大飞机

Bloy, AW; Joumaa, M

New ground vibration testing techniques for large aircraft computation

Gloth, G; Degener, M; Fullekrug, U; et al.

The use of evacuation modelling techniques in the design of very large transport aircraft and blended wing body aircraft

Galea, ER; Blake, SJ; Gwynne, S; et al.

The lateral dynamic stability and control of a large receiver aircraft during air-to-air refuelling

Bloy, AW; Lamont, PJ; Abuassaf, HA; et al.

一代材料技术，一代大型飞机

曹春晓

大飞机用铝合金的研究现状及展望

刘兵，彭超群，王日初，等

大飞机

·编者按·

“大飞机”或“大型飞机”一般是指起飞总质量超过100 t的运输类飞机，包括军用、民用大型运输机，也包括一次航程达到3000 km的军用或乘坐达到100座以上的民用客机。中国把150座以上的干线客机称作大客机。大飞机技术复杂，制造周期长，质量要求高，被称为“现代制造业的一颗明珠”，具有气动外形要求严格、设计更改频繁、产品构型众多、零件材料和形状各异、内部结构复杂、空间紧凑、各类系统布置密集以及零组件数量巨大等特点。

大飞机是一个国家军事战略的重要技术支柱，也是国家经济的重要领域。大飞机的设计制造集成国内前沿高新技术，是国家基础工业水平的体现，同时可以提升国家整体技术水平。2017年5月5日，我国国产大飞机C919在经历了100多个测试项目以后，首飞成功。首飞成功后，C919将转入适航取证阶段，这将意味着其距离面向市场更进一步。有关专家指出，适航取证将是一个长期的任务。

·热点数据排行·

截至2017年5月12日，中国知网（CNKI）和Web of Science（WOS）的数据报告显示，以“大飞机”为词条可以检索到的期刊文献分别为1143、476条，本专题将相关数据按照：研究机构发文数、作者发文数、期刊发文数、被引用频次进行排行，结果如下。

研究机构发文数量排名（CNKI）

研究机构发文数量排名（WOS）

作者发文数量排名（CNKI）

作者发文数量排名（WOS）

期刊发文数量排名（CNKI）

期刊发文数量排名（WOS）

根据中国知网（CNKI）数据报告，以“大飞机”等为词条可以检索到的高被引论文排行结果如下。

国内数据库高被引论文排行

根据Web of Science统计数据，以“大飞机”为词条可以检索到的高被引论文排行结果如下。

国外数据库高被引论文排行

·经典文献推荐·

基于Web of Science检索结果，利用Histcite软件选取LCS（Local Citation Score，本地引用次数）TOP 30文献作为节点进行分析，得到本领域推荐的经典文献如下。

A brief summary of previous works is followed by an in-depth analysis of velocities, circulations, and decay histories of a number of trailing vortices generated by large aircraft during field tests in Memphis, Tennessee. The results suggest that the decay of trailing vortices is governed by the mutual straining of vortices; intermittent exchange of mass, momentum, and vorticity across the core boundary; rotational damping and restructuring of turbulence in the core; stretching of large turbulent structures, turbulent diffusion, and the interaction of oppositely signed vorticity in the overlapping regions of the vortex pair; and the draining of vorticity from the Kelvin oval.

来源出版物：AIAA Journal, 1998, 36(9): 1671-1679

Trailing vortex effects on large receiver aircraft

Bloy, AW; Joumaa, M

Abstract: The aerodynamic forces and moments on the Hercules receiver aircraft, due to its horizontal and vertical position and hank, yaw, and pitch attitudes in the wake of the KC10 tanker aircraft, are assessed relative to the receiver's aerodynamic characteristics in free air. Large changes in lift, drag, and pitching moment are predicted near the tanker wake centerline. As the receiver is displaced sideways towards the tanker wingtip vortices it experiences large side force and yawing moment and particularly high rolling moment. The most significant term due to the receiver attitude is the rolling moment due to bank.

来源出版物：Journal of Aircraft, 1995, 32(6): 1198-1204

New ground vibration testing techniques for large aircraft computation

Gloth, G; Degener, M; Fullekrug, U; et al.

Abstract: A ground vibration test on the prototype of a new aircraft is often regarded as necessary in order to make reliable flutter predictions for flight tests and to update the mathematical model of the aircraft. Due to very high development costs for such aircraft, the goal is to strive for a significantly shorter testing time. However, a degradation in the quality or reliability of the results is not acceptable because of the great impact they have on flutter stability. The French ONERA and the German DLR are cooperating on a test project to meet the necessary requirements. New techniques and test strategies were proven in a joint ground vibration test on an Airbus A340-300 in 1999. This article summarizes the approach and results of the project.

来源出版物：SV Sound and Vibration, 2001, 35(11): 14-18

The use of evacuation modelling techniques in the design of very large transport aircraft and blended wing body aircraft

Galea, ER; Blake, SJ; Gwynne, S; et al.

Abstract: Very Large Transport Aircraft (VLTA) pose considerable challenges to designers, operators and certification authorities. Questions concerning seating arrangement, nature and design of recreational space, the number, design and location of internal staircases, the number of cabin crew required and the nature of the cabin crew emergency procedures are just some of the issues that need to be addressed. Other more radical concepts such as blended wing body (BWB) design, involving one or two decks with possibly four or more aisles offer even greater challenges. Can the largest exits currently available cope with passenger flow arising from four or five aisles? Do we need to consider new concepts in exit design? Should the main aisles be made wider to accommodate more passengers? In this paper we demonstrate how computer based evacuation models can be used to investigate these issues through examination of staircase evacuation procedures for VLTA and aisle/exit configuration for BWB cabin layouts.

来源出版物：The Aeronautical Journal (1968), 2003, 107(1070): 207-218

The lateral dynamic stability and control of a large receiver aircraft during air-to-air refuelling

Bloy, AW; Lamont, PJ; Abuassaf, HA; et al.

Abstract: The lateral dynamic stability and control of a large receiver aircraft was considered during air-to-air refuelling. A simple aerodynamic model was developed in order to determine the aerodynamic forces and moments acting on the receiver aircraft due to the tanker aircraft's vortex field. These forces and moments were then expressed in derivative form and included in the linearised equations of motion. Solution of these equations revealed a divergent oscillation, characteristic of air-to-air refuelling and consisting mainly of bank and sideways displacements. An approximation to this mode, which highlights two important aerodynamic derivatives was made. The values of these derivatives depend mainly on the vertical separation between the tanker and receiver aircraft and the ratio of the tanker-to-receiver aircraft wing spans. In flight, it appears that the pilot controls the divergent mode by frequent alternate movements of the ailerons.

