A320neo的初始商业运营之路不平坦

正A320neo飞机的节油效率超过了预期,但PW1100G-JM发动机还有一些问题需要解决。相对而言,配装LEAP-1A发动机的A320neo虽然"起步"较晚,但运行平稳。空客A320neo(新发动机选项)已服役一年多,航空公司、空客公司及其主要供应商都从中获得了一定的运行经验。到目前为止,A320neo飞机经历了不寻常     

工业动态

<正>哈飞完成首架直15尾梁对接近日,首架直15(AC352)直升机在中航工业哈飞实现尾梁对接,这是该架机交付总装车间后完成的第一个大部件组装,标志着哈飞向直15首飞的目标又迈进了一步。空客A320neo完成首飞9月25日,首架空客A320neo飞机的首次测试飞行取得圆满成功。首飞的A320neo装配了由普惠公司生产的PW 1100G-JM发动机,起飞时飞机重量约60吨。此次首飞为A320neo项目共计3000小时的测试飞行拉开了序幕,空客将投入4架A320neo、2架A319neo和2架A321neo进行相关取证工作,分别配装PW1100G-JM发动机和CFM国     

Ameco完成国内首台PW1100G发动机QEC装配

正近日,Ameco西南航线中心历时4天完成了国内首台PW1100G-JM发动机QEC(发动机快速拆换件)装配工作。随着这台发动机QEC装配工作的顺利完成,标志着Ameco西南航线中心在该项工作维修能力迈出了实质性的一步,为后续A320neo飞机的定检和换发工作打下坚实基础,并积累了经验。     

普惠GTF发动机故障对空客A320neo交付和运营产生影响

正普惠公司PW1100G-JM发动机近期出现了一系列故障,造成多家航空公司的A320neo遭遇停飞,对A320飞机的交付和运营产生了不利的影响。目前,普惠公司正积极解决这些问题,并推出一系列解决方案,力图挽回故障造成的损失,实现GTF发动机与A320neo飞机的更好匹配。     

静洁动力系列发动机蓄势待发

今年9月25日,配装PW1100G—JM发动机的A320neo飞机在法国图卢兹完成了历时2．5h的首次试飞,标志着A320neo项目3000h试飞活动的正式启动。     

PW1100发动机防止空中停车的研究

针对PW1100发动机故障隐患导致的空中停车进行了细致的分析,找出了问题原因,提出了改进方法,并在发动机的实际维修过程中采取了一系列有效措施,实践证明收效显著,使A320neo飞机配装的PW1100发动机的空中停车率大幅下降,保证了飞行安全。     

A320neo开始取证试飞

9月25日，以普惠PW1100G-JM为动力，生产序列号为MSN6101的首架A320neo飞机，从空客总部法国图卢兹布拉尼亚克机场起飞，经过约150min的飞行后，顺利返回机场。A320neo的成功首飞拉开了其取证试飞的大幕。     

普惠庆祝雄鹰服务亚洲公司建成GTF大修能力一周年

2月11日,普惠公司庆祝其新加坡发动机中心暨雄鹰服务亚洲公司(ESA)形成PW1100G-JM齿轮涡扇发动机(GTF)衍生型号大修能力一周年。该生产线能力是普惠新加坡中心价值8500万美元现代化升级的组成部分,该中心是亚太地区的三座GTF发动机中心之一。这座经过现代化升级的设施可处理多条发动机大修生产线,满足包括PW4000系列、GP7200与GTF PW1100G-JM发动机在内的多种发动机型号需要,以及重新配置普惠雄鹰服务亚洲公司的发动机测试能力以适配GTF发动机型号所需。继2019年1月接收首台GTF PW1100G-JM衍生型号发动机进厂大修后,普惠雄鹰服务亚洲公司正按计划在完成其现代化升级后提速生产,计划今年将GTF发动机的大修数量增加一倍以上。     

空客启动A320NEO项目

近日．空客公司宣布为A320系列推出新型发动机选装方案．两种方案分别是CFM国际公司的LEAP-X发动机和普惠公司生产的”静洁动力”PW1100G发动机。装配新款发动机的A320系列飞机被称为A320NEO。A320NEO还将装配”鲨鳍”翼梢小翼．空客公司计划从2016年春季开始交付客户。     

民航动态

正空客总装第8000架A320系列飞机交付国航2月2日,空客公司在空中客车天津交付中心向国航交付空客总装的第8000架A320系列飞机。该架飞机为空客A320neo飞机,由位于中国天津的空中客车亚洲总装线完成总装。该架A320neo飞机使用普惠公司静洁动力PW1100G发动机,采用了舒适的两级客舱布局。截至2018年1月底,国航共运营200架空客飞机,其中包括141架A320系列飞机和59架     

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。