Dynamic Sliding Mode Autopilot for Nonlinear Non-Minimum Phase Flight Vehicle

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概要

• 論文の詳細を見る

• 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.

• 社団法人 日本航空宇宙学会の論文
• 2009-02-04

著者

• Ebrahimi Behrouz

  Department Of Mechanical Engineering Amirkabir University Of Technology

• BAHRAMI Mohsen

  Department of Mechanical Engineering, Amirkabir University of Technology

• ROSHANIAN Jafar

  Aerospace Research Institute

• Roshanian Jafar

  Dep. Of Aerospace Engineering K. N. Toosi Univ. Of Technol.

• Bahrami Mohsen

  Department Of Mechanical Engineering Amirkabir University Of Technology

関連論文

• Dynamic Sliding Mode Autopilot for Nonlinear Non-Minimum Phase Flight Vehicle

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