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The article discusses a study which examined attitude control using modified Rodrigues parameters (MRP). Topics covered include description about the Euler parameters, which is used by the most common parameterization, some works that focused on the attitude disturbance rejection problem, and an illustration of the Euler's equation. It noted a possible formulation for the attitude control problem.

The attitude control of an Earth-pointing spacecraft in a circular orbit, subject to the gravity-gradient torque, is explored. The spacecraft attitude is described using the modified Rodrigues parameters. A series of controllers are designed using the nonlinear H∞ control methodology and are subsequently generated using a Taylor series expansion to approximate solutions of the Hamilton–Jacobi equations. These controllers are applied to the problem of Earth-pointing spacecraft in circular orbits. The controllers are compared using both input–output and initial condition simulations, in an effort to gauge the improvements made possible by nonlinear feedback. [ABSTRACT FROM AUTHOR]