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. 2024 Sep 16;15(9):1159. doi: 10.3390/mi15091159

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© 2024 by the authors.

Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https://creativecommons.org/licenses/by/4.0/).

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Dynamic characteristics of the system in Figure 9 for an actuator with N = 2 DGMSCMGs in parallel configuration: (a) the components of the satellite’s relative angular rate vectors, of the error relative angular rate vectors and of the absolute angular rate vectors; (b) satellite’s attitude with respect to the local orbital frame; (c) the Euler angles; (d) components of the torque vectors; (e) angular rates applied to the gimbals of the actuator-type DGMSCMG; (f) dynamic characteristics of the models of both actuator’s DGMSCMGs; (g) dynamic characteristics of the DGMSCMG 3 gyro sensor; (h) dynamic characteristics of the DGMSCMG 3 gyro sensor.

Dynamic characteristics of the system in Figure 9 for an actuator with N = 2 DGMSCMGs in parallel configuration: (a) the components of the satellite’s relative angular rate vectors, of the error relative angular rate vectors and of the absolute angular rate vectors; (b) satellite’s attitude with respect to the local orbital frame; (c) the Euler angles; (d) components of the torque vectors; (e) angular rates applied to the gimbals of the actuator-type DGMSCMG; (f) dynamic characteristics of the models of both actuator’s DGMSCMGs; (g) dynamic characteristics of the DGMSCMG 3 gyro sensor; (h) dynamic characteristics of the DGMSCMG 3 gyro sensor.