来源出版物：The Aeronautical Journal (1968), 1986, 90(896): 237-243

·推荐综述·

一代材料技术，一代大型飞机

曹春晓

2007年2月26日，温家宝总理主持召开国务院常务会议，原则批准大型飞机研制重大科技专项正式立项，引起了国内外的高度关注。

一百多年来，材料与飞机一直在相互推动下不断发展。“一代材料，一代飞机”正是世界航空发展史的一个真实写照。飞机机体材料结构在大体上经历了4个阶段的发展后，正跨入第5阶段。

显然，大型飞机在机体材料上的变化正反映了这一趋势，并在选材等方面充分体现了“一代材料技术，一代大型飞机”这一辩证的互动关系。

作为借鉴，本文首先归纳分析了欧美新一代大型飞机的材料技术特色，然后在此基础上结合中国具体情况提出一些关于中国大型飞机选材原则的建议。

1 欧美新一代大型飞机的材料技术特色

1.1 复合材料和钛合金的用量创历史新高

从波音787开始，50%用量的复合材料成为未来飞机的起点，也就是说，飞机机体以复合材料为主的时代从此起步。继波音 787之后，空客 A350改进型（A350XWB）的复合材料用量从原来的 37%提高至52%，波音737后继机和空客A320后继机的复合材料用量也将高达50%左右，甚至可能逼近60%。

在20世纪90年代推出的C-17军用运输机和刚推出的A380客机上，铝合金的用量还是排第1位，但在即将投入运营的波音787、A350客机和欧洲A400M军用运输机上，材料用量排第1位的均为复合材料。

大型飞机上钛合金用量与日俱增，波音787上15%钛用量则打破了客机历史最高记录。波音787上大量用钛的原因有两个：首先，为了减轻结构重量；其次，由于大型飞机复合材料用量猛增，铝合金与复合材料中的碳纤维之间存在显著的电位差，因此与复合材料接触的紧固件等零件通常采用钛合金，以避免电化学腐蚀的发生。

直至 2006年，波音 787仍出现超重问题，波音公司为了实现减重2500 kg的目标，决定在2006和2007年度再投入3亿美元研究在飞机一些部位用钛合金取代铝合金制成零部件，并声称不会影响波音787投入运营的进度。

1.2 一些具有新意的材料技术崭露头角

1）波音787采用复合材料整体机身段新型技术

复合材料与金属材料相比，更适合于制备整体结构件。波音 787机身由若干段复合材料大型整体结构件组成，减少了1500个零件和4～5万个连接件，显著地减轻结构重量，提高安全可靠性和降低制造、装配、油耗、维修等成本。然而，要制成这么大型和复杂的机身段整体件还是有很大难度的。比如在2006年初，该机身段就出现孔隙率过高的关键问题，甚至有可能影响适航认证，迫使公司投入更多人力财力进行试验研究。

2）A380率先在中央翼盒上大量采用复合材料

由于中央翼盒是关键的主承力件，因此以往均为全金属结构。A380中央翼盒率先采用复合材料与金属材料的混合结构（以复合材料为主），为在飞机上扩大复合材料应用跨出了重要的一步。该翼盒质量为8800 kg，其中复合材料5300 kg，取得了减重1500 kg的良好效果。

3）液态复合成形（LCM）已作为成熟的工程技术应用于新一代大型飞机

由于 LCM技术具有成本低、周期短、质量高、工作环境好和有利于结构整体化等优点，使原来在减重方面就占优势的树脂基复合材料如虎添翼，显著增强了与金属材料的竞争力。

树脂转移模塑（RTM）和树脂薄膜浸渗（RFI）是LCM中两种主要的制备技术。

比如A380中央翼盒的5个工字梁和襟翼导轨面板用RTM技术制成，并率先采用RFI技术制造复合材料襟翼导轨梁和后压力框。该后压力框是迄今为止最大的一个用RFI工艺制成的结构件。由于它形状均一、厚度较薄，很适于采用RFI技术。空客公司宣称这一技术已很成熟。波音 787机身的很多地板横梁用 RFI技术制造，其起落架撑杆则用RTM技术制造。

4）A380和波音 787分别选用层间混杂复合材料GLARE和TiGr

由于第1代层间混杂复合材料ARALL（芳纶纤维铝合金层板）存在芳纶纤维容易在疲劳过程发生断裂和成本较高的缺点，因而影响了它的扩大应用。与ARALL相比，第 2代层间混杂复合材料 GLARE（玻璃纤维铝合金层板）虽然密度较高和模量较低，但其成本显著降低，而且显著提高了疲劳性能、拉伸强度、压缩性能、冲击性能和阻尼性能，因此GLARE一问世，就引起了世界各大飞机制造公司的关注。A380的机身壁板、垂直尾翼前缘和水平稳定面都选用了 GLARE，其用量占A380总结构重量的3%。

由于第3代层间混杂复合材料CARE（碳纤维铝合金层板）很难彻底解决碳纤维与铝合金之间的电化学腐蚀问题，因而迄今无商品化产品。据报道，波音公司将选用第4代层间混杂复合材料TiGr（石墨纤维钛合金层板）制造波音787的机翼和机身的一些蒙皮。TiGr还可用来作为蜂窝夹层的面板。

5）A380是首次采用全钛挂架的飞机

A380率先采用全钛挂架，A350也采用全钛挂架，并均选用β退火的Ti-6Al-4VELI，以提高断裂韧性和减慢疲劳裂纹扩展速率而有利于损伤容限设计。这一全钛挂架是空客公司作为超前的新技术之一高调推出的。

6）新型高强高韧钛合金Ti-5Al-5V-5Mo-3Cr-1Zr首次在A380平台上闪亮登场

这是空客公司与俄罗斯合作在 ВТ22（Ti-5Al-5V-5Mo-1Cr-1Fe）基础上研发的一种新合金（属近β型），已选用于 A380机翼与挂架的连接装置，它那令人惊异的强度与韧性之间的优良组合受到了设计师和钛合金工作者的青睐。

7）钛合金精铸技术正逐步进入大型飞机领域

近20年来，由于在钛合金精铸工艺上采用了计算机模拟、热等静压和β热处理等先进技术，显著改善了钛铸件（包括大型整体结构件）的组织性能并消除了各种铸造缺陷，因而在F/A-22，V-22等军用飞机上的应用迅猛崛起。然而在客机和军用运输机上的应用却起步较晚。

1999年，波音777的发动机后安装框架钛合金精铸件在零件静力试验成功后已实际应用。虽然钛合金精铸技术早些时候已在 F/A-22，V-22等军用飞机上迅猛发展，但这是首次在安全可靠性要求更高的民机上获得成功应用，故这一开端具有重要意义。

近期，A380客机的钛合金刹车扭力管已由英国Doncasters公司采用离心熔模精铸技术制成，这是欧洲首次采用钛合金刹车扭力管精铸件取代以往的锻件。

最近，Howmet公司、波音公司与美国空军研究实验室联合进行薄壁钛铸件的开发，选择 C-17军用运输机发动机挂架为对象，各用一个整体铸件取代由 17个Ti-6A l-4V钣金件组成的鼻帽和由多个零件、不少紧固件组成的防火封严件。目前已达到厚度1.27 mm的要求，并引入新生产的C-17飞机。60个鼻帽铸件在全寿命期可节约320万美元，防火封严件改用薄壁铸件后可降低成本70%以上。

一种大型军用运输机用的钛合金精铸件，它取代了原22个加工件，节省了大部分成本。

8） 第3代铝锂合金在A350，A380上的大量应用是空客新一代飞机的一大特色

由于每添加1%锂就可降低3%的密度和提高6%的弹性模量，因此A380已正式选用铝锂合金制造地板梁，正打算用做机身蒙皮和下翼面的桁条。A350已选用铝锂合金制造机身蒙皮和地板结构等，其原设计的用量高达总结构重量的23%。铝锂合金经大起大落后东山再起的主要原因是在不断优化成分的基础上推出了2094，2195，2097，2197等第3代合金。这些合金的共同特点是降低了锂含量和优化了铜等合金元素的含量，从而控制了Al3Li相的析出，解决了第2代合金出现的各向异性显著、抗应力腐蚀能力差等问题。第3代铝锂合金取代2124，2024铝合金制成的零部件在F-16战斗机上的成功验证也是东山再起的重要原因。

