Dynamic Sliding Mode Autopilot for Nonlinear Non-Minimum Phase Flight Vehicle
-
- BAHRAMI Mohsen
- Department of Mechanical Engineering, Amirkabir University of Technology Aerospace Research Institute
-
- EBRAHIMI Behrouz
- Department of Mechanical Engineering, Amirkabir University of Technology Aerospace Research Institute
-
- ROSHANIAN Jafar
- Aerospace Research Institute Department of Aerospace Engineering, KNT University of Technology
この論文をさがす
抄録
Design and synthesis of a nonlinear non-minimum phase supersonic flight vehicle longitudinal dynamics control for g commands output tracking are presented. The non-minimum nature of the resulting input/output pair necessitates using a modified switching manifold in sliding mode control theory. The dynamic sliding manifold is designed to compensate for unstable internal dynamics of the system associated with coupling between the moment generating actuators and aerodynamic forces on the flight vehicle. The method is simple to implement in practical applications and enables the sliding mode control design to exhibit the desired dynamic properties during the entire output-tracking process independent of matched perturbations and accommodates unmatched perturbations. Simulation results are presented to demonstrate the performance, robustness, and stability of the autopilot.
収録刊行物
-
- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
-
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 51 (174), 236-243, 2009
一般社団法人 日本航空宇宙学会
- Tweet
詳細情報 詳細情報について
-
- CRID
- 1390001204079458688
-
- NII論文ID
- 10024825629
-
- NII書誌ID
- AA0086707X
-
- ISSN
- 21894205
- 05493811
-
- NDL書誌ID
- 9796503
-
- 本文言語コード
- en
-
- データソース種別
-
- JaLC
- NDL
- Crossref
- CiNii Articles
-
- 抄録ライセンスフラグ
- 使用不可