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Attitude Determination Of Passively Magnetically Stabilized Nano Satellites
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Book Synopsis Attitude Determination of Passively Magnetically Stabilized Nano Satellites by : Roland Burton
Download or read book Attitude Determination of Passively Magnetically Stabilized Nano Satellites written by Roland Burton and published by . This book was released on 2013 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The work in this thesis enables attitude determination to be performed on passively magnetically stabilized nano satellites using only a measurement of the solar vector. Existing state of the art methods can achieve an accuracy of one degree using a full attitude sensor suite. The methods presented in this thesis achieve an accuracy of five degrees at a reduced mass and power cost, opening up new mission opportunities for nano satellites and providing a backup capability for existing designs. Two approaches to attitude determination are presented. Firstly, a batch algorithm is described that simultaneously estimates both satellite attitude and unknown parameters in the satellite's attitude dynamics model. Secondly, an online attitude determination capability is developed by extending the commonly employed multiplicative extended Kalman filter (MEKF) for situations where no gyros are present. Both approaches were applied to actual flight data from NASA's O/OREOS and the University of Michigan's RAX-1 nano satellites and results verified against independent data.
Book Synopsis A flexible attitude control system for three-axis stabilized nanosatellites by : Gordon, Karsten
Download or read book A flexible attitude control system for three-axis stabilized nanosatellites written by Gordon, Karsten and published by Universitätsverlag der TU Berlin. This book was released on 2018-03-15 with total page 197 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis investigates a new concept for the flexible design and verification of an ADCS for a nanosatellite platform. In order to investigate guidelines for the design of a flexible ADCS, observations of the satellite market and missions are recorded. Following these observations, the author formulates design criteria which serve as a reference for the conceptual design of the flexible ADCS. The research of the thesis was carried out during the development of TU Berlin's nanosatellite platform TUBiX20 and its first two missions, TechnoSat and TUBIN. TUBiX20 targets modularity, reuse and dependability as main design goals. Based on the analysis of design criteria for a flexible ADCS, these key design considerations for the TUBiX20 platform were continued for the investigations carried out in this thesis. The resulting concept implements the ADCS as a distributed system of devices complemented by a hardware-independent core application for state determination and control. Drawing on the technique of component-based software engineering, the system is partitioned into self-contained modules which implement unified interfaces. These interfaces specify the state quantity of an input or output but also its unit and coordinate system, complemented by a mathematical symbol for unambiguous documentation. The design and verification process for the TUBiX20 ADCS was also elaborated during the course of this research. The approach targets the gradual development of the subsystem from a purely virtual satellite within a closed-loop simulation to the verification of the fully integrated system on an air-bearing testbed. Finally, the concurrent realization of the investigated concept within the TechnoSat and TUBIN missions is discussed. Starting with the individual ADCS requirements, the scalability of the approach is demonstrated in three stages: from a coarse, but cost- and energy-efficient configuration to realize a technology demonstration mission with moderate requirements (TechnoSat) to a high-performance configuration to support Earth observation missions (TUBIN). Diese Dissertation untersucht ein neues Konzept zur flexiblen Entwicklung und Verifikation eines Lageregelungssystems für eine Nanosatellitenplattform. Als Grundlage für die Erarbeitung eines Leitfadens für die Entwicklung werden zunächst Beobachtung des Satellitenmarkts sowie konkreter Missionen zusammengetragen. Darauf aufbauend formuliert der Autor Entwurfskriterien für die Konzipierung eines flexiblen Lageregelungssystems. Die Dissertation wurde im Rahmen der Entwicklung der TUBiX20 Nanosatellitenplattform und ihrer ersten beiden Missionen, TechnoSat und TUBIN, an der TU Berlin durchgeführt. TUBiX20 verfolgt Modularität, Wiederverwendung und Zuverlässigkeit als Entwicklungsziele. Diese werden unter der Verwendung der vom Autor hergeleiteten Entwurfskriterien in dieser Arbeit im Kontext des Lageregelungssystems verfeinert. Das resultierende Konzept setzt dieses als verteiltes System von Geräten und einem hardware-unabhängigen Software-Kern um. Der Software-Entwurfstechnik Component-based software engineering folgend ist das System in unabhängige Module unterteilt, welche wiederum einheitliche Schnittstellen implementieren. Diese Schnittstellen spezifizieren die Zustandsgrößen für die Ein- und Ausgänge der Module inklusive Einheit, Koordinatensystem und mathematischem Symbol für eine eindeutige Darstellung. Der Entwurfs- und Verifikationsprozess für das TUBiX20 Lageregelungssystem wurde vom Autor im Rahmen der Arbeit untersucht. Hier verfolgt der Ansatz einen schrittweisen übergang von einem virtuellen Satelliten als Simulationsmodell bis hin zur Verifikation des integrierten Systems auf einem Lageregelungsteststand. Abschließend diskutiert die Arbeit die Realisierung des untersuchten Konzepts im Rahmen der Missionen TechnoSat und TUBIN. Beginnend mit den jeweiligen Anforderungen wird die Skalierbarkeit des Ansatzes in drei Stufen demonstriert: von einer groben, aber kosten- und energieeffizienten Konfiguration für eine Technologieerprobungsmission mit moderaten Anforderungen (TechnoSat) bis hin zu einer Konfiguration für hochgenaue Lageregelung als Basis für Erdbeobachtungsmissionen (TUBIN).
