大飛機(jī)

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.

一代材料技術(shù)，一代大型飛機(jī)

曹春曉

大飛機(jī)用鋁合金的研究現(xiàn)狀及展望

劉兵，彭超群，王日初，等

大飛機(jī)

·編者按·

“大飛機(jī)”或“大型飛機(jī)”一般是指起飛總質(zhì)量超過100 t的運(yùn)輸類飛機(jī)，包括軍用、民用大型運(yùn)輸機(jī)，也包括一次航程達(dá)到3000 km的軍用或乘坐達(dá)到100座以上的民用客機(jī)。中國把150座以上的干線客機(jī)稱作大客機(jī)。大飛機(jī)技術(shù)復(fù)雜，制造周期長，質(zhì)量要求高，被稱為“現(xiàn)代制造業(yè)的一顆明珠”，具有氣動外形要求嚴(yán)格、設(shè)計更改頻繁、產(chǎn)品構(gòu)型眾多、零件材料和形狀各異、內(nèi)部結(jié)構(gòu)復(fù)雜、空間緊湊、各類系統(tǒng)布置密集以及零組件數(shù)量巨大等特點。

大飛機(jī)是一個國家軍事戰(zhàn)略的重要技術(shù)支柱，也是國家經(jīng)濟(jì)的重要領(lǐng)域。大飛機(jī)的設(shè)計制造集成國內(nèi)前沿高新技術(shù)，是國家基礎(chǔ)工業(yè)水平的體現(xiàn)，同時可以提升國家整體技術(shù)水平。2017年5月5日，我國國產(chǎn)大飛機(jī)C919在經(jīng)歷了100多個測試項目以后，首飛成功。首飛成功后，C919將轉(zhuǎn)入適航取證階段，這將意味著其距離面向市場更進(jìn)一步。有關(guān)專家指出，適航取證將是一個長期的任務(wù)。

·熱點數(shù)據(jù)排行·

截至2017年5月12日，中國知網(wǎng)（CNKI）和Web of Science（WOS）的數(shù)據(jù)報告顯示，以“大飛機(jī)”為詞條可以檢索到的期刊文獻(xiàn)分別為1143、476條，本專題將相關(guān)數(shù)據(jù)按照：研究機(jī)構(gòu)發(fā)文數(shù)、作者發(fā)文數(shù)、期刊發(fā)文數(shù)、被引用頻次進(jìn)行排行，結(jié)果如下。

研究機(jī)構(gòu)發(fā)文數(shù)量排名（CNKI）

研究機(jī)構(gòu)發(fā)文數(shù)量排名（WOS）

作者發(fā)文數(shù)量排名（CNKI）

作者發(fā)文數(shù)量排名（WOS）

期刊發(fā)文數(shù)量排名（CNKI）

期刊發(fā)文數(shù)量排名（WOS）

根據(jù)中國知網(wǎng)（CNKI）數(shù)據(jù)報告，以“大飛機(jī)”等為詞條可以檢索到的高被引論文排行結(jié)果如下。

國內(nèi)數(shù)據(jù)庫高被引論文排行

根據(jù)Web of Science統(tǒng)計數(shù)據(jù)，以“大飛機(jī)”為詞條可以檢索到的高被引論文排行結(jié)果如下。

國外數(shù)據(jù)庫高被引論文排行

·經(jīng)典文獻(xiàn)推薦·

基于Web of Science檢索結(jié)果，利用Histcite軟件選取LCS（Local Citation Score，本地引用次數(shù)）TOP 30文獻(xiàn)作為節(jié)點進(jìn)行分析，得到本領(lǐng)域推薦的經(jīng)典文獻(xiàn)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.

來源出版物：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.

來源出版物：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.

來源出版物：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.

來源出版物：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.

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

·推薦綜述·

一代材料技術(shù)，一代大型飛機(jī)

曹春曉

2007年2月26日，溫家寶總理主持召開國務(wù)院常務(wù)會議，原則批準(zhǔn)大型飛機(jī)研制重大科技專項正式立項，引起了國內(nèi)外的高度關(guān)注。

一百多年來，材料與飛機(jī)一直在相互推動下不斷發(fā)展。“一代材料，一代飛機(jī)”正是世界航空發(fā)展史的一個真實寫照。飛機(jī)機(jī)體材料結(jié)構(gòu)在大體上經(jīng)歷了4個階段的發(fā)展后，正跨入第5階段。

顯然，大型飛機(jī)在機(jī)體材料上的變化正反映了這一趨勢，并在選材等方面充分體現(xiàn)了“一代材料技術(shù)，一代大型飛機(jī)”這一辯證的互動關(guān)系。

作為借鑒，本文首先歸納分析了歐美新一代大型飛機(jī)的材料技術(shù)特色，然后在此基礎(chǔ)上結(jié)合中國具體情況提出一些關(guān)于中國大型飛機(jī)選材原則的建議。

1 歐美新一代大型飛機(jī)的材料技術(shù)特色

1.1 復(fù)合材料和鈦合金的用量創(chuàng)歷史新高

從波音787開始，50%用量的復(fù)合材料成為未來飛機(jī)的起點，也就是說，飛機(jī)機(jī)體以復(fù)合材料為主的時代從此起步。繼波音 787之后，空客 A350改進(jìn)型（A350XWB）的復(fù)合材料用量從原來的 37%提高至52%，波音737后繼機(jī)和空客A320后繼機(jī)的復(fù)合材料用量也將高達(dá)50%左右，甚至可能逼近60%。

在20世紀(jì)90年代推出的C-17軍用運(yùn)輸機(jī)和剛推出的A380客機(jī)上，鋁合金的用量還是排第1位，但在即將投入運(yùn)營的波音787、A350客機(jī)和歐洲A400M軍用運(yùn)輸機(jī)上，材料用量排第1位的均為復(fù)合材料。