9） 新型高强铝合金7085的问世为特大锻件在A380上的应用开辟了道路

已有高强铝合金的锻件或厚板的厚度均有一定限制，例如7055限于38 mm，7150虽较理想，其厚度也不允许大于 120 mm。为了获得厚度更大的高强铝合金锻件或厚板，美国Alcoa设计了一个具有专利权的7085铝合金，由于溶铸性和淬透性好，其锻件最大厚度已达240 mm。

7085铝合金的成分特点是锌镁比大和控制的Fe，Si含量适当。

7085铝合金制成的A380飞机后翼梁是迄今为止最大的一个飞机模锻件，长6.4 m，宽1.9 m，质量约3900 kg。

10）A380和A350采用激光焊接技术（LBW）制成6000系铝合金和铝锂合金整体结构件

A350采用激光焊接技术制造铝锂合金机身结构件，而A380则采用激光焊接技术制造6000系铝合金下机身壁板结构件，以取代以往的铆接结构件，从而由过去的“装配式结构”概念改变为“整体式结构”概念。这不仅减轻结构重量、降低成本和提高腐蚀抗力，而且从力学角度来看，可减少蒙皮损坏后裂纹的增长。这一激光焊接技术既适用于单曲度壁板，又适用于双曲度壁板。

2 关于中国大型飞机选材原则的建议

1）必须在更高的层次上综合评估选材方案的安全性、经济性、舒适性的环保性

与战斗机等较小型的飞机相比，大型飞机对选材的要求具有4个“更高”的特点，即更高安全性，更高经济性，更高舒适性和更高环保性。波音公司之所以把波音787的复合材料用量增加至50%左右，就是认为这在更高层次上符合了“四性”的要求。其具体理由是：复合材料经 30多年的研究和应用，技术上已经成熟，在安全可靠性上是不成问题的，何况复合材料的损伤容限和抗蚀性显著优于铝合金，更有利于耐久性和安全性的提高；飞机结构重量大幅度减轻带来的经济效益（包括燃油消耗和维修费用显著降低等），远远超过了它的负面效应（制造成本较高）；复合材料的应用使舷窗尺寸加大30%，客舱湿度和气压有所提高，让旅客享受更舒适的空中旅行；大量节省燃油也明显有利于环保性。中国大型客机在将来推出之时，应具有当时的国际市场竞争力，因此其选材也必须充分考虑“四性”，否则就不具备与届时国外同类客机的竞争能力。这个要求非常高，难度很大，但又必须努力去达到。这是因为：一代飞机，一代材料；一代材料，一代飞机。

2）必须尽早具备自主供应关键材料的能力

对于大型运输机，材料应立足于国内是显而易见的。对于大型客机用的材料，可按市场竞争原则进行全球采购，但这个“全球”理应包括国内供应商，特别对于关键材料，都应尽早具备自主供应的能力，即使有些关键材料赶不上首批客机的进度，也应大力安排研制任务并及早解决适航问题，以免出现受制于人的被动局面。

3）必须充分考虑大型客机与大型运输机“材料共用，成果共享”的原则

中国的大型飞机研制项目包含大型客机和大型运输机两大部分。为了缩短研制周期、节省研制费用、降低销售价格和提高成熟程度，建议设计和材料工作者紧密结合，尽可能增加大型客机和大型运输机上共用材料的比例。这样做更有利于客机用国产材料通过适航条例。

4）必须重视先进材料特别是具有中国特色的先进材料的选用

既然要求中国大型客机要具有届时的国际竞争力，就必须在符合安全性要求的前提下尽可能选用一些先进的航空材料，特别是要充分重视具有中国特色的先进材料的选用，例如TC21钛合金不仅具有国际先进水平的性能，而且在合金及其锻造工艺上都具有自主知识产权。

3 结束语

中国要有自己设计制造的大飞机是中国人民，特别是几代航空学者的梦想和愿望。在大型飞机上用更多自主研制生产的航空材料又是中国材料界，特别是航空材料研究者的梦想和愿望。今天，实现这个梦想和愿望的曙光已经拨云而出。只要所有参与大型飞机工程的中华儿女心怀祖国、情系航空、志在超越、脚踏实地、创新图强、团结和谐，那么中国自主设计制造的大型飞机就一定能在不久的将来展翅翱翔在万里晴空！

【作者单位：1. 北京航空材料研究院；2. 南昌航空大学材料科学与工程学院】

（摘自《航空学报》2008年3期）

·高被引论文摘要·

被引频次：321

大飞机用铝合金的研究现状及展望

刘兵，彭超群，王日初，等

简单介绍航空用铝合金的特点及其在大飞机上的应用和发展，重点叙述大飞机常用的2×××系和7×××系铝合金的成分、性能和应用，指出现阶段国内大飞机用铝合金材料存在的问题，预测大飞机用铝合金的发展方向。

大飞机；铝合金；2×××系铝合金；7×××系铝合金；铝锂合金；铝基复合材料

来源出版物：中国有色金属学报, 2010, 20(9): 1705-1715

被引频次：163

大型飞机自动化装配技术

许国康

摘要：简述了大型飞机及其结构特点，通过比较人与机器两种装配系统的特性，及分析装配自动化水平与装配成本等诸因素的关系曲线，指出了自动化装配技术在保证大型飞机结构长寿命、高效率、低成本研制和生产等方面的意义；对国外大型飞机的装配自动化发展状况进行了综述，简要分析了国外发展的几种主要自动化装配系统，总结了国外大型飞机的自动化装配水平；对西方国家在大型飞机自动化装配中采用的先进的装配理念和方法，如决定性装配方法等进行了概述。最后针对国内自动化装配水平低的现状和大型飞机研制和生产的需求，提出了发展模块化结构的自动化装配系统、贯彻并行工程理念、实现面向制造和面向装配的设计等发展建议。

关键词：自动化装配；大型飞机；长寿命；柔性装配；模块化；决定性装配

来源出版物：航空学报, 2008, 29(3): 227-233

被引频次：142

大型飞机部件数字化对接装配技术研究

邹冀华，刘志存，范玉青

摘要：为克服大型飞机部件对接装配的困难，提出了一种集成多项先进数字化技术的柔性装配技术体系。分析并阐述了该体系概念和结构组成，建立了用于部段对接装配的柔性装配工作站原型。归纳和阐述了四项主要支撑技术。其中，装配过程仿真技术是以数字样机为基础的，并说明了其在飞机部段对接中的应用特点和存在的难点。提出了数字化标准工装新概念，纠正了传统实体标工的缺点。对机械随动定位装置的样式、功能及其两类控制软件进行了说明。最后，说明了激光跟踪测量技术在对接装配中的作用、原理和测量方法。

关键词：飞机制造；数字化装配；柔性装配工作站；数字化标准工装；机械随动定位装置；激光跟踪测量

来源出版物：计算机集成制造系统, 2007, 13(7): 1367-1373

被引频次：125

一代材料技术，一代大型飞机

曹春晓

摘要：介绍了用于大型飞机的新材料的发展现状和趋势。当前，欧美大型飞机机体的材料结构正从以铝合金为主过渡至以复合材料为主，50%复合材料用量是未来飞机的起点。新一代大型飞机的材料技术特色首先是复合材料和钛合金用量创历史新高，以大幅度减轻飞机结构重量和降低燃油消耗；其次反映于一些具有新意的材料技术的成功推出，其中包括复合材料整体机身段、全钛发动机挂架、纤维金属层板、第3代铝锂合金、新型高强铝合金7085、新型高强高韧钛合金Ti-55531等。最后，对中国刚立项研制的大型飞机的选材原则提出了建议。