Book Synopsis Design and Testing of Three-axis Satellite Attitude Determination and Stabilization Systems that are Based on Magnetic Sensing and Actuation by : Mark L. Psiaki
Download or read book Design and Testing of Three-axis Satellite Attitude Determination and Stabilization Systems that are Based on Magnetic Sensing and Actuation written by Mark L. Psiaki and published by . This book was released on 2002 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fault Tolerant Attitude Estimation for Small Satellites by : Chingiz Hajiyev
Download or read book Fault Tolerant Attitude Estimation for Small Satellites written by Chingiz Hajiyev and published by CRC Press. This book was released on 2020-12-22 with total page 353 pages. Available in PDF, EPUB and Kindle. Book excerpt: Small satellites use commercial off-the-shelf sensors and actuators for attitude determination and control (ADC) to reduce the cost. These sensors and actuators are usually not as robust as the available, more expensive, space-proven equipment. As a result, the ADC system of small satellites is more vulnerable to any fault compared to a system for larger competitors. This book aims to present useful solutions for fault tolerance in ADC systems of small satellites. The contents of the book can be divided into two categories: fault tolerant attitude filtering algorithms for small satellites and sensor calibration methods to compensate the sensor errors. MATLAB® will be used to demonstrate simulations. Presents fault tolerant attitude estimation algorithms for small satellites with an emphasis on algorithms’ practicability and applicability Incorporates fundamental knowledge about the attitude determination methods at large Discusses comprehensive information about attitude sensors for small satellites Reviews calibration algorithms for small satellite magnetometers with simulated examples Supports theory with MATLAB simulation results which can be easily understood by individuals without a comprehensive background in this field Covers up-to-date discussions for small satellite attitude systems design Dr. Chingiz Hajiyev is a professor at the Faculty of Aeronautics and Astronautics, Istanbul Technical University (Istanbul, Turkey). Dr. Halil Ersin Soken is an assistant professor at the Aerospace Engineering Department, Middle East Technical University (Ankara, Turkey).
Book Synopsis Estimation and Prediction of the Attitude of a Passive Gravity-stabilized Satellite by : Bruce E. Tinling
Download or read book Estimation and Prediction of the Attitude of a Passive Gravity-stabilized Satellite written by Bruce E. Tinling and published by . This book was released on 1969 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Method for predicting attitude of passive gravity stabilized satellite.
Book Synopsis Attitude Stablization for CubeSat by : Mohammed Chessab Mahdi
Download or read book Attitude Stablization for CubeSat written by Mohammed Chessab Mahdi and published by . This book was released on 2018 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book explores CubeSat technology, and develops a nonlinear mathematical model of a spacecraft with the assumption that the satellite is a rigid body. It places emphasis on the CubeSat subsystem, orbit dynamics and perturbations, the satellite attitude dynamic and modeling, and components of attitude determination and the control subsystem. The book focuses on the attitude stabilization methods of spacecraft, and presents gravity gradient stabilization, aerodynamic stabilization, and permanent magnets stabilization as passive stabilization methods, and spin stabilization and three axis stabilization as active stabilization methods. It also discusses the need to develop a control system design, and describes the design of three controller configurations, namely the ProportionalIntegralDerivative Controller (PID), the Linear Quadratic Regulator (LQR), and the Fuzzy Logic Controller (FLC) and how they can be used to design the attitude control of CubeSat three-axis stabilization. Furthermore, it presents the design of a suitable attitude stabilization system by combining gravity gradient stabilization with magnetic torquing, and the design of magnetic coils which can be added in order to improve the accuracy of attitude stabilization. The book then investigates, simulates, and compares possible controller configurations that can be used to control the currents of magnetic coils when magnetic coils behave as the actuator of the system.