大型飛機(jī)上鈦合金用量與日俱增，波音787上15%鈦用量則打破了客機(jī)歷史最高記錄。波音787上大量用鈦的原因有兩個：首先，為了減輕結(jié)構(gòu)重量；其次，由于大型飛機(jī)復(fù)合材料用量猛增，鋁合金與復(fù)合材料中的碳纖維之間存在顯著的電位差，因此與復(fù)合材料接觸的緊固件等零件通常采用鈦合金，以避免電化學(xué)腐蝕的發(fā)生。

直至 2006年，波音 787仍出現(xiàn)超重問題，波音公司為了實現(xiàn)減重2500 kg的目標(biāo)，決定在2006和2007年度再投入3億美元研究在飛機(jī)一些部位用鈦合金取代鋁合金制成零部件，并聲稱不會影響波音787投入運(yùn)營的進(jìn)度。

1.2 一些具有新意的材料技術(shù)嶄露頭角

1）波音787采用復(fù)合材料整體機(jī)身段新型技術(shù)

復(fù)合材料與金屬材料相比，更適合于制備整體結(jié)構(gòu)件。波音 787機(jī)身由若干段復(fù)合材料大型整體結(jié)構(gòu)件組成，減少了1500個零件和4～5萬個連接件，顯著地減輕結(jié)構(gòu)重量，提高安全可靠性和降低制造、裝配、油耗、維修等成本。然而，要制成這么大型和復(fù)雜的機(jī)身段整體件還是有很大難度的。比如在2006年初，該機(jī)身段就出現(xiàn)孔隙率過高的關(guān)鍵問題，甚至有可能影響適航認(rèn)證，迫使公司投入更多人力財力進(jìn)行試驗研究。

2）A380率先在中央翼盒上大量采用復(fù)合材料

由于中央翼盒是關(guān)鍵的主承力件，因此以往均為全金屬結(jié)構(gòu)。A380中央翼盒率先采用復(fù)合材料與金屬材料的混合結(jié)構(gòu)（以復(fù)合材料為主），為在飛機(jī)上擴(kuò)大復(fù)合材料應(yīng)用跨出了重要的一步。該翼盒質(zhì)量為8800 kg，其中復(fù)合材料5300 kg，取得了減重1500 kg的良好效果。

3）液態(tài)復(fù)合成形（LCM）已作為成熟的工程技術(shù)應(yīng)用于新一代大型飛機(jī)

由于 LCM技術(shù)具有成本低、周期短、質(zhì)量高、工作環(huán)境好和有利于結(jié)構(gòu)整體化等優(yōu)點，使原來在減重方面就占優(yōu)勢的樹脂基復(fù)合材料如虎添翼，顯著增強(qiáng)了與金屬材料的競爭力。

樹脂轉(zhuǎn)移模塑（RTM）和樹脂薄膜浸滲（RFI）是LCM中兩種主要的制備技術(shù)。

比如A380中央翼盒的5個工字梁和襟翼導(dǎo)軌面板用RTM技術(shù)制成，并率先采用RFI技術(shù)制造復(fù)合材料襟翼導(dǎo)軌梁和后壓力框。該后壓力框是迄今為止最大的一個用RFI工藝制成的結(jié)構(gòu)件。由于它形狀均一、厚度較薄，很適于采用RFI技術(shù)。空客公司宣稱這一技術(shù)已很成熟。波音 787機(jī)身的很多地板橫梁用 RFI技術(shù)制造，其起落架撐桿則用RTM技術(shù)制造。

4）A380和波音 787分別選用層間混雜復(fù)合材料GLARE和TiGr

由于第1代層間混雜復(fù)合材料ARALL（芳綸纖維鋁合金層板）存在芳綸纖維容易在疲勞過程發(fā)生斷裂和成本較高的缺點，因而影響了它的擴(kuò)大應(yīng)用。與ARALL相比，第 2代層間混雜復(fù)合材料 GLARE（玻璃纖維鋁合金層板）雖然密度較高和模量較低，但其成本顯著降低，而且顯著提高了疲勞性能、拉伸強(qiáng)度、壓縮性能、沖擊性能和阻尼性能，因此GLARE一問世，就引起了世界各大飛機(jī)制造公司的關(guān)注。A380的機(jī)身壁板、垂直尾翼前緣和水平穩(wěn)定面都選用了 GLARE，其用量占A380總結(jié)構(gòu)重量的3%。

由于第3代層間混雜復(fù)合材料CARE（碳纖維鋁合金層板）很難徹底解決碳纖維與鋁合金之間的電化學(xué)腐蝕問題，因而迄今無商品化產(chǎn)品。據(jù)報道，波音公司將選用第4代層間混雜復(fù)合材料TiGr（石墨纖維鈦合金層板）制造波音787的機(jī)翼和機(jī)身的一些蒙皮。TiGr還可用來作為蜂窩夾層的面板。

5）A380是首次采用全鈦掛架的飛機(jī)

A380率先采用全鈦掛架，A350也采用全鈦掛架，并均選用β退火的Ti-6Al-4VELI，以提高斷裂韌性和減慢疲勞裂紋擴(kuò)展速率而有利于損傷容限設(shè)計。這一全鈦掛架是空客公司作為超前的新技術(shù)之一高調(diào)推出的。

6）新型高強(qiáng)高韌鈦合金Ti-5Al-5V-5Mo-3Cr-1Zr首次在A380平臺上閃亮登場

這是空客公司與俄羅斯合作在 ВТ22（Ti-5Al-5V-5Mo-1Cr-1Fe）基礎(chǔ)上研發(fā)的一種新合金（屬近β型），已選用于 A380機(jī)翼與掛架的連接裝置，它那令人驚異的強(qiáng)度與韌性之間的優(yōu)良組合受到了設(shè)計師和鈦合金工作者的青睞。