关键词：大型飞机；客机；运输机；材料；复合材料；钛合金；铝合金

来源出版物：航空学报, 2008, 29(3): 701-706

被引频次：119

复合材料技术与大型飞机

陈绍杰

摘要：给出了先进复合材料在大型飞机上应用的历史和现状，特别是在B787和A380等机种上的近期应用。指出了应用是从小到大、从少到多、从弱到强，一步一步走过来的。分析了应用的技术基础，说明了复合材料是一个性能优异的新材料，这是前提基础；其次应用是各种预研计划认真执行的结果；低成本复合材料技术是应用的重要前提，包括低成本的设计技术、制造技术和材料技术；30多年来复合材料技术的进步是坚实的保障。指出了中国于复合材料技术领域存在的问题和差距，提出了发展中国大型飞机复合材料技术的相关建议。

关键词：复合材料；技术；大型飞机；应用；建议

来源出版物：航空学报, 2008, 29(3): 605-610

被引频次：104

大型整体壁板成形技术

曾元松，黄遐

摘要：大型整体壁板是现代先进民用飞机的重要结构件，大型整体壁板成形技术是整机研制过程中所必须要解决的重大关键技术。从大型整体壁板的结构特点出发，介绍了整体壁板的结构形式和分类，重点阐述了整体带筋壁板喷丸成形技术和时效成形技术的国外研究应用进展及发展趋势，分析了国内现有整体壁板成形技术的基础和存在问题，特别介绍了国内在 ARJ21新支线飞机研制中所取得的最新进展。最后针对中国大飞机研制的紧迫需求，提出了尽快开展大飞机机翼和机身整体壁板成形技术研究的建议和对策。

关键词：整体壁板；喷丸成形；蠕变时效成形；大飞机；铝合金

来源出版物：航空学报, 2008, 29(3): 721-727

被引频次：97

自动铺放技术在大型飞机复合材料结构件制造中的应用

肖军，李勇，李建龙

摘要：自动铺放技术是工业发达国家近30年来发展和广泛应用的自动化制造技术，包括自动铺带技术和自动铺丝技术。这两项技术的共同优点是采用预浸料，并能实现自动化和数字化制造，高效高速。自动铺放技术特别适用于大型复合材料结构件制造，在各类飞行器，尤其是大型飞机的结构制造中所占比重越来越大。

来源出版物：航空制造技术, 2008, (1): 50-53

被引频次：97

碳纤维复合材料在大飞机上的应用

贺福，孙微

摘要：碳纤维复合材料具有质量轻、高比强度、高比模量、耐疲劳、耐腐蚀、耐高温和尺寸稳定性好等一系列优异性能，已广泛用于飞机制造业。尤其是近年来，在大型客机 A380和 B787上的用量已占到结构总量的50%左右，引起人们的极大关注。这一市场的需求必将促进碳纤维工业的大发展。

关键词：碳纤维；碳纤维复合材料；大飞机；应用

来源出版物：高科技纤维与应用, 2007, 32(6): 5-8

被引频次：61

大型飞机数字化装配技术研究

肖庆东，王仲奇，马强，等

摘要：针对大型飞机装配工作的高复杂性和高精度，综合国外航空制造业的先进装配技术，概括了数字化装配技术的内涵。对数字化装配技术作了深入研究，包括数字化装配工艺技术、数字化柔性装配工装技术、光学测量与补偿技术等。在数字化装配技术的应用方面，组建了针对大型飞机机身壁板零件的数字化装配系统平台，并且分析了该平台在飞机零部件装配应用中的特点。飞机数字化装配技术的研究应用，将大幅度降低工装成本，缩短装配周期，提高我国的飞机装配技术水平。

关键词：数字化装配；数字化装配工艺；数字化柔性装配工装；光学检测与补偿；数字化装配系统

来源出版物：中国制造业信息化, 2007, 36(3): 26-29

被引频次：56

大型飞机机身调姿与对接试验系统

邱宝贵，蒋君侠，毕运波，等

摘要：为实现飞机大部件装配过程的数字化、自动化和柔性化，研制了大型飞机机身调姿与对接试验系统。阐述了该系统的工作原理，通过激光跟踪仪测量试验机身上的检测点，集成管理系统计算试验机身的位姿，控制系统驱动多个三坐标数控定位器协同运动，实现试验机身的调姿与对接。建立了位姿调整机构的运动学模型，针对构建的硬件平台完成了包括集成管理系统、测量系统和控制系统在内的软件开发与集成，并对系统的性能进行了测试。试验结果表明，试验机身的位置调整精度优于0.09 mm，姿态调整精度优于0.0005。试验系统涉及的若干关键技术已成功应用于多项国家重点型号工程，大幅提高了飞机装配的质量和效率。

关键词：装配；三坐标数控定位器；激光跟踪仪；位姿调整；运动协调

来源出版物：航空学报, 2011, 32(5): 908-919

被引频次：259

Impinging jet studies for turbulence model assessment - I. Flow-field experiments

Cooper, D; Jackson, DC; Launder, BE

Abstract: The paper reports an extensive set of measurements of a turbulent jet impinging orthogonally onto a large plane surface. Two Reynolds numbers have been considered, 2.3 × 104and 7 × 104while the height of the jet discharge above the plate ranges from two to ten diameters, with particular attention focused on two and six diameters. The experiment has been designed so that it provides hydrodynamic data for conditions the same as those for which Baughn and Shimizu [ASME J. Heal Transfer 111, 1096 (1989)] have recently reported Nusselt number data (at Re = 23000). In both experiments, before discharge, the air passed along a smooth pipe sufficiently long to give fully developed flow at the exit plane of the jet—a feature that is helpful in using the data for turbulence-model evaluation. Hot-wire measurements have been made with pipes of nominally one-inch (26 mm) and four inches (101.6 mm) diameter. Data are reported of the mean velocity profile in the vicinity of the plate surface and also of the three Reynolds-stress components lying in the x-r plane. Computational results reported in a companion paper [Inl. J. Heal Mass Transfer 36, 2685–2697 (1993)] indicate a good degree of internal consistency between the mean and turbulent field data in that models predicting the mean flow poorly (or well) also predict the turbulence data poorly (well).

来源出版物：International Journal of Heat and Mass Transfer, 1993, 36(10): 2675-2684

被引频次：104

Measurement of large plane surface shapes by connecting small-aperture interferograms

Otsubo, M; Okada, K; Tsujiuchi, J

Abstract: We propose a method to obtain the shape of a large plane surface by connecting phase distributions measured by a small-aperture interferometer. These separately measured phase distributions cannot be connected directly because the object will tilt or have vertical displacement during the measurements. To correct these errors, the measurements are made so that the adjacent interferograms have common areas, and these interferograms are connected to minimize the difference of the phase distributions in the common areas. A matrix equation is derived to obtain coefficients to correct tilt and vertical displacement, and the accuracy of connection increases in proportion to an exponent of 1.5 of the width of the common area.

关键词：interferometry; precision measurements; leastsquares methods; large optical elements

来源出版物：Optical Engineering, 1994, 33(2): 608-613

被引频次：84

Noise sensitivity and reactions to noise and other environmental conditions

Miedema, HME; Vos, H

Abstract: This article integrates findings from the literature and new results regarding noise sensitivity. The new results are based on analyses of 28 combined datasets (N = 23038), and separate analyses of a large aircraft noise study (N = 10939). Three topics regarding noise sensitivity are discussed, namely, its relationship with noise exposure, its working mechanism, and the scope of its influence. (1) A previous review found that noise sensitivity has no relationship with noise exposure. The current analyses give consistent results, and show that there is at, most a very weak, positive relationship. (2) It was observed earlier that noise sensitivity alters the effect of noise exposure on noise annoyance, and does not (only) have an additive effect. The current analyses confirm this, and show that the relation of the annoyance score with the noise exposure is relatively flat for nonsensitives while it is steeper for sensitives. (3) Previous studies showed that noise sensitivity also influences reactions other than noise annoyance. The current analyses of the aircraft noise study extend these results, but also indicate that noise sensitivity has relatively little influence on reactions to nonenvironmental conditions.

