普惠公司完成XTC67/1核心机试验

为达到IHPTET计划第三阶段目标,普惠公司进行了XTC67/1核心机试验。该公司在实施XTC67/1计划中取得了一些成果,但也存在一些问题     

预研核心机压气机盘和涡轮盘强度试验

在轮盘超转试验器上对带叶片的第二、四级压气机盘和涡轮盘进行了24-105%转速下的常温应变测量及加温超转试验。试验结果表明，理论计算值与试验结果吻合，盘的强度储备足够。     

核心机和验证机—航空动力研究与发展中必不可少的重要阶段

本阐明了核心机和验证机在航空发动机研究与发展工作中的重要性，指出了当前存在的问题，提出了解决问题的措施和建议。     

大涵道比涡扇发动机核心机试验性能评定方法

为了在试验验证阶段准确、全面地剖析涡扇发动机核心机性能,基于核心机多次试验结果,提出在工程中易实现的核心机性能评定方法。通过试验确定测量参数,介绍核心机性能评定工作流程,论述性能评定关键参数的测量和计算方法。分析部件流量、效率等参数变化对核心机循环功及油耗的影响,以涡轮为例阐述部件试验与核心机试验差异的原因包含气动构型、工作环境、测量不确定度、冷气4个维度的因素,论述了通过减少漏气、优化工作线等手段提升部件效率,讨论核心机流量、循环功、耗油率对整机的支撑作用。核心机与部件偏离的合理范围应参照测量不确定度,超出合理范围的偏离采用了单因素敏感性分析方法分解到部件层级。结果表明：该方法适用于大涵道比涡扇发动机核心机试验性能评定,对其他构型的核心机也有一定借鉴作用。     

"系列核心机及派生发展"的航空发动机发展思路

核心机的派生发展一直受到航空发达国家的高度重视，并成为发动机系列化发展的主要技术途径。根据我国目前的发动机发展现状。本文提出了“系列核心机及派生发展”的发动机发展思路，对核心机技术及核心机的派生发展进行了讨论和分析。详细介绍了5个核心机的基本参数，通过这5个核心机派生发展形成的系列化发动机，其推力可以覆盖200～20000daN范围，基本能够满足我国军民用飞机发展对动力装置的需求。     

核心机系列发展方法在5kg/s流量级核心机上的应用研究

在研究国内外核心机系列发展研究成果的基础上,以中国燃气涡轮研究院研制的5 k N推力涡扇发动机的5 kg/s流量级核心机为平台,开展了核心机派生发展10 k N推力中等涵道比涡扇发动机的应用研究。通过对派生发动机方案实施效果的分析,验证了核心机派生发展发动机技术途径的可行性。归纳了系列发展在核心机设计时应考虑的主要因素,以及发展大推力跨度和不同用途发动机时核心机所需的改进设计。     

Dust Environment Modelling of Comet 67P/Churyumov-Gerasimenko

Dust is an important constituent of cometary emission; its analysis is one of the major objectives of ESA’s Rosetta mission to comet 67P/Churyumov-Gerasimenko (C–G). Several instruments aboard Rosetta are dedicated to studying various aspects of dust in the cometary coma, all of which require a certain level of exposure to dust to achieve their goals. At the same time, impacts of dust particles can constitute a hazard to the spacecraft. To conciliate the demands of dust collection instruments and spacecraft safety, it is desirable to assess the dust environment in the coma even before the arrival of Rosetta. We describe the present status of modelling the dust coma of 67P/C–G and predict the speed and flux of dust in the coma, the dust fluence on a spacecraft along sample trajectories, and the radiation environment in the coma. The model will need to be refined when more details of the coma are revealed by observations. An overview of astronomical observations of 67P/C–G is given, because model parameters are derived from this data if possible. For quantities not yet measured for 67P/C–G, we use values obtained for other comets, e.g. concerning the optical and compositional properties of the dust grains. One of the most important and most controversial parameters is the dust mass distribution. We summarise the mass distribution functions derived from the in-situ measurements at comet 1P/Halley in 1986. For 67P/C–G, constraining the mass distribution is currently only possible by the analysis of astronomical images. We find that both the dust mass distribution and the time dependence of the dust production rate of 67P/C–G are those of a fairly typical comet.     