7）鈦合金精鑄技術(shù)正逐步進(jìn)入大型飛機(jī)領(lǐng)域

近20年來，由于在鈦合金精鑄工藝上采用了計算機(jī)模擬、熱等靜壓和β熱處理等先進(jìn)技術(shù)，顯著改善了鈦鑄件（包括大型整體結(jié)構(gòu)件）的組織性能并消除了各種鑄造缺陷，因而在F/A-22，V-22等軍用飛機(jī)上的應(yīng)用迅猛崛起。然而在客機(jī)和軍用運(yùn)輸機(jī)上的應(yīng)用卻起步較晚。

1999年，波音777的發(fā)動機(jī)后安裝框架鈦合金精鑄件在零件靜力試驗成功后已實際應(yīng)用。雖然鈦合金精鑄技術(shù)早些時候已在 F/A-22，V-22等軍用飛機(jī)上迅猛發(fā)展，但這是首次在安全可靠性要求更高的民機(jī)上獲得成功應(yīng)用，故這一開端具有重要意義。

近期，A380客機(jī)的鈦合金剎車扭力管已由英國Doncasters公司采用離心熔模精鑄技術(shù)制成，這是歐洲首次采用鈦合金剎車扭力管精鑄件取代以往的鍛件。

最近，Howmet公司、波音公司與美國空軍研究實驗室聯(lián)合進(jìn)行薄壁鈦鑄件的開發(fā)，選擇 C-17軍用運(yùn)輸機(jī)發(fā)動機(jī)掛架為對象，各用一個整體鑄件取代由 17個Ti-6A l-4V鈑金件組成的鼻帽和由多個零件、不少緊固件組成的防火封嚴(yán)件。目前已達(dá)到厚度1.27 mm的要求，并引入新生產(chǎn)的C-17飛機(jī)。60個鼻帽鑄件在全壽命期可節(jié)約320萬美元，防火封嚴(yán)件改用薄壁鑄件后可降低成本70%以上。

一種大型軍用運(yùn)輸機(jī)用的鈦合金精鑄件，它取代了原22個加工件，節(jié)省了大部分成本。

8） 第3代鋁鋰合金在A350，A380上的大量應(yīng)用是空客新一代飛機(jī)的一大特色

由于每添加1%鋰就可降低3%的密度和提高6%的彈性模量，因此A380已正式選用鋁鋰合金制造地板梁，正打算用做機(jī)身蒙皮和下翼面的桁條。A350已選用鋁鋰合金制造機(jī)身蒙皮和地板結(jié)構(gòu)等，其原設(shè)計的用量高達(dá)總結(jié)構(gòu)重量的23%。鋁鋰合金經(jīng)大起大落后東山再起的主要原因是在不斷優(yōu)化成分的基礎(chǔ)上推出了2094，2195，2097，2197等第3代合金。這些合金的共同特點是降低了鋰含量和優(yōu)化了銅等合金元素的含量，從而控制了Al3Li相的析出，解決了第2代合金出現(xiàn)的各向異性顯著、抗應(yīng)力腐蝕能力差等問題。第3代鋁鋰合金取代2124，2024鋁合金制成的零部件在F-16戰(zhàn)斗機(jī)上的成功驗證也是東山再起的重要原因。

9） 新型高強(qiáng)鋁合金7085的問世為特大鍛件在A380上的應(yīng)用開辟了道路

已有高強(qiáng)鋁合金的鍛件或厚板的厚度均有一定限制，例如7055限于38 mm，7150雖較理想，其厚度也不允許大于 120 mm。為了獲得厚度更大的高強(qiáng)鋁合金鍛件或厚板，美國Alcoa設(shè)計了一個具有專利權(quán)的7085鋁合金，由于溶鑄性和淬透性好，其鍛件最大厚度已達(dá)240 mm。

7085鋁合金的成分特點是鋅鎂比大和控制的Fe，Si含量適當(dāng)。

7085鋁合金制成的A380飛機(jī)后翼梁是迄今為止最大的一個飛機(jī)模鍛件，長6.4 m，寬1.9 m，質(zhì)量約3900 kg。

10）A380和A350采用激光焊接技術(shù)（LBW）制成6000系鋁合金和鋁鋰合金整體結(jié)構(gòu)件

A350采用激光焊接技術(shù)制造鋁鋰合金機(jī)身結(jié)構(gòu)件，而A380則采用激光焊接技術(shù)制造6000系鋁合金下機(jī)身壁板結(jié)構(gòu)件，以取代以往的鉚接結(jié)構(gòu)件，從而由過去的“裝配式結(jié)構(gòu)”概念改變?yōu)椤罢w式結(jié)構(gòu)”概念。這不僅減輕結(jié)構(gòu)重量、降低成本和提高腐蝕抗力，而且從力學(xué)角度來看，可減少蒙皮損壞后裂紋的增長。這一激光焊接技術(shù)既適用于單曲度壁板，又適用于雙曲度壁板。

2 關(guān)于中國大型飛機(jī)選材原則的建議

1）必須在更高的層次上綜合評估選材方案的安全性、經(jīng)濟(jì)性、舒適性的環(huán)保性

與戰(zhàn)斗機(jī)等較小型的飛機(jī)相比，大型飛機(jī)對選材的要求具有4個“更高”的特點，即更高安全性，更高經(jīng)濟(jì)性，更高舒適性和更高環(huán)保性。波音公司之所以把波音787的復(fù)合材料用量增加至50%左右，就是認(rèn)為這在更高層次上符合了“四性”的要求。其具體理由是：復(fù)合材料經(jīng) 30多年的研究和應(yīng)用，技術(shù)上已經(jīng)成熟，在安全可靠性上是不成問題的，何況復(fù)合材料的損傷容限和抗蝕性顯著優(yōu)于鋁合金，更有利于耐久性和安全性的提高；飛機(jī)結(jié)構(gòu)重量大幅度減輕帶來的經(jīng)濟(jì)效益（包括燃油消耗和維修費(fèi)用顯著降低等），遠(yuǎn)遠(yuǎn)超過了它的負(fù)面效應(yīng)（制造成本較高）；復(fù)合材料的應(yīng)用使舷窗尺寸加大30%，客艙濕度和氣壓有所提高，讓旅客享受更舒適的空中旅行；大量節(jié)省燃油也明顯有利于環(huán)保性。中國大型客機(jī)在將來推出之時，應(yīng)具有當(dāng)時的國際市場競爭力，因此其選材也必須充分考慮“四性”，否則就不具備與屆時國外同類客機(jī)的競爭能力。這個要求非常高，難度很大，但又必須努力去達(dá)到。這是因為：一代飛機(jī)，一代材料；一代材料，一代飛機(jī)。