来源出版物：The Journal of the Acoustical Society of America, 2003, 113(3): 1492-1504

被引频次：65

Towards application of fibre metal laminates in large aircraft

Vlot, A; Vogelesang, LB; de Vries, TJ

Abstract: Fibre metal laminates were developed at Delft University during the last two decades as a family of new hybrid materials consisting of bonded thin metal sheets and fibre/adhesive layers. This laminated structure provides the material with excellent fatigue, impact and damage tolerance characteristics and a low density. While the 20 per cent weight reduction was the prime driverbehind the development of this new family of materials, it turns out that additional benefits like cost reduction and an improved safety level have become more and more important. The combination of these aspects in one material makes fibre metal laminates a strong candidate material for fuselage skin structures of the new generation of high capacity aircraft. The focus on this application currently leads to industrialization and qualification that makes this material available to the aircraft designer.

关键词：flight safety; laminates; fatigue; aircraft; flame resistance

来源出版物：Aircraft Engineering and Aerospace Technology, 1999, 71(6): 558-570

被引频次：62

Flight dynamics of highly flexible flying wings

Patil, MJ; Hodges, DH

Abstract: The paper presents a theory for flight-dynamic analysis of highly flexible flying-wing configurations. The analysis takes into account large aircraft motion coupled with geometrically nonlinear structural deformation subject only to a restriction to small strain. A large motion aerodynamic loads model is integrated into the analysis. The analysis can be used for complete aircraft analysis including trim, stability analysis linearized about the trimmed-state, and nonlinear simulation. Results are generated for a typical high-aspect-ratio “flying-wing”configuration. The results indicate that the aircraft undergoes large deformation during trim. The flight-dynamic characteristics of the deformed aircraft are completely different as compared with a rigid aircraft. When the example aircraft is loaded sufficiently, the pair of complex-conjugate short-period roots merges to become two real roots, and the phugoid mode goes unstable. Furthermore, nonlinear flight simulation of the aircraft indicates that the phugoid instability leads to catastrophic consequences.

来源出版物：Journal of Aircraft, 2006, 43(6): 1790-1799

被引频次：56

Demand driven dispatch: A method for dynamic aircraft capacity assignment, models and algorithms

Berge, ME; Hopperstad, CA

Abstract: A major problem for the airline industry is the assignment of airplane capacity to flight schedules to meet fluctuating market needs. Demand Driven Dispatch (D3) is an operating concept that addresses this problem. Utilizing a demand forecast which improves as flight departure approaches, aircraft are dynamically assigned to flights to better match the predicted final demands. The result, demonstrated in studies of actual airline systems, is an increase in passenger loads and revenues with simultaneously reduced costs for a net of 1%–5% improvement in operating profits. Concept implementation is simplified by the prevalence of yield management systems which provide the forecasting capability, and the emergence of airplane families which provide the necessary operational flexibility. Implementation also requires frequent solution of extremely large aircraft assignment problems. These problems, which can be formulated in terms of a multicommodity network flow, can be solved with heuristic algorithms shown to exhibit an accuracy and efficiency essential to successful concept implementation.

来源出版物：Operations Research, 1993, 41(1): 153-168

被引频次：52

High-power density switched reluctance motor drive for aerospace applications

Radun, AV

Abstract: An advanced development, variable speed, 120 hp motor drive system for an electric motor-driven, large aircraft engine fuel pump application is described. The system is designed to demonstrate advanced technologies that will allow the design of motor drive systems with the necessary power densities, reliability, and environmental specifications for aerospace applications. The drive runs from 270 VDC, which is the emerging power standard for future aircraft power. The intended load of the drive is a centrifugal pump, although all system testing was done on a dynamometer test stand.

来源出版物：Transactions on Industry Applications, 1992, 28(1): 113-119

被引频次：47

Evaluation of ice water content retrievals from cloud radar reflectivity and temperature using a large airborne in situ microphysical database

Protat, A; Delanoe, J; Bouniol, D; et al.

Abstract: The objective of this paper is to assess the performances of the proposed ice water content (IWC)–radar reflectivity Z and IWC–Z–temperature T relationships for accurate retrievals of IWC from radar inspace or at ground-based sites, in the framework of the forthcoming CloudSat spaceborne radar, and of the European CloudNET and U.S. Atmospheric Radiation Measurement Program projects. For this purpose, a large airborne in situ microphysical database is used to perform a detailed error analysis of the IWC–Z and IWC–Z–T methods. This error analysis does not include the error resulting from the mass–dimension relationship assumed in these methods, although the expected magnitude of this error is bounded in the paper. First, this study reveals that the use of a single IWC–Z relationship to estimate IWC at global scale would be feasible up to −15 dBZ, but for larger reflectivities (and therefore larger IWCs) different sets of relationships would have to be used for midlatitude and tropical ice clouds. New IWC–Z and IWC–Z–T relationships are then developed from the large aircraft database and by splitting this database into midlatitude and tropical subsets, and an error analysis is performed. For the IWC–Z relationships, errors decrease roughly linearly from +210%/−70% for IWC = 10−4g m−3to +75%/−45% for IWC = 10−2g m−3, are nearly constant (+50%/−33%) for the intermediate IWCs (0.03–1 g m−3), and then linearly increase up to +210%/−70% for the largest IWCs. The error curves have the same shape for the IWC–Z–Trelationships, with a general reduction of errors with respect to the IWC–Z relationships. Comparisons with radar–lidar retrievals confirm these findings. The main improvement brought by the use of temperature as an additional constraint to the IWC retrieval is to reduce both the systematic overestimation and rms differences of the small IWCs (IWC < 0.01 g m−3). For the large IWCs, the use of temperature also results in a slight reduction of the rms differences but in a substantial reduction (by a factor of 2) of the systematic underestimation of the large IWCs, probably owing to a better account of the Mie effect when IWC–Zrelationships are stratified by temperature.

来源出版物：Journal of Applied Meteorology and Climatology, 2007, 46(5): 557-572

被引频次：45

Method for accelerating the destruction of aircraft wake vortices

Rennich, SC; Lele, SK

Abstract: The wake vortices shed by large aircraft and their associated hazard to following aircraft remain an important issue in commercial aviation. Extensive research into methods for alleviating this wake vortex hazard has been continuing for many years. This paper presents results from numerical simulations detailing a potentially useful mechanism for accelerating the destruction of the aircraft vortex wake and reducing the wake vortex hazard, The term destruction is used to refer to the progressive annihilation of the wake caused by mixing of vorticity of opposite sign and the associated elimination of large coherent structures, The emphasis here is on a description of the mechanism and its connection to previous work.

来源出版物：Journal of Aircraft, 1999, 36(2): 398-404

被引频次：33

Multi-agent system design and evaluation for collaborative wireless sensor network in large structure health monitoring

Wu, J; Yuan, SF; Ji, S; et al.