A Portrait of the Nucleus of Comet 67P/Churyumov-Gerasimenko

In 2003, comet 67P/Churyumov–Gerasimenko was selected as the new target of the Rosetta mission as the most suitable alternative to the original target, comet 46P/Wirtanen, on the basis of orbital considerations even though very little was known about the physical properties of its nucleus. In a matter of a few years and based on highly focused observational campaigns as well as thorough theoretical investigations, a detailed portrait of this nucleus has been established that will serve as a baseline for planning the Rosetta operations and observations. In this review article, we present a novel method to determine the size and shape of a cometary nucleus: several visible light curves were inverted to produce a size–scale free three–dimensional shape, the size scaling being imposed by a thermal light curve. The procedure converges to two solutions which are only marginally different. The nucleus of comet 67P/Churyumov–Gerasimenko emerges as an irregular body with an effective radius (that of the sphere having the same volume) = 1.72 km and moderate axial ratios a/b = 1.26 and a/c = 1.5 to 1.6. The overall dimensions measured along the principal axis for the two solutions are 4.49–4.75 km, 3.54–3.77 km and 2.94–2.92 km. The nucleus is found to be in principal axis rotation with a period = 12.4–12.7 h. Merging all observational constraints allow us to specify two regions for the direction of the rotational axis of the nucleus: RA = 220°^+50° _−30° and Dec = −70^° ± 10^° (retrograde rotation) or RA = 40°^+50° _-30° and Dec = +70^°± 10^° (prograde), the better convergence of the various determinations presently favoring the first solution. The phase function, although constrained by only two data points, exhibits a strong opposition effect rather similar to that of comet 9P/Tempel 1. The definition of the disk–integrated albedo of an irregular body having a strong opposition effect raises problems, and the various alternatives led to a R-band geometric albedo in the range 0.045–0.060, consistent with our present knowledge of cometary nuclei. The active fraction is low, not exceeding ~ 7% at perihelion, and is probably limited to one or two active regions subjected to a strong seasonal effect, a picture coherent with the asymmetric behaviour of the coma. Our slightly downward revision of the size of the nucleus of comet 67P/Churyumov-Gerasimenko resulting from the present analysis (with the correlative increase of the albedo compared to the originally assumed value of 0.04), and our best estimate of the bulk density of 370 kg m⁻³, lead to a mass of ~ 8 × 10¹² kg which should ease the landing of Philae and insure the overall success of the Rosetta mission.     

碳纤维、芳纶纤维、蜂窝芯零件数控加工刀具的选用

通过以下所述刀具材料的选择以及加工中应注意的事项,可以很好地完成这些复合材料零件的数控加工。但复合材料的范围很广泛,各种材料由于其结构和性能不同,其加工所使用的刀具及其结构、所使用的参数各不相同,在好多方面我们还应努力研究与摸索,制造出更好的复合材料零件。     

Leap项目进展顺利

首台Leap-1A发动机于2013年9月4日开始试车,进入早期评估阶段,预计在2016年取得适航证并随A320neo投入商业运营。     

A380的试飞历程

在空中客车公司投入试飞的5架 A380试飞原型机完成了2600小时的飞行试验之后,2006年12月12日,欧洲航空安全局(EASA)和美国联邦航空局(FAA)的官员正式向装配罗一罗公司遄达900发动机的 A380巨型客机颁发了型号合格证(TC),A380的飞行试验计划取得重大进展,但是目前工作仍未结束。     

GP7200准备试验和取证

GE-普惠发动机联盟公司将用8台发动机和1台核心机进行GP7200发动机的试验和取证计划。今年将有7台发动机和1台核心机投入试验,预计首架装GP7200的A380-800将在2006年10月交付运营     

Modeling of Heat Conduction in Thermoplastic Honeycomb Core/Face Sheet Fusion Bonding

Honeycomb sandwich materials have been widely used in aerospace industry as secondary structural materials or interior panels. Recently the research of full thermoplastic honeycomb sandwich materials has been of interest due to their recyclability. In their production, they usually demand an adhesive-free process, namely fusion bonding, to connect thermoplastic honeycomb core and face sheets. It is a heat induced process where a parameter of temperature should be well controlled to guarantee the product quality. This article presents a mathematical model of heat conduction to analyze the transient temperature distribution from heating tools towards inner part of the core under fusion bonding conditions. In order to simplify the complexity of 3D honeycomb geometry, a homogenization method is used to obtain average thermal properties of the honeycomb along the major heat flux direction. The model is validated by comparing with the results of in-situ temperature measurement during fusion bonding. The presented model can also be applied to analyzing general out-of-plane heat conduction through honeycomb sandwich structures made from other materials.     

打造世界一流试飞机构 中航工业飞行试验研究院50年试飞经典回顾

50年峥嵘岁月,像50笔铁画银钩,浓墨重彩地抒写了中国航空试飞业发展的辉煌历程;50年经典的试飞项目回顾,衬映出中国航空工业的成长足迹。     

环境试验简介

介绍了环境试验的目的、分类及其应用,重点介绍实验室环境试验在各个阶段的应用。