DEVELOPMENT OF INTELLIGENT CAD FOR AIRCRAFT CONCEPTUAL DESIGN

Research Project

Project/Area Number	02650044
Research Category	Grant-in-Aid for General Scientific Research (C)
Allocation Type	Single-year Grants
Research Field	Aerospace engineering
Research Institution	THE UNIVERSITY OF TOKYO
Principal Investigator	SATO Junzo UNIVERSITY OF TOKYO,FACULTY OF ENGINEERING,PROFESSOR, 工学部, 教授 (80011211)
Co-Investigator(Kenkyū-buntansha)	SUNADA Yasuto UNIVERSITY OF TOKYO,FACULTY OF ENGINEERING,ASSISTANT, 工学部, 助手 (50216488) TATSUMI Kaoru UNIVERSITY OF TOKYO,FACULTY OF ENGINEERING,ASSISTANT, 工学部, 助手 (40236550) 杉本剛東京大学, 工学部, 助手 (60196748)
Project Period (FY)	1990 – 1992
Project Status	Completed (Fiscal Year 1992)
Budget Amount *help	¥1,900,000 (Direct Cost: ¥1,900,000) Fiscal Year 1992: ¥200,000 (Direct Cost: ¥200,000) Fiscal Year 1991: ¥500,000 (Direct Cost: ¥500,000) Fiscal Year 1990: ¥1,200,000 (Direct Cost: ¥1,200,000)
Keywords	CAD / AIRCRAFT / CONCEPTUAL DESIGN / 航空桟概念設計
Research Abstract	The initial aircraft conceptual design has traditionally been made with the help of the statistical treatment of the empirical data taken from the aircrafts currently in use. Aircrafts are sized to match the requirements both from the user and from the airworthiness regulations which are set just for safety. Sizings were done mostly by tedious trial-and-error method. The recent advances in computer technology, however, make it possible to perform the initial sizing of aircrafts while taking into account the aircraft detailed performance by using small computers. In the present research a method of sizing aircraft wings and fuselages optimized for performance is presented. The aerodynamic performances are computed by using the panel method and the optimum shapes are obtained through the nonlinear optimization. The classical sizing procedure using the empirical data is also programed for personal computer in BASIC language. Unification with the aerodynamic optimization program remains to be a future problem.