Satellite Attitude Control Utilizing the Earth's Magnetic Field PDF Download
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Author: John S. White (writer on artificial satellites.)
Publisher:
ISBN:
Category : Artificial satellites
Languages : en
Pages : 42
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Book Description
The torque developed by the interaction of current-carrying coils with the earth's magnetic field can be used as a means of attitude control. The degree to which the attitude of a vehicle can be maintained utilizing this torque depends on the fluctuations of the magnetic field at the satellite as the satellite orbits about the earth. Due to the nature of the torque developed only two vehicle axes can be c ntinuously controlled simultaneously. With the principle described, either a two- or three-coil system can be used to control vehicle attitude about two axes. Intermittent control about three axes can be obtained. (Author).
Author: John S. White (writer on artificial satellites.)
Publisher:
ISBN:
Category : Artificial satellites
Languages : en
Pages : 42
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Book Description
The torque developed by the interaction of current-carrying coils with the earth's magnetic field can be used as a means of attitude control. The degree to which the attitude of a vehicle can be maintained utilizing this torque depends on the fluctuations of the magnetic field at the satellite as the satellite orbits about the earth. Due to the nature of the torque developed only two vehicle axes can be c ntinuously controlled simultaneously. With the principle described, either a two- or three-coil system can be used to control vehicle attitude about two axes. Intermittent control about three axes can be obtained. (Author).
Author: R. E. TOEPFER
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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Book Description
Author: Wilfred Joseph Minkus
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Book Description
The report investigates a means of controlling the attitude of a satellite in a circular orbit about the earth by the torque due to the interaction between the earth's magnetic field and the magnetic moments produced by currents in three orthogonal coils aboard the satellite. This system has the advantage over more conventional ones in that no mass is expended in the control process. It is designed to rotate the satellite about its longitudinal axis in a minimum amount of time while limiting the deviation of this axis from the local normal to the earth. The analysis is limited to the period during which the satellite's attitude is being changed by magnetically produced torques. When these torques are not applied, gravity gradient effects act as a restoring force to align the longitudinal axis with the local normal to the earth. The method is applicable to a satellite with symmetry such that the moment of inertia about its longitudinal axis is much smaller than those about body-fixed axes lying in a plane perpendicular to it and whose moments of inertia about axes in this plane are approximately equal. The model of the earth's magnetic field that is used is a dipole with its poles located at the observed geographical positions. The control system is developed to be applicable to the general type of satellite indicated above and to all orbits except those passing close to the magnetic poles. It is then applied to a particular satellite and type of orbit of interest to RADC. (Author).
Author: Karthik G. Ganesh
Publisher:
ISBN:
Category : Artificial satellites
Languages : en
Pages : 125
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Book Description
This document describes the design, analysis of Orbit Maneuvers and Attitude Control for NanoSat class satellites, which uses an electro-magnetic force controller which was proposed by the Florida Space Institute (FSI).
Author: THOMAS TERRELL MCELROY
Publisher:
ISBN:
Category :
Languages : en
Pages : 225
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Author: V. Matthewson
Publisher:
ISBN:
Category :
Languages : en
Pages : 41
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Book Description
Author: Warren Gillespie
Publisher:
ISBN:
Category :
Languages : en
Pages : 92
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Book Description
Author: James J. Adams
Publisher:
ISBN:
Category : Artificial satellites
Languages : en
Pages : 22
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Book Description
Author:
Publisher:
ISBN:
Category : Geomagnetism
Languages : en
Pages : 44
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Book Description
Author: Nitin Seth
Publisher:
ISBN: 9780494600139
Category : Aerospace engineering
Languages : en
Pages : 82
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Book Description
The following is a study of an attitude control system (ACS) for a low earth orbit nanosatellite. Control actuation is applied using three reaction wheels and three mutually orthogonal current-driven magnetorquers which produce torques by interacting with the earth's magnetic field. Control torques are distributed amongst the actuators allowing them to work together in concert. This type of control is referred to as hybrid magnetic attitude control. To account for the nearly periodic behavior of the earth's magnetic field, control torques are assigned using periodic and optimal control theory. The primary focus is to apply the time-varying Linear Quadratic Regulator controller to test the stability and energy consumption of the ACS when reaction wheels are removed from the control law, or are simulated to be missing. Other situations studied include the effects of control saturation, introducing uncertainty in the orbital inclination, and observing performance as the number of magnetic coils is increased.