Abstract: Much attention has been focused on the research of structural health monitoring (SHM), since it could increase the safety and reduce the maintenance costs of engineering structures. In recent years, wireless sensor network (WSN) has been explored for adoption to improve the centralized cable-based SHM system performances. This paper presents a multi-agent design method and system evaluation for wireless sensor network based structural health monitoring to validate the efficiency of the multi-agent technology. Through the cooperation of six different agents for SHM applications, the distributed wireless sensor network can automatically allocate SHM tasks, self-organize the sensor network and aggregate different sensor information. In the evaluation work, the strain gauge and PZT sensors are used to monitor strain distribution change and joint failure of an experimental aluminum plate structure. A dedicated sensor network platform including the wireless strain node, wireless PZT node and wireless USB station is designed for the evaluation system. Based on the hardware platform, the multi-agents software architecture is defined. The multi-agent monitoring principle and implementation in the validation work for two typical kinds of structure states are presented. This paper shows the efficiency of the multi-agent technology for WSN based the SHM applications on the large aircraft structures.

来源出版物：Expert Systems with Applications, 2010, 37(3): 2028-2036

·推荐论文摘要·

大型飞机气动载荷向有限元节点等效分配的方法

张建刚，孙仁俊，唐长红

摘要：将气动载荷分配到有限元节点上是工程实际中的一项重要而繁琐的工作。对于二维的翼面气动载荷，根据原始的气动压力点的压力值，采用样条曲面拟合的方法，拟合得到翼面压力分布曲面，由该曲面得到有限元节点上的压力值，再在有限元模型单元上积分得到有限元节点载荷供强度设计使用。大型飞机具有复杂的增升装置，增升装置的气动载荷可能是三维的，对于三维的翼面载荷，直接在气动网格上积分得到气动载荷的小块集中力，然后按照沿某一方向投影的方法，找到该集中力作用的单元，最后按照二次规划的方法，将其分配到有限元节点上。

关键词：气动载荷；有限元节点；薄板样条

来源出版物：力学与实践, 2017, 39(1): 25-29

联系邮箱：张建刚，155246438@qq.com

大型飞机研制中的若干数字化智能装配技术

董一巍，李晓琳，赵奇

摘要：大型飞机的研制是国家提高自主创新能力的战略重点。为了提高大飞机装配质量与生产效率，采用数字化智能装配技术是必然的发展趋势。本文介绍了飞机智能化装配的系统框架与其技术体系架构，阐述了目前大型飞机装配所面临的难题，并指出虚拟现实仿真优化技术、专用智能装配工艺装备的开发，以及飞机总装智能装配生产线技术是智能装配技术的热点与发展方向，并分别进行了介绍，并阐述了国内外应用发展现状，最后指出了国内现有智能装配技术的不足与差距。

关键词：大飞机；智能装配；虚拟仿真；智能工装

来源出版物：航空制造技术, 2016, 497(1/2): 58-63

大飞机数字化制造关键技术

韩志仁

摘要：大型飞机数字化制造是一个非常复杂的系统工程，主要关键技术包括数字化并行协同技术、仿真技术、数字化测量技术、智能集成技术、柔性制造技术、飞机部件便捷传送技术、数字化信息处理技术、脉动线制造技术等，通过这些关键技术保证大飞机数字化制造的每个环节高效、顺利地进行，从而保证大飞机研制和生产周期短、质量高、成本低。对关键技术进行了综述分析，指出了关键技术中技术要点和关键问题，对更好地开展大飞机数字化制造具有参考作用。

关键词：大飞机；数字化制造；协同仿真；数字化测量；柔性制造

来源出版物：航空制造技术, 2016, 497(1/2): 53-57

一种提高风洞动态试验数据质量的模型姿态控制和测量技术

刘志涛，孙海生

摘要：低速风洞动态试验装置通常采用“电机+减速器+偏心机构+线性传动机构”的方式，存在传递环节多、机械间隙大等问题，给模型运动的精确控制和模型姿态的精确测量带来较大困难。为满足大型客机等大飞机对低速风洞动态试验的要求，基于现有的静态试验通用支撑平台，采用“电子凸轮”技术，建立了一套迎角/侧滑角解耦、可进行飞机小振幅动导数和大振幅非定常气动特性研究的动态试验装置。利用该动态试验装置进行了某飞机大尺度动态试验模型动导数试验和大振幅振荡试验，获得了试验数据的重复性，并研究了动态试验数据和静态试验数据之间的相关性。试验结果表明：利用该装置获得的某飞机动态试验数据重复性较好、规律合理，能满足大型飞机动态试验要求。

关键词：大型飞机；动导数；非定常气动力；风洞试验；支撑装置

来源出版物：航空学报, 2016, 37(8): 101-110

联系邮箱：刘志涛，liuzhitao@cardc.cn

8米×6米风洞TPS反推力试验技术

黄勇，胡卜元，张卫国，等

摘要：TPS（涡扇动力模拟器）试验技术是风洞中模拟发动机反推力状态最有效的手段。开展反推力试验的目的是获得反推力发动机对飞机气动特性的影响，确定反推力发动机的再吸入速度边界。为满足我国大飞机研制的试验技术需求，中国空气动力研究与发展中心在8 m × 6 m风洞发展了全模TPS反推力试验技术。自主研制了TPS反推力试验专用的高精度六分量杆式应变天平、大流量空气桥和流量控制单元、TPS监视报警系统、数据采集系统、综合显示系统等 TPS反推力试验系统，制定了试验模拟准则、试验流程和试验方法，建立了完善的全模TPS反推力试验技术。利用TPS反推力试验技术，开展了国内首期全模 TPS反推力风洞试验，研究了某型飞机反推力发动机的再吸入特性，获得了反推力发动机的再吸入速度边界。

关键词：大飞机；反推力；涡扇动力模拟器；试验技术；低速风洞

来源出版物：空气动力学学报, 2016, 34(3): 67-74

联系邮箱：黄勇，dragonhyong@163.com

复合材料在新一代大型民用飞机中的应用

马立敏，张嘉振，岳广全，等

摘要：新一代大型民用飞机机体结构的突出特点是广泛采用复合材料。总结了复合材料在大型民用飞机中的发展，其用量已经从1980年整机质量的4%上升到目前的50%，并广泛应用于主承力结构和复杂曲面结构。以波音787和空客A350飞机为例，分析了波音和空客公司复合材料的应用情况，发现复合材料不仅减轻了飞机的结构质量，提高了飞机结构的使用寿命，降低了飞机的维护费用，而且可以增加舱内压力和空气湿度，提高民用飞机的经济性、舒适性、环保性。复合材料取代金属和非金属等常规材料制造结构件已经成为世界民机制造业的主流趋势，这对中国自主研制的大型民用飞机的市场竞争力提出了严峻的考验，为此提出了中国在研制大型民用飞机时应用复合材料应注意的一些问题。

关键词：复合材料；民用航空；大型飞机；飞机结构；波音；空中客车

来源出版物：复合材料学报, 2015, 32(2): 317-322

联系邮箱：马立敏，malimin@comac.cc

中国复合材料自动铺放技术研究进展

文立伟，肖军，王显峰，等

摘要：首先扼要介绍了复合材料自动铺放（自动铺带和自动铺丝）成形技术的原理、特点和该技术在国外航空航天领域的应用概况。然后系统介绍了近年来中国国内复合材料自动铺带的装备技术、软件技术和材料工艺技术的研发历程，总结了其关键技术的突破和应用进展，并指出开发低成本高效铺带技术是未来的重要方向。同时介绍了国内自动铺丝技术基础研究（装备、软件和工艺方法）的进展，并且着重介绍了南京航空航天大学自动铺丝应用技术（工业样机与材料工艺技术）的研发和应用情况。最后通过分析，归纳了自动铺丝技术应用研究的瓶颈问题，并提出了研究建议。