2）必須盡早具備自主供應(yīng)關(guān)鍵材料的能力

對于大型運(yùn)輸機(jī)，材料應(yīng)立足于國內(nèi)是顯而易見的。對于大型客機(jī)用的材料，可按市場競爭原則進(jìn)行全球采購，但這個“全球”理應(yīng)包括國內(nèi)供應(yīng)商，特別對于關(guān)鍵材料，都應(yīng)盡早具備自主供應(yīng)的能力，即使有些關(guān)鍵材料趕不上首批客機(jī)的進(jìn)度，也應(yīng)大力安排研制任務(wù)并及早解決適航問題，以免出現(xiàn)受制于人的被動局面。

3）必須充分考慮大型客機(jī)與大型運(yùn)輸機(jī)“材料共用，成果共享”的原則

中國的大型飛機(jī)研制項目包含大型客機(jī)和大型運(yùn)輸機(jī)兩大部分。為了縮短研制周期、節(jié)省研制費(fèi)用、降低銷售價格和提高成熟程度，建議設(shè)計和材料工作者緊密結(jié)合，盡可能增加大型客機(jī)和大型運(yùn)輸機(jī)上共用材料的比例。這樣做更有利于客機(jī)用國產(chǎn)材料通過適航條例。

4）必須重視先進(jìn)材料特別是具有中國特色的先進(jìn)材料的選用

既然要求中國大型客機(jī)要具有屆時的國際競爭力，就必須在符合安全性要求的前提下盡可能選用一些先進(jìn)的航空材料，特別是要充分重視具有中國特色的先進(jìn)材料的選用，例如TC21鈦合金不僅具有國際先進(jìn)水平的性能，而且在合金及其鍛造工藝上都具有自主知識產(chǎn)權(quán)。

3 結(jié)束語

中國要有自己設(shè)計制造的大飛機(jī)是中國人民，特別是幾代航空學(xué)者的夢想和愿望。在大型飛機(jī)上用更多自主研制生產(chǎn)的航空材料又是中國材料界，特別是航空材料研究者的夢想和愿望。今天，實現(xiàn)這個夢想和愿望的曙光已經(jīng)撥云而出。只要所有參與大型飛機(jī)工程的中華兒女心懷祖國、情系航空、志在超越、腳踏實地、創(chuàng)新圖強(qiáng)、團(tuán)結(jié)和諧，那么中國自主設(shè)計制造的大型飛機(jī)就一定能在不久的將來展翅翱翔在萬里晴空！

【作者單位：1. 北京航空材料研究院；2. 南昌航空大學(xué)材料科學(xué)與工程學(xué)院】

（摘自《航空學(xué)報》2008年3期）

·高被引論文摘要·

被引頻次：321

大飛機(jī)用鋁合金的研究現(xiàn)狀及展望

劉兵，彭超群，王日初，等

簡單介紹航空用鋁合金的特點及其在大飛機(jī)上的應(yīng)用和發(fā)展，重點敘述大飛機(jī)常用的2×××系和7×××系鋁合金的成分、性能和應(yīng)用，指出現(xiàn)階段國內(nèi)大飛機(jī)用鋁合金材料存在的問題，預(yù)測大飛機(jī)用鋁合金的發(fā)展方向。

大飛機(jī)；鋁合金；2×××系鋁合金；7×××系鋁合金；鋁鋰合金；鋁基復(fù)合材料

來源出版物：中國有色金屬學(xué)報, 2010, 20(9): 1705-1715

被引頻次：163

大型飛機(jī)自動化裝配技術(shù)

許國康

摘要：簡述了大型飛機(jī)及其結(jié)構(gòu)特點，通過比較人與機(jī)器兩種裝配系統(tǒng)的特性，及分析裝配自動化水平與裝配成本等諸因素的關(guān)系曲線，指出了自動化裝配技術(shù)在保證大型飛機(jī)結(jié)構(gòu)長壽命、高效率、低成本研制和生產(chǎn)等方面的意義；對國外大型飛機(jī)的裝配自動化發(fā)展?fàn)顩r進(jìn)行了綜述，簡要分析了國外發(fā)展的幾種主要自動化裝配系統(tǒng)，總結(jié)了國外大型飛機(jī)的自動化裝配水平；對西方國家在大型飛機(jī)自動化裝配中采用的先進(jìn)的裝配理念和方法，如決定性裝配方法等進(jìn)行了概述。最后針對國內(nèi)自動化裝配水平低的現(xiàn)狀和大型飛機(jī)研制和生產(chǎn)的需求，提出了發(fā)展模塊化結(jié)構(gòu)的自動化裝配系統(tǒng)、貫徹并行工程理念、實現(xiàn)面向制造和面向裝配的設(shè)計等發(fā)展建議。

關(guān)鍵詞：自動化裝配；大型飛機(jī)；長壽命；柔性裝配；模塊化；決定性裝配

來源出版物：航空學(xué)報, 2008, 29(3): 227-233

被引頻次：142

大型飛機(jī)部件數(shù)字化對接裝配技術(shù)研究

鄒冀華，劉志存，范玉青

摘要：為克服大型飛機(jī)部件對接裝配的困難，提出了一種集成多項先進(jìn)數(shù)字化技術(shù)的柔性裝配技術(shù)體系。分析并闡述了該體系概念和結(jié)構(gòu)組成，建立了用于部段對接裝配的柔性裝配工作站原型。歸納和闡述了四項主要支撐技術(shù)。其中，裝配過程仿真技術(shù)是以數(shù)字樣機(jī)為基礎(chǔ)的，并說明了其在飛機(jī)部段對接中的應(yīng)用特點和存在的難點。提出了數(shù)字化標(biāo)準(zhǔn)工裝新概念，糾正了傳統(tǒng)實體標(biāo)工的缺點。對機(jī)械隨動定位裝置的樣式、功能及其兩類控制軟件進(jìn)行了說明。最后，說明了激光跟蹤測量技術(shù)在對接裝配中的作用、原理和測量方法。

