(3)機(jī)身整體壁板
建議以焊接整體帶筋壁板為研究重點(diǎn) ,盡快開展如下工作 :①針對典型結(jié)構(gòu)的焊接 (激光和攪拌摩擦焊)和成形工藝 (噴丸成形和時(shí)效成形)基礎(chǔ)試驗(yàn) ;②焊接和成形后材料力學(xué)性能分析評估 ;
③材料微觀組織結(jié)構(gòu)變化規(guī)律研究 ;④針對激光焊接和攪拌摩擦焊接的工藝驗(yàn)證試驗(yàn) ;⑤針對焊

核心關(guān)鍵制造
,應(yīng)盡快立項(xiàng)開展針對大飛機(jī)機(jī)翼和機(jī)身的整體壁板長壽命、低成本成形技術(shù)的系統(tǒng)研究 ,才能有效地解決這一長期制約中國飛機(jī)研制的重大瓶頸問題 ,確保大飛機(jī)的研制成功。
參　考　文　獻(xiàn)
[1]　《航空制造工程手冊》總編委會.航空制造工程手冊 —
—飛機(jī)鈑金工藝[M].北京 :航空工業(yè)出版社 , 1992 : 3972400. Aeronautical Manufacturing Technology Manual Ehief Ed2 itorial Committee. Aeronautical manufacturing technology manual —sheet metal forming[M]. Beijing: Aviation In2 dustry Press,1992: 3972400. (in Chinese)

[2]　常榮福.飛機(jī)鈑金零件制造技術(shù)[ M ].北京 :國防工業(yè)出版社 , 1992 :942117. Chang Rongfu. Sheet metal forming technology[M].Bei2 jing: National Defence Industry Press, 1992:942117. (in Chinese)

[3]　MunroeJ , Wilkins K, Gruber M. Integral airframe struc2 tures (IAS) —validated feasibility study of integrally stiff2 ened metallic fuselage panels for reducing manufacturing costs[R]. NASA/CR220002209337 ,2000.

[4]　曾元松 ,黃遐 ,李志強(qiáng).先進(jìn)噴丸成形技術(shù)及其應(yīng)用與發(fā)展

[J ].塑性工程學(xué)報(bào) ,2006 , 13 (3) :23228.
Zeng Yuansong , Huang Xia , Li Zhiqiang. The application
and development of advanced shot peen forming technolo2
gies[J].Journal of Plasticity Enginnering, 2006, 13 (3) :
23228. (in Chinese)

[5]　O’Hara P. Peen2forming —a developmenting technique

[C] ∥Proceedings of the 8th International Conference on Shot Peening (ICSP8).2002:2152226.

[6]　Staff S P. The development of roto peening[J]. TSP,

488.
[ 12 ]　Hambrick D M. Age forming technology expanded in an aotoclave[R]. SAE Paper 850885 , 1985.

[ 13 ]　RonanD. Ageformablepanelsforcommercialaircraft[R]. G4RD2CT22002200743 ,2002.

[14 ]　曾元松 ,許春林 ,王俊彪 ,等. ARJ21飛機(jī)大型超臨界機(jī)翼整體壁板噴丸成形技術(shù) [J ].航空制造技術(shù) ,2007 (3) :382

41.
Zeng Yuansong , Xu Chunlin , Wang junbiao ,et al. Shot
peenformingof integralpanelfor supercritical wings [J].
Aeronautical Manufacturing Technology , 2007 (3) :38241.
(in Chinese)

[ 15 ]　李勁風(fēng) ,鄭子樵 ,李世晨 ,等.鋁合金時(shí)效成形及時(shí)效成形鋁合金[J ].材料導(dǎo)報(bào) , 2006 ,20 (5) :1012103. Li Jinfeng , Zheng Ziqiao ,Li Shichen , et al. Age forming of Al alloys and ageformable Al alloys[J]. Journal of Ma2 terials , 2006 ,20 (5) :1012103. (in Chinese)

