Please wait a minute...
航空学报
 Home  |  About Journal  |  Editorial Board  |  Forthcoming Articles  |  Archive  |  Subscribe  |  Download  |  Contacts Us  |  Chinese
Acta Aeronautica et Astronautica Sinica  2011, Vol. 32 Issue (1): 117-127    DOI: CNKI:11-1929/V.20101115.1834.005
Solid Mechanics and Vehicle Conceptual Design Current Issue | Archive | Adv Search |
Preliminary Design of Unconventional Configuration Aircraft Using Multidisciplinary Design Optimization
HU Tianyuan, YU Xiongqing
Key Laboratory of Fundamental Sciences for National Defense-Advanced Design Technology of Flight Vehicles,Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Download:  PDF(1868KB) 
Export:  BibTeX | EndNote (RIS)      
Abstract  This article is aimed at demonstrating how multidisciplinary design optimization (MDO) can be effectively applied to the preliminary design of an unconventional configuration aircraft, using the flying wing configuration aircraft as an example. Based on the two-level optimization method, a procedure is proposed for the implementation of MDO of the aircraft preliminary design, which consists of three main parts: system level optimization, subsystem level optimization (or evaluation) and multidisciplinary model generator. The objective of the system level optimization is to obtain overall optimal performance through the adjustment of the global design variables. The subsystem level consists of several disciplines, including aerodynamics, stealth, structure, internal layout, mass and performance. The task of the subsystem level optimization is to optimize the design goal of each discipline under the discipline constraints by the adjustment of local shape design variables. A multidisciplinary model generator is used to generate automatically a model for each disciplinary analysis, and it is one of the key techniques enabling the automation of the MDO process. A computing framework which integrates all the disciplinary analyses and optimization models is established based on the proposed MDO procedure. The application example indicates that the MDO procedure proposed in this article can be applied effectively to the preliminary design of an unconventional configuration aircraft.
Key words:  aircraft preliminary design      multidisciplinary design optimization      unconventional configuration      flying wing      aerodynamics      stealth      radar cross section      structure      performance     
Received:  14 May 2010      Published:  25 January 2011
V211  

Cite this article: 

HU Tianyuan;YU Xiongqing. Preliminary Design of Unconventional Configuration Aircraft Using Multidisciplinary Design Optimization. Acta Aeronautica et Astronautica Sinica, 2011, 32(1): 117-127.

URL: 

http://hkxb.buaa.edu.cn/EN/CNKI:11-1929/V.20101115.1834.005      OR     http://hkxb.buaa.edu.cn/EN/Y2011/V32/I1/117

[1] WANG Rong, YAN Ming, BAI Peng, YANG Yunjun, XU Guowu. Optimization design of aerodynamics and stealth for a flying-wing UAV planform[J]. 航空学报, 2017, 38(S1): 721532-721532.
[2] LEI Xiaoxin, ZHANG Yanjun, JI Luming, ZHU Liang. Equivalent analysis spectrum construction method for aircraft structure containing cracks[J]. 航空学报, 2017, 38(S1): 721577-721577.
[3] WANG Jin, YANG Hui, WANG Liping, DONG Pu. Surface design for anti-icing and hydrophobic micro-structures[J]. 航空学报, 2017, 38(S1): 721522-721522.
[4] HAN Ge, YANG Chengwu, LI Ziliang, ZHAO Shengfeng, LU Xin'gen. A review of studies on pipe diffuser of centrifugal compressor[J]. 航空学报, 2017, 38(9): 520949-520949.
[5] GAO Jie, ZHENG Qun, YUE Guoqiang, DONG Ping, JIANG Yuting. Research progress on turbine blade tip aerodynamics and heat transfer technology for gas turbines[J]. 航空学报, 2017, 38(9): 521019-521019.
[6] LIU Haitao, ZHAO Wenqiang, LI Chunming, LI Dongxia. Path planning method for UAV relay communication system with space-time block coding[J]. 航空学报, 2017, 38(9): 321048-321048.
[7] CHEN Yunyong, WAN Ke, YANG Xiaohe, DING Jianguo. Influence of tip clearance on high-bypass-ratio fan/booster[J]. 航空学报, 2017, 38(9): 520951-520951.
[8] LI Wencan, RAO Yu, LI Bo, QIN Jiang. Experimental of turbulent flow heat transfer of dimple vortex generators with rounded edge[J]. 航空学报, 2017, 38(9): 520999-520999.
[9] QIAN Chao, ZHANG Zijian, LI Dawei. On-line reliability assessment of platform inertial navigation system[J]. 航空学报, 2017, 38(9): 321259-321259.
[10] HONG Shuli, HUANG Guoping. Introducing DMD method to study dynamic structures of flow separation with and without control[J]. 航空学报, 2017, 38(8): 120876-120876.
[11] LUO Yanyan, CAI Ming, YU Changchao, WANG Biao. Influence of vibration on contact performance degradation of electrical connectors[J]. 航空学报, 2017, 38(8): 220936-220936.
[12] YAN Xufei, CHEN Renliang. Control strategy optimization of dynamic conversion procedure of tilt-rotor aircraft[J]. 航空学报, 2017, 38(7): 520865-520865.
[13] ZHAO Hong, LI Jianbo, LIU Cheng. Conceptual design and analysis of electric helicopters[J]. 航空学报, 2017, 38(7): 520866-520866.
[14] WANG Ziyi, ZHANG Weiwei. Unsteady aerodynamic reduced-order modeling method for parameter changeable structure[J]. 航空学报, 2017, 38(6): 220829-220829.
[15] QI Junwei, WANG Chunjie, DING Jianzhong. Precision analysis of deployable structures based on dimension reduction method and effective link length[J]. 航空学报, 2017, 38(6): 220590-220590.
No Suggested Reading articles found!

Copyright © 2010 Chinese Journal of Aeronautics
Add: Press of AAAS 37 Xueyuan Road,Haidian District,Beijing 100191,China
Tel:010-82317058, 82318016   Fax:010-82313502   E-mail:hkxb@buaa.edu.cn
Support by Beijing Magtech Co.ltd, E-mail: support@magtech.com.cn