關(guān)鍵詞：飛機(jī)制造；數(shù)字化裝配；柔性裝配工作站；數(shù)字化標(biāo)準(zhǔn)工裝；機(jī)械隨動定位裝置；激光跟蹤測量

來源出版物：計算機(jī)集成制造系統(tǒng), 2007, 13(7): 1367-1373

被引頻次：125

一代材料技術(shù)，一代大型飛機(jī)

曹春曉

摘要：介紹了用于大型飛機(jī)的新材料的發(fā)展現(xiàn)狀和趨勢。當(dāng)前，歐美大型飛機(jī)機(jī)體的材料結(jié)構(gòu)正從以鋁合金為主過渡至以復(fù)合材料為主，50%復(fù)合材料用量是未來飛機(jī)的起點。新一代大型飛機(jī)的材料技術(shù)特色首先是復(fù)合材料和鈦合金用量創(chuàng)歷史新高，以大幅度減輕飛機(jī)結(jié)構(gòu)重量和降低燃油消耗；其次反映于一些具有新意的材料技術(shù)的成功推出，其中包括復(fù)合材料整體機(jī)身段、全鈦發(fā)動機(jī)掛架、纖維金屬層板、第3代鋁鋰合金、新型高強(qiáng)鋁合金7085、新型高強(qiáng)高韌鈦合金Ti-55531等。最后，對中國剛立項研制的大型飛機(jī)的選材原則提出了建議。

關(guān)鍵詞：大型飛機(jī)；客機(jī)；運(yùn)輸機(jī)；材料；復(fù)合材料；鈦合金；鋁合金

來源出版物：航空學(xué)報, 2008, 29(3): 701-706

被引頻次：119

復(fù)合材料技術(shù)與大型飛機(jī)

陳紹杰

摘要：給出了先進(jìn)復(fù)合材料在大型飛機(jī)上應(yīng)用的歷史和現(xiàn)狀，特別是在B787和A380等機(jī)種上的近期應(yīng)用。指出了應(yīng)用是從小到大、從少到多、從弱到強(qiáng)，一步一步走過來的。分析了應(yīng)用的技術(shù)基礎(chǔ)，說明了復(fù)合材料是一個性能優(yōu)異的新材料，這是前提基礎(chǔ)；其次應(yīng)用是各種預(yù)研計劃認(rèn)真執(zhí)行的結(jié)果；低成本復(fù)合材料技術(shù)是應(yīng)用的重要前提，包括低成本的設(shè)計技術(shù)、制造技術(shù)和材料技術(shù)；30多年來復(fù)合材料技術(shù)的進(jìn)步是堅實的保障。指出了中國于復(fù)合材料技術(shù)領(lǐng)域存在的問題和差距，提出了發(fā)展中國大型飛機(jī)復(fù)合材料技術(shù)的相關(guān)建議。

關(guān)鍵詞：復(fù)合材料；技術(shù)；大型飛機(jī)；應(yīng)用；建議

來源出版物：航空學(xué)報, 2008, 29(3): 605-610

被引頻次：104

大型整體壁板成形技術(shù)

曾元松，黃遐

摘要：大型整體壁板是現(xiàn)代先進(jìn)民用飛機(jī)的重要結(jié)構(gòu)件，大型整體壁板成形技術(shù)是整機(jī)研制過程中所必須要解決的重大關(guān)鍵技術(shù)。從大型整體壁板的結(jié)構(gòu)特點出發(fā)，介紹了整體壁板的結(jié)構(gòu)形式和分類，重點闡述了整體帶筋壁板噴丸成形技術(shù)和時效成形技術(shù)的國外研究應(yīng)用進(jìn)展及發(fā)展趨勢，分析了國內(nèi)現(xiàn)有整體壁板成形技術(shù)的基礎(chǔ)和存在問題，特別介紹了國內(nèi)在 ARJ21新支線飛機(jī)研制中所取得的最新進(jìn)展。最后針對中國大飛機(jī)研制的緊迫需求，提出了盡快開展大飛機(jī)機(jī)翼和機(jī)身整體壁板成形技術(shù)研究的建議和對策。

關(guān)鍵詞：整體壁板；噴丸成形；蠕變時效成形；大飛機(jī)；鋁合金

來源出版物：航空學(xué)報, 2008, 29(3): 721-727

被引頻次：97

自動鋪放技術(shù)在大型飛機(jī)復(fù)合材料結(jié)構(gòu)件制造中的應(yīng)用

肖軍，李勇，李建龍

摘要：自動鋪放技術(shù)是工業(yè)發(fā)達(dá)國家近30年來發(fā)展和廣泛應(yīng)用的自動化制造技術(shù)，包括自動鋪帶技術(shù)和自動鋪絲技術(shù)。這兩項技術(shù)的共同優(yōu)點是采用預(yù)浸料，并能實現(xiàn)自動化和數(shù)字化制造，高效高速。自動鋪放技術(shù)特別適用于大型復(fù)合材料結(jié)構(gòu)件制造，在各類飛行器，尤其是大型飛機(jī)的結(jié)構(gòu)制造中所占比重越來越大。

