Design and simulation of a three-axis stabilized satellite and Kalman filter rate estimator
Approved for public release; distribution is unlimited === Design requirements for a small satellite (NPSAT-1) Attitude Determination and Control Subsystem (ADCS) is a three-axis stabilized spacecraft which requires a control attitude of +/- 1.0 degrees and knowledge attitude of +/- 0.1 degree. Seve...
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ndltd-nps.edu-oai-calhoun.nps.edu-10945-8882017-05-24T16:06:36Z Design and simulation of a three-axis stabilized satellite and Kalman filter rate estimator Vitalich, John Titus, Hal A. Agrawal, Brij N. Electrical Engineering Kalman filtering Artificial satellites Attitude control systems Space vehicles Gyroscopes Approved for public release; distribution is unlimited Design requirements for a small satellite (NPSAT-1) Attitude Determination and Control Subsystem (ADCS) is a three-axis stabilized spacecraft which requires a control attitude of +/- 1.0 degrees and knowledge attitude of +/- 0.1 degree. Several design aspects are considered in development of attitude control systems for a small satellite, such as: spacecraft dynamics, space environment, disturbance torques, orbit type, and spacecraft complexity. The ideal spacecraft's attitude sensor is a rate gyroscope, which provides rate information to the attitude control system. In the case of NPSAT-1, due to budget constraints alternative sensors will be utilized, such as: a three-axis magnetometer, earth sensors, and a Global Positioning System (GPS). A small satellite designed to have a three-axis stabilized, biased momentum system, must have a robust control system and requires a momentum wheel to provide stiffness to maintain attitude, and magnetic torque rods on each axis. The current design of NPSAT-1 uses all of these sensors to provide rate information for damping and stability to the control system that requires a complicated attitude control design. The purpose of this attitude control design simulation is to investigate and propose a control law utilizing a single pitch momentum wheel and three magnetic torque rods. A further proposal is to utilize a constant speed momentum wheel to avoid momentum damping and over speed, replace the pitch control with magnetic torquers, and develop a Kalman filter estimator to provide all the required angular rates. Lieutenant Commander, United States Navy 2012-03-14T17:29:51Z 2012-03-14T17:29:51Z 2003-06 Thesis http://hdl.handle.net/10945/888 This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted. xxii, 91 p. : ill. (some col.) ; application/pdf Monterey, California. Naval Postgraduate School |
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Kalman filtering Artificial satellites Attitude control systems Space vehicles Gyroscopes |
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Kalman filtering Artificial satellites Attitude control systems Space vehicles Gyroscopes Vitalich, John Design and simulation of a three-axis stabilized satellite and Kalman filter rate estimator |
description |
Approved for public release; distribution is unlimited === Design requirements for a small satellite (NPSAT-1) Attitude Determination and Control Subsystem (ADCS) is a three-axis stabilized spacecraft which requires a control attitude of +/- 1.0 degrees and knowledge attitude of +/- 0.1 degree. Several design aspects are considered in development of attitude control systems for a small satellite, such as: spacecraft dynamics, space environment, disturbance torques, orbit type, and spacecraft complexity. The ideal spacecraft's attitude sensor is a rate gyroscope, which provides rate information to the attitude control system. In the case of NPSAT-1, due to budget constraints alternative sensors will be utilized, such as: a three-axis magnetometer, earth sensors, and a Global Positioning System (GPS). A small satellite designed to have a three-axis stabilized, biased momentum system, must have a robust control system and requires a momentum wheel to provide stiffness to maintain attitude, and magnetic torque rods on each axis. The current design of NPSAT-1 uses all of these sensors to provide rate information for damping and stability to the control system that requires a complicated attitude control design. The purpose of this attitude control design simulation is to investigate and propose a control law utilizing a single pitch momentum wheel and three magnetic torque rods. A further proposal is to utilize a constant speed momentum wheel to avoid momentum damping and over speed, replace the pitch control with magnetic torquers, and develop a Kalman filter estimator to provide all the required angular rates. === Lieutenant Commander, United States Navy |
author2 |
Titus, Hal A. |
author_facet |
Titus, Hal A. Vitalich, John |
author |
Vitalich, John |
author_sort |
Vitalich, John |
title |
Design and simulation of a three-axis stabilized satellite and Kalman filter rate estimator |
title_short |
Design and simulation of a three-axis stabilized satellite and Kalman filter rate estimator |
title_full |
Design and simulation of a three-axis stabilized satellite and Kalman filter rate estimator |
title_fullStr |
Design and simulation of a three-axis stabilized satellite and Kalman filter rate estimator |
title_full_unstemmed |
Design and simulation of a three-axis stabilized satellite and Kalman filter rate estimator |
title_sort |
design and simulation of a three-axis stabilized satellite and kalman filter rate estimator |
publisher |
Monterey, California. Naval Postgraduate School |
publishDate |
2012 |
url |
http://hdl.handle.net/10945/888 |
work_keys_str_mv |
AT vitalichjohn designandsimulationofathreeaxisstabilizedsatelliteandkalmanfilterrateestimator |
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1718452464337813504 |