Published 2005
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Analysis of aircraft pitch axis stability augmentation system using sum of squares optimization
Abstract
The region of attraction of a trim point for the pitch axis of a nonlinear modeled aircraft modulated via linear dynamic inversion based controller was determined numerically. The model incorporates uncertainty in the position of center of gravity along the X-body axis. The stability regions are computed using SOSTOOLS, which converts the required sum of squares conditions to an appropriate semi definite program that is then solved using SeDuMi.
Additional Information
© 2005 AACC. Issue Date: 8-10 June 2005. Date of Current Version: 01 August 2005.Attached Files
Published - KRIacc05a.pdf
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Additional details
- Eprint ID
- 23963
- Resolver ID
- CaltechAUTHORS:20110609-133753780
- Created
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2011-06-14Created from EPrint's datestamp field
- Updated
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2021-11-09Created from EPrint's last_modified field
- Series Name
- Proceedings of the American Control Conference
- Other Numbering System Name
- INSPEC Accession Number
- Other Numbering System Identifier
- 8633800