Book Synopsis Advances in Aerospace Guidance, Navigation and Control by : Joël Bordeneuve-Guibé
Download or read book Advances in Aerospace Guidance, Navigation and Control written by Joël Bordeneuve-Guibé and published by Springer. This book was released on 2015-04-04 with total page 730 pages. Available in PDF, EPUB and Kindle. Book excerpt: The two first CEAS (Council of European Aerospace Societies) Specialist Conferences on Guidance, Navigation and Control (CEAS EuroGNC) were held in Munich, Germany in 2011 and in Delft, The Netherlands in 2013. ONERA The French Aerospace Lab, ISAE (Institut Supérieur de l’Aéronautique et de l’Espace) and ENAC (Ecole Nationale de l’Aviation Civile) accepted the challenge of jointly organizing the 3rd edition. The conference aims at promoting new advances in aerospace GNC theory and technologies for enhancing safety, survivability, efficiency, performance, autonomy and intelligence of aerospace systems. It represents a unique forum for communication and information exchange between specialists in the fields of GNC systems design and operation, including air traffic management. This book contains the forty best papers and gives an interesting snapshot of the latest advances over the following topics: l Control theory, analysis, and design l Novel navigation, estimation, and tracking methods l Aircraft, spacecraft, missile and UAV guidance, navigation, and control l Flight testing and experimental results l Intelligent control in aerospace applications l Aerospace robotics and unmanned/autonomous systems l Sensor systems for guidance, navigation and control l Guidance, navigation, and control concepts in air traffic control systems For the 3rd CEAS Specialist Conference on Guidance, Navigation and Control the International Program Committee conducted a formal review process. Each paper was reviewed in compliance with standard journal practice by at least two independent and anonymous reviewers. The papers published in this book were selected from the conference proceedings based on the results and recommendations from the reviewers.
Book Synopsis Attitude Determination and Control of Nano-Satellites by : John G. Warner
Download or read book Attitude Determination and Control of Nano-Satellites written by John G. Warner and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The University of Illinois's IlliniSat2 satellite bus is unique in that it is among only a few nano-satellites that implements three-axis, onboard attitude determination and control. Though this is an ambitious goal, it will allow for a wide range of scientific missions to be accomplished on this bus. To complete the system, an accurate attitude determination system needs to be developed. Several methods for determining the attitude state as well as mitigating system noise are explored. In particular, an extended Kalman lter is developed to obtain accurate angular rate information from noisy rate measurements. These rate measurements may be provided by either rate gyros or by successive vector measurements. A linear Kalman lter is developed to obtain an accurate attitude estimate. The attitude may be measured with two vector measurements via the TRIAD algorithm, while sensor noise may be rejected via the lter. Using these techniques the requirements for an e ective attitude determination and control system are met.
Book Synopsis Four Methods of Attitude Determination for Spin-stabilized Spacecraft with Applications and Comparative Results by : Gene A. Smith
Download or read book Four Methods of Attitude Determination for Spin-stabilized Spacecraft with Applications and Comparative Results written by Gene A. Smith and published by . This book was released on 1975 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Spacecraft Attitude Determination and Control by : J.R. Wertz
Download or read book Spacecraft Attitude Determination and Control written by J.R. Wertz and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 877 pages. Available in PDF, EPUB and Kindle. Book excerpt: Roger D. Werking Head, Attitude Determination and Control Section National Aeronautics and Space Administration/ Goddard Space Flight Center Extensiye work has been done for many years in the areas of attitude determination, attitude prediction, and attitude control. During this time, it has been difficult to obtain reference material that provided a comprehensive overview of attitude support activities. This lack of reference material has made it difficult for those not intimately involved in attitude functions to become acquainted with the ideas and activities which are essential to understanding the various aspects of spacecraft attitude support. As a result, I felt the need for a document which could be used by a variety of persons to obtain an understanding of the work which has been done in support of spacecraft attitude objectives. It is believed that this book, prepared by the Computer Sciences Corporation under the able direction of Dr. James Wertz, provides this type of reference. This book can serve as a reference for individuals involved in mission planning, attitude determination, and attitude dynamics; an introductory textbook for stu dents and professionals starting in this field; an information source for experimen ters or others involved in spacecraft-related work who need information on spacecraft orientation and how it is determined, but who have neither the time nor the resources to pursue the varied literature on this subject; and a tool for encouraging those who could expand this discipline to do so, because much remains to be done to satisfy future needs.
