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| DC Field | Value | Language |
|---|---|---|
| dc.creator | Wiese, Daniel P. | - |
| dc.creator | Annaswamy, Anuradha M. | - |
| dc.creator | Muse, Jonathan A. | - |
| dc.creator | Bolender, Michael A. | - |
| dc.creator | Lavretsky, Eugene | - |
| dc.date | 2016-03-09T20:49:00Z | - |
| dc.date | 2016-03-09T20:49:00Z | - |
| dc.date | 2016-03-09 | - |
| dc.date.accessioned | 2023-04-13T08:25:00Z | - |
| dc.date.available | 2023-04-13T08:25:00Z | - |
| dc.identifier | http://hdl.handle.net/1721.1/101648 | - |
| dc.identifier.uri | http://lib.yhn.edu.vn/handle/YHN/682 | - |
| dc.description | This paper presents a new method of synthesizing an output feedback adaptive controller for a class of uncertain, non-square, multi-input multi-output systems that often occur in hypersonic vehicle models. The main challenge that needs to be addressed is the determination of a corresponding square and strictly positive real transfer function. This paper proposes a new procedure to synthesize two gain matrices that allows the realization of such a transfer function, thereby allowing a globally stable adaptive output feedback law to be generated. The unique features of this output feedback adaptive controller are a baseline controller that uses a Luen- berger observer, a closed-loop reference model, manipulations of a bilinear matrix inequality, and the Kalman- Yakubovich Lemma. Using these features, a simple design procedure is proposed for the adaptive controller, and the corresponding stability property is established. The proposed adaptive controller is compared to the classical multi-input multi-output adaptive controller. A numerical example based on a 6 degree-of-freedom nonlinear, scramjet powered, blended wing-body generic hypersonic vehicle model is presented. The adaptive output feedback controller is applied to result in stable tracking of uncertainties that destabilize the baseline linear output feedback controller. | - |
| dc.description | Approved for Public Release; Distribution Unlimited. Case Number 88ABW-2014-2551. | - |
| dc.format | application/pdf | - |
| dc.language | en_US | - |
| dc.rights | Attribution-NoDerivs 3.0 United States | - |
| dc.rights | http://creativecommons.org/licenses/by-nd/3.0/us/ | - |
| dc.title | Adaptive Output Feedback Based on Closed-Loop Reference Models for Hypersonic Vehicles | - |
| Appears in Collections | Tài liệu ngoại văn | |
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