來源出版物：航空制造技術(shù), 2008, (1): 50-53

被引頻次：97

碳纖維復(fù)合材料在大飛機(jī)上的應(yīng)用

賀福，孫微

摘要：碳纖維復(fù)合材料具有質(zhì)量輕、高比強(qiáng)度、高比模量、耐疲勞、耐腐蝕、耐高溫和尺寸穩(wěn)定性好等一系列優(yōu)異性能，已廣泛用于飛機(jī)制造業(yè)。尤其是近年來，在大型客機(jī) A380和 B787上的用量已占到結(jié)構(gòu)總量的50%左右，引起人們的極大關(guān)注。這一市場的需求必將促進(jìn)碳纖維工業(yè)的大發(fā)展。

關(guān)鍵詞：碳纖維；碳纖維復(fù)合材料；大飛機(jī)；應(yīng)用

來源出版物：高科技纖維與應(yīng)用, 2007, 32(6): 5-8

被引頻次：61

大型飛機(jī)數(shù)字化裝配技術(shù)研究

肖慶東，王仲奇，馬強(qiáng)，等

摘要：針對大型飛機(jī)裝配工作的高復(fù)雜性和高精度，綜合國外航空制造業(yè)的先進(jìn)裝配技術(shù)，概括了數(shù)字化裝配技術(shù)的內(nèi)涵。對數(shù)字化裝配技術(shù)作了深入研究，包括數(shù)字化裝配工藝技術(shù)、數(shù)字化柔性裝配工裝技術(shù)、光學(xué)測量與補(bǔ)償技術(shù)等。在數(shù)字化裝配技術(shù)的應(yīng)用方面，組建了針對大型飛機(jī)機(jī)身壁板零件的數(shù)字化裝配系統(tǒng)平臺，并且分析了該平臺在飛機(jī)零部件裝配應(yīng)用中的特點。飛機(jī)數(shù)字化裝配技術(shù)的研究應(yīng)用，將大幅度降低工裝成本，縮短裝配周期，提高我國的飛機(jī)裝配技術(shù)水平。

關(guān)鍵詞：數(shù)字化裝配；數(shù)字化裝配工藝；數(shù)字化柔性裝配工裝；光學(xué)檢測與補(bǔ)償；數(shù)字化裝配系統(tǒng)

來源出版物：中國制造業(yè)信息化, 2007, 36(3): 26-29

被引頻次：56

大型飛機(jī)機(jī)身調(diào)姿與對接試驗系統(tǒng)

邱寶貴，蔣君俠，畢運(yùn)波，等

摘要：為實現(xiàn)飛機(jī)大部件裝配過程的數(shù)字化、自動化和柔性化，研制了大型飛機(jī)機(jī)身調(diào)姿與對接試驗系統(tǒng)。闡述了該系統(tǒng)的工作原理，通過激光跟蹤儀測量試驗機(jī)身上的檢測點，集成管理系統(tǒng)計算試驗機(jī)身的位姿，控制系統(tǒng)驅(qū)動多個三坐標(biāo)數(shù)控定位器協(xié)同運(yùn)動，實現(xiàn)試驗機(jī)身的調(diào)姿與對接。建立了位姿調(diào)整機(jī)構(gòu)的運(yùn)動學(xué)模型，針對構(gòu)建的硬件平臺完成了包括集成管理系統(tǒng)、測量系統(tǒng)和控制系統(tǒng)在內(nèi)的軟件開發(fā)與集成，并對系統(tǒng)的性能進(jìn)行了測試。試驗結(jié)果表明，試驗機(jī)身的位置調(diào)整精度優(yōu)于0.09 mm，姿態(tài)調(diào)整精度優(yōu)于0.0005。試驗系統(tǒng)涉及的若干關(guān)鍵技術(shù)已成功應(yīng)用于多項國家重點型號工程，大幅提高了飛機(jī)裝配的質(zhì)量和效率。

關(guān)鍵詞：裝配；三坐標(biāo)數(shù)控定位器；激光跟蹤儀；位姿調(diào)整；運(yùn)動協(xié)調(diào)

來源出版物：航空學(xué)報, 2011, 32(5): 908-919

被引頻次：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).

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

被引頻次：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.

關(guān)鍵詞：interferometry; precision measurements; leastsquares methods; large optical elements

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

被引頻次：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.

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

被引頻次：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.

關(guān)鍵詞：flight safety; laminates; fatigue; aircraft; flame resistance

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

被引頻次：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.

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

被引頻次：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.

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

被引頻次：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.

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

被引頻次：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.

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

被引頻次：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.

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

被引頻次：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.

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

·推薦論文摘要·

大型飛機(jī)氣動載荷向有限元節(jié)點等效分配的方法

張建剛，孫仁俊，唐長紅

摘要：將氣動載荷分配到有限元節(jié)點上是工程實際中的一項重要而繁瑣的工作。對于二維的翼面氣動載荷，根據(jù)原始的氣動壓力點的壓力值，采用樣條曲面擬合的方法，擬合得到翼面壓力分布曲面，由該曲面得到有限元節(jié)點上的壓力值，再在有限元模型單元上積分得到有限元節(jié)點載荷供強(qiáng)度設(shè)計使用。大型飛機(jī)具有復(fù)雜的增升裝置，增升裝置的氣動載荷可能是三維的，對于三維的翼面載荷，直接在氣動網(wǎng)格上積分得到氣動載荷的小塊集中力，然后按照沿某一方向投影的方法，找到該集中力作用的單元，最后按照二次規(guī)劃的方法，將其分配到有限元節(jié)點上。

關(guān)鍵詞：氣動載荷；有限元節(jié)點；薄板樣條

來源出版物：力學(xué)與實踐, 2017, 39(1): 25-29

聯(lián)系郵箱：張建剛，155246438@qq.com

大型飛機(jī)研制中的若干數(shù)字化智能裝配技術(shù)