Book Synopsis Design and Simulation of a Nano-satellite Attitude Determination System by :
Download or read book Design and Simulation of a Nano-satellite Attitude Determination System written by and published by . This book was released on 2009 with total page 129 pages. Available in PDF, EPUB and Kindle. Book excerpt: Earth imaging satellites have typically been large systems with highly accurate and expensive sensors. With the recent push for Operationally Responsive Space, Earth imaging has potentially achievable with small and reletively inexpensive satellites. This has led to the research currently underway to develop very small, low-cost imaging satellites that can produce useful Operational-level and Tactical-level imagery products. This thesis contributes to that effort by developing a detailed design for the attitude determination for a tactically useful earth-imaging nano-satellite. Tactical Imaging Nano-sat Yielding Small-Cost Operations and Persistent Earth-coverage (TINYSCOPE) is an ongoing investigation at NPS, concerning using a nano-satellite, based on the CubeSat standard, to achieve Earth imaging from LEO orbit. A detailed design of the attitude determination system includes sensor selection ahd characterization, as well as high fidelity simulation via MATLAB/Simulink. The attitude determination system is based on an Extended Kalman Filter using multiple sensor types and data rates. The sensors include a star tracker, sun sensor, gyroscope and magnetometer.
Book Synopsis Attitude Determination and Control Hardware Development for Small Satellites by : Marc Fournier
Download or read book Attitude Determination and Control Hardware Development for Small Satellites written by Marc Fournier and published by . This book was released on 2011 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt: The development of a small spacecraft attitude determination and control subsystem is described. This subsystem is part of The Space Flight Laboratory's Generic Nanosatellite Bus. With a 20cm3 body, the bus has an attitude determination and control subsystem capable of full three-axis stabilization and control enabling more advanced missions previously only possible with bulkier and more power-consuming attitude control hardware. Specific contributions to the Space Flight Lab's attitude control hardware are emphasised. Particularly, the full development of a 32g three-axis nanosatellite rate sensing unit is described. This includes embedded software development, skew calibration, hardware modeling and qualification testing for the unit. Development work on a three-axis boom-mounted magnetometer is also detailed. A full hardware design is also described for a new microsatellite-sized rate sensor. Larger and more powerful than the nanosatellite rate sensors, the design ensures a low noise, low drift architecture to improve attitude determination on future microsatellite missions.
Book Synopsis Magnetic Attitude and Spin Control of the Small Scientific Satellite S3-A by : Thomas W. Flatley
Download or read book Magnetic Attitude and Spin Control of the Small Scientific Satellite S3-A written by Thomas W. Flatley and published by . This book was released on 1970 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Magnetic attitude and spin control of small scientific satellite.
Book Synopsis Attitude Determination of Triad and TIP-II and -III Gravity-Gradient-Stabilized Satellites by : C. E. Williams
Download or read book Attitude Determination of Triad and TIP-II and -III Gravity-Gradient-Stabilized Satellites written by C. E. Williams and published by . This book was released on 1977 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: The attitude of a satellite refers to the rotational orientation of the spacecraft relative to some reference triad of Cartesian axes (these being, for the type of spacecraft treated here, the orbit radius vector, the normal-to-the-orbit plane, and the vector cross product of the two). Mathematically, the attitude is usually represented by nine direction cosines and/or three Euler angles. The numerical determination of these parameters is the objective of attitude estimation. Various schemes have been developed and used by the Applied Physical Laboratory to determine the attitude performance of its satellites. In recent years, a least-squares technique that involves eigenvalue and eigenvector computation has been added. This report presents the formulation of the technique and discusses its successful application. Attitude estimation results from three orbiting spacecraft are included. (Author).
