Nutation control strategy through state feedback: application to a spin-stabilized autonomous system
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ORIGINAL RESEARCH
Nutation control strategy through state feedback: application to a spin-stabilized autonomous system A. H. Mazinan1
Received: 13 December 2019 / Accepted: 29 June 2020 Ó Bharati Vidyapeeth’s Institute of Computer Applications and Management 2020
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 spinstabilized 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.
& A. H. Mazinan [email protected]; [email protected] 1
Department of Control Engineering, Faculty of Electrical Engineering, South Tehran Branch, Islamic Azad University (IAU), No. 209, North Iranshahr St., P.O. Box 11365/4435, Tehran, Iran
Keywords Spin-stabilized autonomous system Nutation control strategy State feedback Parameter’s uncertainties External disturbances
1 Introduction A large number of potential investigations in the area of attitude maneuvers control via spin-stabilized technique with its application to spacecraft are now made. Prior to illustrating the contribution of the present research, in the clear form, the recent background of the aforementioned topics are briefly considered with a focus on the spin-stabilized control in connection with the space attitude maneuvers through the proceeding paragraphs. With this purpose, the solid fundamental information in the area of spacecraft dynamics and control is first presented [1]. Subsequently, the detumbling and nutation canceling maneuvers under complete analytic reduction regarding the axially symmetric spacecraft and also the spin up problem and accelerating convergence in the steady state are proposed [2, 3]. The nonlinear optimal control of spacecraft to be approached the tumbling targe
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