关键词：先进复合材料；大型飞机；自动铺带；自动铺丝

来源出版物：南京航空航天大学学报, 2015, 47(5): 637-649

联系邮箱：肖军，xiao@nuaa.edu.cn

高升力系统控制计算机容错技术研究

徐奡，夏德天，郑久寿

摘要：在大型飞机的起飞、降落、巡航飞行中，高升力系统起着重要的作用。电传控制技术在高升力系统中的应用减轻了系统重量，为系统带来更佳的性能，高级自动控制和更好的鲁棒性。以现代大型飞机先进高升力电传控制系统为研究对象，对高升力电传控制计算机设计技术开展研究，重点探讨了系统冗余架构、硬件设计、余度管理及节点一致性机制等关键设计技术。

关键词：大型飞机；高升力；安全性；冗余；容错

来源出版物：微电子学与计算机, 2015, (6): 36-40, 45

联系邮箱：徐奡，xuao@21cn.com

MBD技术在大飞机研制中的应用

李婷婷，刘俊堂，张永辉

摘要：大飞机研制MBD技术应用实践表明，MBD技术不仅仅是信息表达方式的改变，更是由于这种改变引起的飞机研制模式的改变。同时，由于三维设计更符合人类的原始创新方式及更进一步的设计信息数学描述等，采用MBD技术还可以研制出更多的设计效能工具，如从基本的设计模板、左右件自动生成到保证上下游设计信息唯一且一致的关联设计等。

来源出版物：航空制造技术, 2014, 461(17): 88-92

Control system designing for correcting wingfuselage assembly deformation of a large aircraft

Fang, Q; Chen, WD; Zhao, AA; et al.

Abstract: Purpose: In aircraft wing–fuselage assembly, the distributed multi-point support layout of positioners causes fuselage to deform under gravity load, leading to assembly difficulty and assembly stress. This paper aimsto propose a hybrid force position control method to balance aerodynamic shape accuracy and deformation of assembly area, thereby correcting assembly deformation and reducing assembly stress. Design/methodology/ approach: Force and position control axes of positioners are selected based on screw theory and ellipsoid method. The position-control axes follow the posture trajectory to align the fuselage posture. To exert force on the fuselage and correct the deformations, the force-control axes follow the contact force derived by using orthogonal experiments and partial least squares regression (PLSR). Finite element simulation and one-dimension deformation correction experiment are conducted to verify the validity of this method. Findings: Simulation results indicate that hybrid force position control method can correct assembly deformation and improve the wing–fuselage assembly quality significantly. Experiment on specimen verifies the effect of this method indirectly. Originality/value: The proposed method gives a solution to solve the deformation problem during aircraft wing-fuselage assembly, thereby reducing assembly stress and improving assembly quality.

来源出版物：Assembly Automation, 2017, 37(1): 22-33

Optimal placement of measurement points on large aircraft fuselage panels in digital assembly

Bi, YB; Yan, WM; Ke,YL

Abstract: A large aircraft fuselage panel is commonly composed of a variety of thin-walled components. Most of these components are large, thin and compliant, and they are also prone to some flexible deformation during assembly and remain deformed after assembly. Besides, many different fabrication and assembly manners are adopted in order to guarantee the complicated assembly relationships between each component. The above characteristics often cause large aircraft fuselage panels to exhibit low stiffness and weak strength, thereby inducing deformation during assembly. Since the posture of a large aircraft fuselage panel is commonly evaluated by matching the theoretical and actual positions of the measurement points placed on it, and its assembly deformation is also represented by the position errors of the measurement points, a reasonable measurement point placement is significant for the large aircraft fuselage panel in digital assembly. This article presents a method based on the D-optimality method and the adaptive simulated annealing genetic algorithm to optimize the placement of the measurement points which can cover more deformation information of the panel for effective assembly error diagnosis. By taking the principle of the D-optimality method, an optimal set of measurement points is selected from a larger candidate set through adaptive simulated annealing genetic algorithm. As illustrated by an example, the final measurement point configuration is more effective to maximize the determinant of the corresponding Fisher Information Matrix and minimize the estimation error of the assembly deformation than those obtained by other methods.

关键词：large aircraft fuselage panel; deformation; measurement point; D-optimality; adaptive simulated annealing genetic algorithm; Fisher Information Matrix

来源出版物：Proceedings of the Institution of Mechanical Engineers, Part B: Journal of Engineering Manufacture, 2017, 231 (1): 73-84

联系邮箱：Yan, WM; yanweimiao@zju.edu.cn

Design and test of dual actuator nose wheel steering system for large civil aircraft

Zhang, M; Jiang, RM; Nie, H

Abstract: In order to improve aircraft ground handling characteristics and airport working efficiency, large handling angle and torque are requested for the nose wheel steering system of large civil aircraft. A following swivel selector valve is firstly designed to meet the demand for the hydraulic pressure commutating as soon as the dual actuator nose wheel steering mechanism passes through its dead center position. Considering the multiple objective functions of nose wheel steering mechanisms, those core design parameters are multiobjective optimized. A nose wheel steering electrohydraulic servo system with handling and antishimmy functions is designed for the steering mechanism. Then the prototypes of the steering mechanism and electrohydraulic servo system are researched to validate the design. Using the swing actuator to provide the load torque and ground excitation, the steering test bench is prepared to test the system working. The steering test and the antishimmy test are conducted to verify the functions of the system. The test results, such as steer angle, steer torque hydraulic pressure, and antishimmy torque, are analyzed in detail and compared with the theoretical results. The results show that the property of the prototype achieves the design objectives, such as work mode, steer angle, and steer torque.

来 源 出版物： International Journal of Aerospace Engineering, 2016, 1626015

联系邮箱：Zhang, M; zhm6196@nuaa.edu.cn

Variation modeling for fuselage structures in large aircraft digital assembly

Cheng, L; Wang, Q; Li, JX; et al.

Abstract: Purpose: The aim of this paper is to present a new variation modeling method for fuselage structures in digital large aircraft assembly. The variation accumulated in a large aircraft assembly process will influence the dimensional accuracy and fatigue life of airframes. However, in digital large aircraft assembly, variation analysis and modeling are still unresolved issues. Design/methodology/approach: An elastic structure model based on beam elements is developed, which is an equivalent idealization of the actual complex structure. The stiffness matrix of the structure model is obtained by summing the stiffness matrices of the beam elements. For each typical stage of the aircraft digital assembly process, including positioning, coordinating, joining and releasing, variation models are built using the simplified structure model with respective loads and boundary conditions. Findings: Using position errors and manufacturing errors as inputs, the variations for every stage of the assembly process can be calculated using the proposed model. Practical implications—This method has been used in a large fuselage section assembly project, and the calculated results were shown to be a good prediction of variation in the actual assembly. Originality/value: Although certain assumptions have been imposed, the proposed method provides a better understanding of the assembly process and creates an analytical foundation for further work on variation control and tolerance optimization.