Book Synopsis Attitude Determination and Control System Design and Implementation for a 6U CubeSat Proximity Operations Mission by : Francisco J. Franquiz
Download or read book Attitude Determination and Control System Design and Implementation for a 6U CubeSat Proximity Operations Mission written by Francisco J. Franquiz and published by . This book was released on 2015 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this work is to discuss the attitude determination and control system (ADCS) design process and implementation for a 12 kg, 6U (36.6 cm x 23.9 cm x 27.97 cm) CubeSat class nano-satellite. The design is based on the requirements and capabilities of the Application for Resident Space Object Proximity Analysis and IMAging (ARAPAIMA) proximity operations mission. The satellite is equipped with a cold gas propulsion system capable of exerting 2.5 mN m torques in both directions about each body axis. The attitude sensors include an angular rate gyro and star tracker (STR), supplemented by the payload optical array cameras. The dynamic simulation of the satellite includes extensive environmental models and analyses that show how the satellite attitude is affected by aerodynamic drag, solar radiation pressure, gravity gradient torques, and residual magnetic moments. A mechanical propellant slosh model and a reaction torque analysis of the deployable solar panel hinges approximate the internal dynamics of the satellite. A trade study is presented to justify the use of a reaction control thruster actuated system over the more traditional reaction wheel configuration. Both actuation systems are modeled to hardware specifications and their propellant and energy requirements are examined alongside pointing performance. Two methods of accounting for sensor noise and sampling rates are presented. The first is an extended Kalman filter based on the nonlinear model of a rate gyro coupled with quaternion attitude kinematics. The second presents a gyro-less angular rate observer capable of extrapolating STR measurements to the desired frequency. An additional method uses images from the payload cameras to perform [camera] frame centering maneuvers and to address the possibility of bias in the controller reference signal. Four different controllers are described to reflect the chronological progression of the ADCS design. The first controller, designed to perform long angle maneuvers and target tracking, utilizes fixed gain eigenaxis control. The same controller is then augmented with a parallel proportional-integral-derivative (PID) type control law using scheduled gains. This configuration is designed to switch between eigenaxis and PID control during imaging procedures to take advantage of the integral control introduced by the PID algorithm. To reduce system complexity, a modified eigenaxis control law, which incorporates scheduled integral control but does not require a switch to PID control, is introduced. A discrete time equivalent of the modified eigenaxis control law is also developed. Additionally, a brief description of a detumbling control law is presented. Each of the four control laws is paired and tested with the different feedback and estimation methods discussed. An extensive showcase of numerical simulation results outlines the pointing performance of each system configuration and evaluates their capabilities of meeting a 1 arcmin pointing requirement. A comparison of the different properties and performance of each control system configuration precedes the selection of the discrete modified eigenaxis control law as the best alternative.
Book Synopsis Analysis of a Magnetic Three-Axis Stabilized Attitude Control System for the NPSAT1 Spacecraft by : Todd A. Zirkle
Download or read book Analysis of a Magnetic Three-Axis Stabilized Attitude Control System for the NPSAT1 Spacecraft written by Todd A. Zirkle and published by . This book was released on 2001-09 with total page 111 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NPSAT1 satellite uses an active magnetic torque rod system, with a magnetometer for attitude determination, to maintain 3-axis stabilization, with a slightly gravity gradient friendly structure, This thesis will examine the performance of three combinations of programs and simulation models for the NPSAT1 satellite attitude control system. The models include a magnetic control law with a reduced order estimator to generate torque commands to achieve spacecraft nadir pointing and a magnetic rate (Bdot) control law to reduce spacecraft angular rates. The performances of two Bdot mode switching designs are compared Also, a case is made for the benefits of performing the system's reduced estimator prior to mode switching. All of the control methods analyzed appear to be valid control methods to achieve three-axis attitude stabilization using only magnetic torquers for active control. The most efficient control method analyzed incorporates a hand-off method from a magnetic rate (Bdot) control loop to a magnetic control loop. The results of this analysis indicates that the best use of this method is to perform the Bdot hand-off following the achievement of a predetermined combined angular rate.
Book Synopsis Satellite Attitude Control Utilizing the Earth's Magnetic Field by : John S. White (writer on artificial satellites.)
Download or read book Satellite Attitude Control Utilizing the Earth's Magnetic Field written by John S. White (writer on artificial satellites.) and published by . This book was released on 1961 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
