Nonlinear H microsatellite attitude control

Ciann-Dong Yang, Yuan Hsiang Shen, Chi Chung Luo, Gong Chen, Yeong Hwa Chang

Research output: Contribution to journalArticlepeer-review


Because of a great decrease in size and weight, the pointing accuracy of microsatellite is vulnerable to space environmental disturbance and the internal uncertainty of moment-of-inertia variation. This paper demonstrates to model a microsatellite and design a nonlinear H attitude controller, which is determined via the solution of Hamilton-Jacobi partial differential inequality corresponding to nonlinear H state feedback control law. Considering the constraints in accuracy of sensors and actuators, and the disturbance from gravity-gradient torque, geomagnetic torque and aerodynamic torque, the microsatellite attitude control is designed to validate the robust performance of nonlinear H attitude controller.

Original languageEnglish
Pages (from-to)55-64
Number of pages10
JournalZhongguo Hangkong Taikong Xuehui Huikan/Transactions of the Aeronautical and Astronautical Society of the Republic of China
Issue number1
Publication statusPublished - 2004 Mar 1

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


Dive into the research topics of 'Nonlinear H microsatellite attitude control'. Together they form a unique fingerprint.

Cite this