Control Moment Gyro Gravity Stabilization

Scott, E. D.

doi:10.1016/b978-0-12-395587-6.50009-0

Cited by 9 publications

(1 citation statement)

References 1 publication

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“…The angular momentum of these gyros is of the same order of magnitude as the angular momentum of the satellite due to its rotation in orbit. A full discussion of the control moment gyro is, however, beyond the scope of this paper (ScoTT, 1964;DE LISLE, OGLETREE and HILDEBRANT, 1964). The secondary mass to damp the satellite's oscillations can also consist of one or more rigid bodies.…”

Section: Gravity-gradient Stabilizationmentioning

confidence: 99%

Attitude stabilization and control of earth satellites

Gerlach

1965

Space Sci Rev

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In this paper a survey is made of some aspects of satellite attitude stabilization and control. After a brief discussion of the equations of motion governing the satellite's behaviour, the various disturbing torques acting on a satellite in a space enviromnent are considered. Quantitative values for a hypothetical satellite are discussed. Next, attention is given to several methods of attitude stabilization and control. The analysis is based on the various means to exert torques on the satellite for control purposes. Passive methods, such as spin-stabilization and gravity-gradient stabilization, are discussed in some detail. Not only are the basic principles involved indicated, but also some quantitative values of the variables concerned are mentioned where possible.

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Section: Gravity-gradient Stabilizationmentioning

confidence: 99%

Attitude stabilization and control of earth satellites

Gerlach

1965

Space Sci Rev

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A Two-Gyro, Gravity-Gradient Satellite Attitude Control System

Lewis¹,

Zajac²

1964

Bell System Technical Journal

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This article gives the results of an analytical and numerical study of a two‐gyro, gravity‐oriented communications satellite. The principal purpose of the study was to uncover and solve the analytical problems arising in the design of passive gravity‐gradient altitude control systems. Although the study was directed at satellite orientation, it is felt that many of the techniques developed have general use in the investigation of dynamical systems. We consider both small and large motions about the desired earth‐pointing orientation. In the small‐motion study, the goal is simultaneous optimization of the transient response and the forced response to perturbations caused by orbital eccentricity, magnetic torques, solar torques, thermal rod bending, and micrometeorite impact. In the large‐motion study, we enumerate all possible equilibrium positions of the satellite and then consider initial despin after injection into orbit, inversion of the satellite from one stable equilibrium position to another by switching of gyro bias torques, and the decay of transient motions resulting from large initial angular rates. As a specific numerical example, we have treated a 300‐lb satellite in a 6000‐nm orbit, stabilized by a 60‐ft extensible rod with a 20‐lb tip mass, and by two single‐degree‐of‐freedmn gyros, each with an angular momentum of 106 cgs units. Without a detailed discussion of hardware, it is concluded that such a system, having a total weight of 50 to 75 pounds including power supply, will provide a settling time for small disturbances of less than one orbit and will hold the antenna pointing error within a few degrees.

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