Nutation control strategy through state feedback: application to a spin-stabilized autonomous system

Abstract

This research relies on nutation control strategy through state feedback with its application to a spin-stabilized autonomous system such as spacecraft. The key subject behind the investigation is to present a new formulation in the area of attitude control to be able to handle the rotational angles in connection with angular rates, while the system under control is in a predefined mission operation plan. In a word, the main contribution of the research is to cope with the nutation in the process of spin-stabilized attitude control approach in association with the y, z-axis rotational angles to be desirable, at each instant of time. With this goal, the x-axis spin up mode of the system under control is first handled, while the y, z-axis rotational angles of such a system can instantly be adjustable to guarantee the performance of the aforementioned mission operation plan with high accuracy. And then the nutation and angular rates of the system are appropriately controlled in the presence of large disturbances, as long as the propellant engine on mode is addressed to complete the maneuvers in the predefined space mission. The novelty of this research with respect to state-of-the-art materials in this filed is briefly taken in the unique system’s integration and its investigated outcomes. The aforementioned ones are finally considered with regard to some measurable techniques in a number of different cases to indicate that the proposed control approach is well resulted, tangibly.