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The Design of attitude control system for large maneuvering aircrafts
Pages: 16-25+7
Year: Issue:  3
Journal: Aerospace Control

Keyword:  Flight control Nonlinear system Attitude control system.;
Abstract: For the condition of widely using strapdown systems in tactical missiles and the singularity problem caused by using attitude angle error feedback for controlling the attitudes of large maneuvering aircrfts the design method for the atttude control systems based on quaternion is preseuted and studied in the paper. A dynamics model described by quaternion for the air crafts is given first. Then, a nonlinear attitude control system is designed as an example based on the synthesis method of nonlineal cntrol systems. Finally the effectiveness of the proposed method is proved by digital simulation. The stady results show that the method can not only resolve the singularity problem existed in the attitude description but also reduce largely the computig time of computers.
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