Development experience of the attitude control system using single-axis control moment gyros for long-term orbiting space stations

Branets, V. N.; Weinberg, D.M.; Verestchagin, V.P.; Danilov-Nitusov, N.; Legostayev, V.P.; Platonov, V. N.; Semyonov, Yu.P.; Semyachkin, V.S.; Chertock, B.E.; Sheremetyevsky, N.N.

doi:10.1016/0094-5765(88)90091-4

Cited by 22 publications

(6 citation statements)

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“…Various problems, advantages and disadvantages in different choices, associated with the design of a space station control system are discussed in [58]. Singh [46,59] presented an approach to the three-axis attitude control of a spacecraft-beam-tip body system, based on invertibility results.…”

Section: A Literature Review For the Attitude Control Problemmentioning

confidence: 99%

Neuro-genetic adaptive attitude control

Dracopoulos

Jones

1994

Neural Comput & Applic

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Section: A Literature Review For the Attitude Control Problemmentioning

confidence: 99%

Neuro-genetic adaptive attitude control

Dracopoulos

Jones

1994

Neural Comput & Applic

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“…One alternative to generating an external torque is to modify the angular momentum of some part(s) of the spacecraft, imparting motion for the entire system whilst maintaining conservation of the angular momentum. Control moment gyroscopes [30] are an example of such a system. Gyros use a relationship called a steering law [31][32][33][34][35][36] to calculate gyro commands for designed changes in angular momentum (torque commands generated by attitude controllers to accomplish a desired maneuver).…”

Section: Introductionmentioning

confidence: 99%

Non-Symmetric Gyroscope Skewed Pyramids

et al. 2019

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The novel contribution in this manuscript is an expansion of the current state-of-the-art in the geometric installation of control moment gyroscopes beyond the benchmark symmetric skewed arrays and the four asymmetric arrays presented in recent literature. The benchmark pyramid symmetrically skewed at 54.73 degrees mandates significant attention to singularity avoidance, escape, and penetration, while the most recent four asymmetric arrays are strictly useful in instances where space is available to mount at least one gyro orthogonal to the others. Skewed arrays of gyros and the research-benchmark are introduced, followed by the present-day box-90 and “roof” configurations, where the roof configuration is the first prevalently used asymmetric geometry. Six other asymmetric options in the most recent literature are introduced, where four of the six options are obviously quite useful. From this inspiration, several dozen discrete options for asymmetric installations are critically evaluated using two figures of merit: maximum momentum (saturation) and maximum singularity-free momentum. Furthermore, continuous surface plots are presented to provide readers with countless (infinite) options for geometric installations. The manuscript firmly establishes many useful options for engineers who learn that the physical space on their spacecraft is insufficient to permit standard installations.

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“…Therefore, SGCMG has been widely used as the actuator for attitude control system of large-scale spacecraft, such as the Sport-5 of France, the MIR of the Former Soviet Union [1] , and so on. In recent years, a class of smaller satellites which is required to execute rapidly attitude maneuver missions, for instance, the Pl iades and the BilSat, etc.…”

Section: Introductionmentioning

confidence: 99%

Steering laws analysis of SGCMGs based on singular value decomposition theory

Zhang

2008

Appl. Math. Mech.-Engl. Ed.

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The steering laws of single gimbal control moment gyros (SGCMGs) are analyzed and compared in this paper for a spacecraft attitude control system based on singular value decomposition (SVD) theory. The mechanism of steering laws escaping singularity, especially how the steering laws affect singularity of gimbal configuration and the output torque error, is studied using SVD theory. Performance of various steering laws are analyzed and compared quantitatively by simulation. The obtained results can be used as a reference for designers.

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Development experience of the attitude control system using single-axis control moment gyros for long-term orbiting space stations

Cited by 22 publications

References 0 publications

Neuro-genetic adaptive attitude control

Neuro-genetic adaptive attitude control

Non-Symmetric Gyroscope Skewed Pyramids

Steering laws analysis of SGCMGs based on singular value decomposition theory

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