来源出版物：Assembly Automation, 2015, 35(2): 172-182

联系邮箱：Wang, Q; wqing@zju.edu.cn

Accurate and efficient analysis of large antenna arrays with radome on a large aircraft

Zhao, HH; Jian, LR; Liu, Y

Abstract: An accurate and efficient computational approach is presented for analyzing radiation characteristics of large antenna arrays with radome. This approach is based on the hybrid finite element-boundary integral-multilevel fast multipole algorithm (FE-BIMLFMA). Unlike the conventional single-domain FE-BIMLFMA, the whole domain of the antenna array with radome is separated into many disconnected domains. A large free space area unavoidable in the single-domain FE-BI-MLFMA is eliminated in this multi-domain FE-BIMLFMA formulation, thus the number of unknowns is greatly reduced in the presented multi-domain FE-BIMLFMA approach. Different from the single-domain FEBI-MLFMA, many integral equations are required in this multi-domain FE-BI-MLFMA. The numerical experiment shows that the presented multi-domain FE-BI-MLFMA is more efficient than the single-domain one while maintaining the same accuracy. A whole complicated system of a slottedwaveguide array with radome mounted on an aircraft is analyzed to further demonstrate the generality and capability of the presented multi-domain FE-BI-MLFMA.

来源出版物：Progress in Electromagnetics Research, 2015, 153: 103-111

联系邮箱：Liu, Y; clly1985528@163.com

Electrical load-sizing methodology to aid conceptual and preliminary design of large commercial aircraft

Seresinhe, R; Lawson, C

Abstract: The importance of the more electric aircraft has been highlighted in many publications, projects and industrial presentations. By definition, the more electric aircraft concept achieves the majority of the required system functionality by using electrically powered sub-systems and components. This manifests itself in much higher electrical power demands on-board aircraft, compared to conventional architectures. This presents many challenges in the design process. To alleviate the risk and choose the optimum architectures for the systems on the aircraft, it is essential to incorporate the characteristics and possible configurations of the electrical network in the conceptual and preliminary design stages. Hence the current practice of performing an electrical load analysis at the detailed design stage is not adequate. To address this gap, this paper presents a viable and robust methodology to define requirements, size components and systems and calculates the electric power requirements at the preliminary design stages. The methodology uses the conventional aircraft, systems and components as the baseline and uses mathematical techniques and logical sequences of component operation, developed through the research, to size electrical load profiles for conventional aircraft. It then adapts this result to the more electric aircraft concept by adding key components that would account for the difference between a conventional system and a more electric system. The methodology presented here makes the design process more robust and aids the choice of the optimum design for the aircraft.

关键词：aircraft design; aircraft systems; electrical load analysis; more electric aircraft

来源出版物：Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2015, 229(3): 445-466

联系邮箱：Seresinhe, R; r.w.seresinhe@cranfield.ac.uk

Comparing different fidelity models for the impact analysis of large commercial aircrafts on acontainment building

Lu, XZ; Lin, KQ; Cen, S; et al.

Abstract: Three Boeing 767 finite element models with different fidelities are built using CATIA, Hypermesh and LS-DYNA in this study. The impacts of these models on a rigid wall and a containment building are simulated with LS-DYNA. The simulation results show that the time histories of the impact forces and impulses differ significantly among these models for the low-speed impact case. With the increase of the impact velocity, the time histories of impact forces and the damage of the containment building become similar. Moreover, the impact on the back side of the containment building will occur only when the high fidelity model impacts the containment building with a high velocity. The over-simplified aircraft models will underestimate the impact load and induce a different failure mode compared to the high fidelity model. The internal structures of an aircraft should be accounted for in the impact simulation. This investigation provides a reference for further studies of aircraft impacts on containment buildings.

关键词：impact; large commercial aircraft; containment building; different fidelity models; finite element simulation

来源出版物：Engineering Failure Analysis, 2015, 57: 254-269

Adaptive decoupling synchronous control of dissimilar redundant actuation system for large civil aircraft

Shi C; Wang XJ; Wang SP; et al.

Abstract: In order to meet the increasing reliability requirements of actuation system for large civil aircraft, the novel distributed dissimilar redundant actuation system composed of one hydraulic actuator (HA) and one electro-hydrostatic actuator (EHA) has been applied to the design of advanced aircraft. This configuration can greatly improve the system reliability and effectively avoid potential common-mode/common-cause (CM/CC) failure. However, this actuation configuration can exhibit force fighting problem between HA and EHA due to their different driving mechanisms and rigid coupling when they operate in the active/active mode, which may even cause damage to the control surface. To resolve this problem, an adaptive decoupling synchronous controller (ADSC) is proposed in this study. The coupling effect between HA and EHA is taken into account, and an adaptive decoupling controller is designed to eliminate the coupling term. Parameter adaption law is designed for the parametric uncertainties. In addition, a feed-forward compensator is proposed to compensate for the difference between HA and EHA by accelerating the dynamic response of EHA. Finally, the comparative simulation results indicate that the proposed ADSC controller has high speed/high robustness performances and can effectively reduce the force fighting between HA and EHA.

关键词：actuation system; dissimilar redundant; force fighting; adaptive decoupling control; synchronous control

来源出版物：Aerospace Science and Technology, 2015, 47: 114-124

联系邮箱：Wang, XJ, wangxj@buaa.edu.cn

Efficient optimisation of large aircraft fuselage structures

Vankan, WJ; Maas, R; Grihon, S; et al.

Abstract: This paper presents an innovative optimisation method for aircraft fuselage structural design. Detailed local finite element analyses of panel buckling are further processed such that they can be applied as failure constraints in the global level optimisation. The high computational costs involved with the finite element analyses are limited by advanced use of surrogate modelling methods. This yields high flexibility and efficiency in the local level optimisation procedure and allows for efficient gradient based search methods as well as more costly direct search optimisations like genetic algorithms (GAs). The method is demonstrated on a composite fuselage barrel design case considering common structural sizing variables like thicknesses and stringer dimensions. Optimised barrel designs are obtained where the constraints that are derived from the panel buckling analyses are active. The total computational cost for the complete local and global level optimisation procedures is in the order of days on common-performance hardware.

来源出版物：The Aeronautical Journal, 2014, 118(1199): 31-52

编辑：王微

典

文章题目第一作者来源出版物1 D e c a y o f w a k e v o r t i c e s o f l a r g e a i r c r a f t S a r p k a y a , T A I A A J o u r n a l , 1 9 9 8 , 3 6 ( 9 ) : 1 6 7 1 -1 6 7 9 2 T r a i l i n g v o r t e x e f f e c t s o n l a r g e r e c e i v e r a i r c r a f t B l o y , A W J o u r n a l o f A i r c r a f t , 1 9 9 5 , 3 2 ( 6 ) : 1 1 9 8 -1 2 0 4 3 N e w g r o u n d v i b r a t i o n t e s t i n g t e c h n i q u e s f o r l a r g e a i r c r a f t c o m p u t a t i o n G l o t h , G S V S o u n d a n d V i b r a t i o n , 2 0 0 1 , 3 5 ( 1 1 ) : 1 4 -1 8 T h e u s e o f e v a c u a t i o n m o d e l l i n g t e c h n i q u e s i n t h e 4 d e s i g n o f v e r y l a r g e t r a n s p o r t a i r c r a f t a n d b l e n d e d G a l e a , E R T h e A e r o n a u t i c a l J o u r n a l ( 1 9 6 8 ) , 2 0 0 3 , w i n g b o d y a i r c r a f t 1 0 7 ( 1 0 7 0 ) : 2 0 7 -2 1 8 5 T h e l a t e r a l d y n a m i c s t a b i l i t y a n d c o n t r o l o f a l a r g e r e c e i v e r a i r c r a f t d u r i n g a i r -t o -a i r r e f u e l l i n g B l o y , A W T h e A e r o n a u t i c a l J o u r n a l ( 1 9 6 8 ) , 1 9 8 6 , 9 0 ( 8 9 6 ) : 2 3 7 -2 4 3

Decay of wake vortices of large aircraft

Sarpkaya, T