董一巍，李曉琳，趙奇

摘要：大型飛機(jī)的研制是國家提高自主創(chuàng)新能力的戰(zhàn)略重點。為了提高大飛機(jī)裝配質(zhì)量與生產(chǎn)效率，采用數(shù)字化智能裝配技術(shù)是必然的發(fā)展趨勢。本文介紹了飛機(jī)智能化裝配的系統(tǒng)框架與其技術(shù)體系架構(gòu)，闡述了目前大型飛機(jī)裝配所面臨的難題，并指出虛擬現(xiàn)實仿真優(yōu)化技術(shù)、專用智能裝配工藝裝備的開發(fā)，以及飛機(jī)總裝智能裝配生產(chǎn)線技術(shù)是智能裝配技術(shù)的熱點與發(fā)展方向，并分別進(jìn)行了介紹，并闡述了國內(nèi)外應(yīng)用發(fā)展現(xiàn)狀，最后指出了國內(nèi)現(xiàn)有智能裝配技術(shù)的不足與差距。

關(guān)鍵詞：大飛機(jī)；智能裝配；虛擬仿真；智能工裝

來源出版物：航空制造技術(shù), 2016, 497(1/2): 58-63

大飛機(jī)數(shù)字化制造關(guān)鍵技術(shù)

韓志仁

摘要：大型飛機(jī)數(shù)字化制造是一個非常復(fù)雜的系統(tǒng)工程，主要關(guān)鍵技術(shù)包括數(shù)字化并行協(xié)同技術(shù)、仿真技術(shù)、數(shù)字化測量技術(shù)、智能集成技術(shù)、柔性制造技術(shù)、飛機(jī)部件便捷傳送技術(shù)、數(shù)字化信息處理技術(shù)、脈動線制造技術(shù)等，通過這些關(guān)鍵技術(shù)保證大飛機(jī)數(shù)字化制造的每個環(huán)節(jié)高效、順利地進(jìn)行，從而保證大飛機(jī)研制和生產(chǎn)周期短、質(zhì)量高、成本低。對關(guān)鍵技術(shù)進(jìn)行了綜述分析，指出了關(guān)鍵技術(shù)中技術(shù)要點和關(guān)鍵問題，對更好地開展大飛機(jī)數(shù)字化制造具有參考作用。

關(guān)鍵詞：大飛機(jī)；數(shù)字化制造；協(xié)同仿真；數(shù)字化測量；柔性制造

來源出版物：航空制造技術(shù), 2016, 497(1/2): 53-57

一種提高風(fēng)洞動態(tài)試驗數(shù)據(jù)質(zhì)量的模型姿態(tài)控制和測量技術(shù)

劉志濤，孫海生

摘要：低速風(fēng)洞動態(tài)試驗裝置通常采用“電機(jī)+減速器+偏心機(jī)構(gòu)+線性傳動機(jī)構(gòu)”的方式，存在傳遞環(huán)節(jié)多、機(jī)械間隙大等問題，給模型運(yùn)動的精確控制和模型姿態(tài)的精確測量帶來較大困難。為滿足大型客機(jī)等大飛機(jī)對低速風(fēng)洞動態(tài)試驗的要求，基于現(xiàn)有的靜態(tài)試驗通用支撐平臺，采用“電子凸輪”技術(shù)，建立了一套迎角/側(cè)滑角解耦、可進(jìn)行飛機(jī)小振幅動導(dǎo)數(shù)和大振幅非定常氣動特性研究的動態(tài)試驗裝置。利用該動態(tài)試驗裝置進(jìn)行了某飛機(jī)大尺度動態(tài)試驗?zāi)Ｐ蛣訉?dǎo)數(shù)試驗和大振幅振蕩試驗，獲得了試驗數(shù)據(jù)的重復(fù)性，并研究了動態(tài)試驗數(shù)據(jù)和靜態(tài)試驗數(shù)據(jù)之間的相關(guān)性。試驗結(jié)果表明：利用該裝置獲得的某飛機(jī)動態(tài)試驗數(shù)據(jù)重復(fù)性較好、規(guī)律合理，能滿足大型飛機(jī)動態(tài)試驗要求。

關(guān)鍵詞：大型飛機(jī)；動導(dǎo)數(shù)；非定常氣動力；風(fēng)洞試驗；支撐裝置

來源出版物：航空學(xué)報, 2016, 37(8): 101-110

聯(lián)系郵箱：劉志濤，liuzhitao@cardc.cn

8米×6米風(fēng)洞TPS反推力試驗技術(shù)

黃勇，胡卜元，張衛(wèi)國，等

摘要：TPS（渦扇動力模擬器）試驗技術(shù)是風(fēng)洞中模擬發(fā)動機(jī)反推力狀態(tài)最有效的手段。開展反推力試驗的目的是獲得反推力發(fā)動機(jī)對飛機(jī)氣動特性的影響，確定反推力發(fā)動機(jī)的再吸入速度邊界。為滿足我國大飛機(jī)研制的試驗技術(shù)需求，中國空氣動力研究與發(fā)展中心在8 m × 6 m風(fēng)洞發(fā)展了全模TPS反推力試驗技術(shù)。自主研制了TPS反推力試驗專用的高精度六分量桿式應(yīng)變天平、大流量空氣橋和流量控制單元、TPS監(jiān)視報警系統(tǒng)、數(shù)據(jù)采集系統(tǒng)、綜合顯示系統(tǒng)等 TPS反推力試驗系統(tǒng)，制定了試驗?zāi)M準(zhǔn)則、試驗流程和試驗方法，建立了完善的全模TPS反推力試驗技術(shù)。利用TPS反推力試驗技術(shù)，開展了國內(nèi)首期全模 TPS反推力風(fēng)洞試驗，研究了某型飛機(jī)反推力發(fā)動機(jī)的再吸入特性，獲得了反推力發(fā)動機(jī)的再吸入速度邊界。

