NDLI: H control of winged rocket and its flight test

Content Provider	IEEE Xplore Digital Library
Author	Yonemoto, K. Kaji, S.
Copyright Year	2009
Description	Author affiliation: Toyota Motor Kyushu, Inc., Fukuoka, Japan (Kaji, S.) \|\| Faculty of Engineering, Department of Mechanical and Control Engineering, Space Engineering Section, Kyushu Institute of Technology, Fukuoka, Japan (Yonemoto, K.)
Abstract	H theory is one of the advanced design methodologies of attitude control law with robustness. There have been many application studies of H theory on the actual flight vehicle, but the problem of insufficient performance of controllability and poor adaptability to flight environmental conditions such as dynamic pressure or flight Mach number have been always in questions. In addition to the design problem, the selection of weighting function for loop-shaping to achieve appropriate control with robustness and controllability by try and error requires the designers a lot of labor. This paper discusses the applicability of H theory, which employs feed forward controller and dynamic pressure attenuator, to the design of the attitude control law of a small winged rocket developed by Kyushu Institute of Technology and its flight test.
Starting Page	3222
Ending Page	3227
File Size	844275
Page Count	6
File Format	PDF
ISBN	9784907764340
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2009-08-18
Publisher Place	Japan
Access Restriction	Subscribed
Rights Holder	SICE
Subject Keyword	Robust control Controllability Vehicle dynamics Design methodology Vehicles Error correction Feeds Pressure control Attenuators Rockets flight test H∞ theory winged rocket
Content Type	Text
Resource Type	Article

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4	Project PI / Joint PI	Principal Investigator and Joint Principal Investigators of the project	Dr. B. Sutradhar bsutra@ndl.gov.in Prof. Saswat Chakrabarti will be added soon
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