MATHEMATICAL MODEL OF TRIAXIAL MULTIMODE ATTITUDE AND HEADING REFERENCE SYSTEM

• Main Author: Olha Sushchenko
• Format: Article
• Language: English
• Published: National Aviation University 2017-07-01
• Series: Vìsnik Nacìonalʹnogo Avìacìjnogo Unìversitetu
• Subjects: accelerometers; attitude and heading reference systems; control and correction moments; dynamically tuned gyros; inertial navigation systems
• Online Access: http://jrnl.nau.edu.ua/index.php/visnik/article/view/11745

<p><strong><em>Purpose: </em></strong><em>The paper deals with the mathematical description of the gimballed attitude and heading reference systems, which can be applied in design of strategic precision navigation systems. The main goal is to created mathematical description taking into consideration the necessity to use different navigations operating modes of this class of navigation systems. To provide the high accuracy the indirect control is used when the position of the gimballed platform is controlled by signals of gyroscopic devices, which are corrected using accelerometer’s signals. <strong>Methods:</strong> To solve the given problem the methods of the classical theoretical mechanics, gyro theory, and inertial navigation are used. <strong>Results:</strong> The full mathematical model of the gimballed attitude and heading reference system is derived including descriptions of different operating modes. The mathematical models of the system Expressions for control and correction moments in the different modes are represented. The simulation results are given. <strong>Conclusions: </strong>The represented results prove efficiency of the proposed models. Developed mathematical models can be useful for design of navigation systems of the wide class of moving vehicles.</em><strong><em></em></strong></p>