關(guān)鍵詞：大飛機(jī)；反推力；渦扇動力模擬器；試驗技術(shù)；低速風(fēng)洞

來源出版物：空氣動力學(xué)學(xué)報, 2016, 34(3): 67-74

聯(lián)系郵箱：黃勇，dragonhyong@163.com

復(fù)合材料在新一代大型民用飛機(jī)中的應(yīng)用

馬立敏，張嘉振，岳廣全，等

摘要：新一代大型民用飛機(jī)機(jī)體結(jié)構(gòu)的突出特點是廣泛采用復(fù)合材料?？偨Y(jié)了復(fù)合材料在大型民用飛機(jī)中的發(fā)展，其用量已經(jīng)從1980年整機(jī)質(zhì)量的4%上升到目前的50%，并廣泛應(yīng)用于主承力結(jié)構(gòu)和復(fù)雜曲面結(jié)構(gòu)。以波音787和空客A350飛機(jī)為例，分析了波音和空客公司復(fù)合材料的應(yīng)用情況，發(fā)現(xiàn)復(fù)合材料不僅減輕了飛機(jī)的結(jié)構(gòu)質(zhì)量，提高了飛機(jī)結(jié)構(gòu)的使用壽命，降低了飛機(jī)的維護(hù)費(fèi)用，而且可以增加艙內(nèi)壓力和空氣濕度，提高民用飛機(jī)的經(jīng)濟(jì)性、舒適性、環(huán)保性。復(fù)合材料取代金屬和非金屬等常規(guī)材料制造結(jié)構(gòu)件已經(jīng)成為世界民機(jī)制造業(yè)的主流趨勢，這對中國自主研制的大型民用飛機(jī)的市場競爭力提出了嚴(yán)峻的考驗，為此提出了中國在研制大型民用飛機(jī)時應(yīng)用復(fù)合材料應(yīng)注意的一些問題。

關(guān)鍵詞：復(fù)合材料；民用航空；大型飛機(jī)；飛機(jī)結(jié)構(gòu)；波音；空中客車

來源出版物：復(fù)合材料學(xué)報, 2015, 32(2): 317-322

聯(lián)系郵箱：馬立敏，malimin@comac.cc

中國復(fù)合材料自動鋪放技術(shù)研究進(jìn)展

文立偉，肖軍，王顯峰，等

摘要：首先扼要介紹了復(fù)合材料自動鋪放（自動鋪帶和自動鋪絲）成形技術(shù)的原理、特點和該技術(shù)在國外航空航天領(lǐng)域的應(yīng)用概況。然后系統(tǒng)介紹了近年來中國國內(nèi)復(fù)合材料自動鋪帶的裝備技術(shù)、軟件技術(shù)和材料工藝技術(shù)的研發(fā)歷程，總結(jié)了其關(guān)鍵技術(shù)的突破和應(yīng)用進(jìn)展，并指出開發(fā)低成本高效鋪帶技術(shù)是未來的重要方向。同時介紹了國內(nèi)自動鋪絲技術(shù)基礎(chǔ)研究（裝備、軟件和工藝方法）的進(jìn)展，并且著重介紹了南京航空航天大學(xué)自動鋪絲應(yīng)用技術(shù)（工業(yè)樣機(jī)與材料工藝技術(shù)）的研發(fā)和應(yīng)用情況。最后通過分析，歸納了自動鋪絲技術(shù)應(yīng)用研究的瓶頸問題，并提出了研究建議。

關(guān)鍵詞：先進(jìn)復(fù)合材料；大型飛機(jī)；自動鋪帶；自動鋪絲

來源出版物：南京航空航天大學(xué)學(xué)報, 2015, 47(5): 637-649

聯(lián)系郵箱：肖軍，xiao@nuaa.edu.cn

高升力系統(tǒng)控制計算機(jī)容錯技術(shù)研究

徐奡，夏德天，鄭久壽

摘要：在大型飛機(jī)的起飛、降落、巡航飛行中，高升力系統(tǒng)起著重要的作用。電傳控制技術(shù)在高升力系統(tǒng)中的應(yīng)用減輕了系統(tǒng)重量，為系統(tǒng)帶來更佳的性能，高級自動控制和更好的魯棒性。以現(xiàn)代大型飛機(jī)先進(jìn)高升力電傳控制系統(tǒng)為研究對象，對高升力電傳控制計算機(jī)設(shè)計技術(shù)開展研究，重點探討了系統(tǒng)冗余架構(gòu)、硬件設(shè)計、余度管理及節(jié)點一致性機(jī)制等關(guān)鍵設(shè)計技術(shù)。

關(guān)鍵詞：大型飛機(jī)；高升力；安全性；冗余；容錯

來源出版物：微電子學(xué)與計算機(jī), 2015, (6): 36-40, 45

聯(lián)系郵箱：徐奡，xuao@21cn.com

MBD技術(shù)在大飛機(jī)研制中的應(yīng)用

李婷婷，劉俊堂，張永輝

摘要：大飛機(jī)研制MBD技術(shù)應(yīng)用實踐表明，MBD技術(shù)不僅僅是信息表達(dá)方式的改變，更是由于這種改變引起的飛機(jī)研制模式的改變。同時，由于三維設(shè)計更符合人類的原始創(chuàng)新方式及更進(jìn)一步的設(shè)計信息數(shù)學(xué)描述等，采用MBD技術(shù)還可以研制出更多的設(shè)計效能工具，如從基本的設(shè)計模板、左右件自動生成到保證上下游設(shè)計信息唯一且一致的關(guān)聯(lián)設(shè)計等。

來源出版物：航空制造技術(shù), 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.

來源出版物：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.

關(guān)鍵詞：large aircraft fuselage panel; deformation; measurement point; D-optimality; adaptive simulated annealing genetic algorithm; Fisher Information Matrix

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

聯(lián)系郵箱：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.

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

聯(lián)系郵箱：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.

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

聯(lián)系郵箱：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.

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

聯(lián)系郵箱：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.

關(guān)鍵詞：aircraft design; aircraft systems; electrical load analysis; more electric aircraft

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

聯(lián)系郵箱：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.

關(guān)鍵詞：impact; large commercial aircraft; containment building; different fidelity models; finite element simulation

來源出版物：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.

關(guān)鍵詞：actuation system; dissimilar redundant; force fighting; adaptive decoupling control; synchronous control

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

聯(lián)系郵箱：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.

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

編輯：王微

典

文章題目第一作者來源出版物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