Linearization‐based attitude error regulation: multiplicative error case

Abstract

Linearization-based attitude error regulation: multiplicative error case R. Ozgur Doruk Article information:To cite this document: R. Ozgur Doruk, (2009),"Linearization-based attitude error regulation: multiplicative error case", Aircraft Engineering and Aerospace Technology, Vol. 81 Iss 6 pp. 536 -540 Permanent link to this document: http://dx.(2010),"State space identification and implementation of H∞ control design for small-scale helicopter", Aircraft Engineering and Aerospace Technology, Vol. 82 Iss 6 pp. 340-352 http://dx.If you would like to write for this, or any other Emerald publication, then please use our Emerald for Authors service information about how to choose which publication to write for and submission guidelines are available for all. Please visit www.emeraldinsight.com/authors for more information. About Emerald www.emeraldinsight.comEmerald is a global publisher linking research and practice to the benefit of society. The company manages a portfolio of more than 290 journals and over 2,350 books and book series volumes, as well as providing an extensive range of online products and additional customer resources and services.Emerald is both COUNTER 4 and TRANSFER compliant. The organization is a partner of the Committee on Publication Ethics (COPE) and also works with Portico and the LOCKSS initiative for digital archive preservation. AbstractPurpose -The purpose of this paper is to design and simulate a linearized attitude stabilizer based on linear quadratic regulator theory (LQR) using the multiplicative definition of the attitude. Design/methodology/approach -The attitude is modeled by the modified Rodriguez parameters that provide a minimal representation of attitude and always invertible kinematics. The nonlinear model of the satellite attitude dynamics is linearized around the origin and an LQR is proposed for the linearized design. They are also simulated using the original nonlinear satellite dynamics in order to verify that the controller is operating properly. Simulations include randomly selected initial conditions to justify the stability against various initial conditions. Findings -Theoretically, the resultant controllers are locally stable around the origin. However, the simulation results show that the attitude is well regulated in the presence of both inertia uncertainties and random initial conditions. Originality/value -The originality of this work is due to its demonstration that complicated attitude regulators are not the solution for proper satellite or spacecraft attitude stabilization.

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