响研究

为研究偏流板升起条件下发动机进口温升的变化,采用计算流体动力学的方法,计算了不同的发动机推力状态、偏流板板位角、偏流板与发动机距离对流场和发动机进口温升的影响。结果表明:在偏流板升起时,随着发动机推力状态的升高,发动机进口温升逐渐增大;随着板位角的增大,高温燃气沿甲板向发动机进口方向扩散范围越大,进口温升逐渐增大;在相同发动机推力状态和板位角时,增加偏流板与发动机距离可显著减小发动机进口温升。