[ 16 ]　周賢賓 ,常和生 ,陳愛雅 ,等.帶筋壁板的時(shí)效應(yīng)力松弛校形[J ].航空制造工程與維修 , 1998 (5) :19223. Zhou Xianbing, Chang Hesheng, Chen Aiya. Stress2re2 laxtion sizing integral panel[J ]. Aviation Engineering and Maintenance ,1998 (5) :19223. (in Chinese)

作者簡介 :曾元松 (1971 -)　男 ,博士 ,研究員。主要研究方向 :整體壁板成形與強(qiáng)化技術(shù)、管件成形技術(shù)和鈑金零件數(shù)字化制造技術(shù)等。
Tel : 010285701351 E2mail: yszengnantes@yahoo.com
黃遐(1977 -)　女 ,碩士 ,工程師。主要研究方向 :整體壁板成形技術(shù)。
Tel : 010285701254 E2mail : huangxia @bamtri. com. cn
(責(zé)任編輯 :蔡斐 ,楊冬)

　　文章編號 :100026893 (2008) 0320627207

帶油箱結(jié)構(gòu)的機(jī)身框段墜撞仿真分析

何歡 ,陳國平 ,張家濱 (南京航空航天大學(xué)振動工程研究所 ,江蘇南京　 210016)
Crash Simulation of Fuselage Section with Fuel Tank
He Huan , Chen Guoping , Zhang Jiabin
(Institute of Vibration Engineering Research , Nanjing University of Aeronautics and Astronautics ,
Nanjing　210016 , China)
摘　要 :主要研究了任意拉格朗日 /歐拉耦合方法計(jì)算帶油箱的機(jī)身框段的墜撞過程。首先 ,建立了帶油箱結(jié)構(gòu)的機(jī)身框段墜撞分析模型 ,包括機(jī)身框段結(jié)構(gòu)模型和歐拉流體模型。采用水代替油箱內(nèi)部燃油 ,考慮了
裝水量和機(jī)身框段最大垂向壓縮位移、最大過載和能量吸收等參數(shù)之間的關(guān)系。通過仿真分析 ,揭示了沖擊載荷作用下油箱內(nèi)部燃油量對機(jī)身框段各個(gè)部分結(jié)構(gòu)的損傷破壞的影響。研究指出 ,在垂直撞擊環(huán)境下 ,機(jī)身加強(qiáng)框和蒙皮是主要的吸能結(jié)構(gòu)。在油箱內(nèi)裝水量多的情況下 ,油箱結(jié)構(gòu)的吸能作用不能忽略。給出了應(yīng)急著陸或可生存墜撞事故發(fā)生前 ,飛行員所應(yīng)采取的緊急措施。關(guān)鍵詞 :任意拉格朗日 /歐拉耦合 ;耐撞性 ;油箱結(jié)構(gòu) ;機(jī)身框段中圖分類號 : V221　　　文獻(xiàn)標(biāo)識碼 :A Abstract : A numerical model for the crash simulation of a fuselage section with a fuel tank is developed in this paper. The fluid2structure interaction is considered in the impact simulation using the arbitrary Lagrangian/ Eulerian coupling method. The whole model consists of a finite element model of the fuselage section with a fu2 el tank and an Eulerian model of the water inside the fuel tank , which is used instead of fuel. Crashworthiness of the fuselage section under the influence of the water volume inside the fuel tank is taken into account. How the water sloshing inside the fuel tank influences the deformation of the fuselage section is analyzed. The rela2 tionship is established between the water volume and the maximal vertical impact displacement , overload and energy absorption of the fuselage section. Simulation results reveal the relationship between the fuel weight and the responses and failure of the fuselage section. Numerical results show that most of the impact energy is absorbed by the stiffening frame and out2skin , and that the energy absorbed by the fuel tank cannot be ignored when there is a lot of water in it. Recommendations are made to the pilots to deal with emergency landing or survive crash conditions. Key words : arbitraryLagrangian/Euleriancoupling; crashworthiness;fuel tank;fuselage section
　
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