民航机务维修标准工时管理常见问题与解决方法探讨

维修工时管理和控制是维修生产运行和控制中的一个重要组成部分,但标准工时的评估和采集存在一定的困难。本文对当前行业标准工时管理方面普遍存在的难点问题进行分析,基于某公司积累的管理数据,提出一些可行方案,以使民航维修标准工时的管理更加准确、有效。     

关于我国民航维修工卡无纸化发展的若干问题思考

通过深入了解民航维修工卡无纸化的定义、优势,以及维修工卡无纸化发展中面临的难题与应对措施,探索我国民航维修工卡无纸化未来的发展趋势。     

使用中的民用航空器的质量保证

本文从建立新型的质量保证机构，做到与国际惯例接轨；采用民用航空适航规章，保证维修质量；实施全过程的质量管理等三个方面简述了民航维修单位对民用航空器在使用中的维修质量保证情况。     

关于DMM／FH验证的设想

对每飞行小时维修工作中维修工时的含义及数据采集进行了讨论,对直接维修工时和间接维修工时的标准包括内容及保证采集数据的有效性,充分性做了具体探讨,在此基础上提出了数据采集的方法,并以直接维修工时统计实例进行了说明。     

浅析民航维修人员心理健康对安全生产的影响

通过对某民航维修单位开展心理调研,结合人为因素分析和归类系统—维修延伸分析模型,关联得出该维修单位易发生的不安全行为和人员状况,并在此基础上提出民航维修单位提升员工心理健康水平的建议和对策,以减少人为因素造成的不安全事件。     

维修单位规章标准整合初探

航空器维修是民航事业的重要组成部分,各维修单位一般是根据自身的业务、经济和人文状况形成适合自己的管理体系.     

属地化后机场飞机维修面临的问题及发展初探

由于体制原因,过去有的单位对机场飞机维修工作重视程度不够,机场属地化后的这几年,通过对机场飞机维修工作的适航年检和独立航线维修单位自我质量审核,发现机场的飞机维修工作,尤其是中小机场的飞机维修工     

民航维修系统分层次审核体系研究

<正>随着民航机队规模不断扩大，维修系统工作不断增长，质量管理的链条越来越长，管理的幅度和难度不断增加。维修系统纷纷运用不同的审核模式，对维修工作程序的完整性、维修工作的有效性及其与适航规章的符合性的监督，加强维修系统的质量管理，保证飞机的维修质量。然而，要实现安全质量管理齐抓共管，提升安全质量管理的效率及效果，就必须充分发挥民航维修系统外部监督以及内部管理者、班组长、质量人员的共同作用。     

面向未来的民航自治化维修

在分析自治化维修中的概念与关键技术的基础上,提出把自治化维修应用到面向未来的民航维修领域,进而对数字化维修的理论的构成、实现和关键技术进行了初步探讨,确定了民航实现自治化维修的途径和方法。     

南方航沈阳维修基地

南方航沈阳维修基地是南航集团下属的大型综合飞机维修企业,可以独立完成MD82飞机1D检、MD82飞机2D检、MD90飞机4C检、飞机整机喷漆、A300飞机8C检、并取得了ISO9002国际质量认证和美国联邦航空局FAA飞机部附件维修许可。沈阳维修基地有着40年安全维修的辉煌历史,多年来,沈阳维修基地先后被中国民航总局、辽宁省政府等单位授予“全国民航质量管理先进单位”“、辽宁省用户满意企业”、“全国民航先进基层党组织”、“精神文明建设先进单位”等60余种荣誉称号。南方航沈阳维修基地     

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.      

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。     

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。     

Research on Auto-detection for Remainder Particles of Aerospace Relay Based on Wavelet Analysis

Aerospace relay is one kind of electronic components which is used widely in national defense system and aerospace system. The existence of remainder particles induces the reliability declining, which has become a severe problem in the development of aerospace relay. Traditional particle impact noise detection (PIND) method for remainder detection is ineffective for small particles, due to its low precision and involvement of subjective factors. An auto-detection method for PIND output signals is proposed in this paper, which is based on direct wavelet de-noising (DWD), cross-correlation analysis (CCA) and homo-filtering (HF), the method enhances the affectiv-ity of PIND test about the small particles. In the end, some practical PIND output signals are analysed, and the validity of this new method is proved.