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Dissertations / Theses on the topic 'Attitude determination'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Bejeryd, Johan. "GPS-based attitude determination." Thesis, Linköping University, Department of Electrical Engineering, 2007. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-11029.

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<p>Inertial sensors and magnetometers are often used for attitude determination of moving platforms. This thesis treats an alternative method; GPS-based attitude determination. By using several GPS-antennas, and with carrier phase measurements determining the relative distance between them, the attitude can be calculated.</p><p>Algorithms have been implemented in Matlab and tested on real data. Two commercial GPS-based attitude determination systems have also been tested on a mobile platform and compared to a navigation grade Inertial Navigation System (INS). The results from the tests show th

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2

Thorstensson, Erika. "GPS based attitude determination." Thesis, Linköpings universitet, Institutionen för teknik och naturvetenskap, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-94447.

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This paper is the result of a masters thesis performed at Linköping University for Saab Bofors Dynamics in Linköping, Sweden. Attitude is defined as the orientation of a coordinate frame in reference to another coordinate frame. This is often referred to as three consecutive rotations, called roll, pitch and yaw (or heading). Attitude determination is generally performed using inertial navigation systems composed of gyros and accelerometers. These systems are highly accurate but are very expensive and experience a drift when used for a long period of time. The global positioning system, or GPS

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3

Hollensteiner, Erwin. "Drilling attitude determination and control." Thesis, University of Nottingham, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.555799.

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This thesis is concerned with the development of a new robust and efficient real time signal processing algorithm for a rotating strapdown inertial navigation system (INS). Although the signal processing in INS is dominated by the Kalman filter algorithm, often this algorithm is not feasible for small microcontroller or digital signal processor (DSP) applications. This thesis develops a new fixed point DSP algorithm for cal- culating the optimal estimate of orientation of the INS. In this thesis Kalman filter algorithms in INS are discussed. A filter algorithm for a rotating inertial navigatio

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4

Jacquemont, Christian M. (Christian Marie) 1972. "Aircraft attitude determination using robust estimation." Thesis, Massachusetts Institute of Technology, 1997. http://hdl.handle.net/1721.1/10202.

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5

Arrigo, Jeanette Fay Freauf. "Improved VLSI architecture for attitude determination computations." Connect to a 24 p. preview or request complete full text in PDF format. Access restricted to UC campuses, 2006. http://wwwlib.umi.com/cr/ucsd/fullcit?p3195257.

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Thesis (Ph. D.)--University of California, San Diego, 2006.<br>Title from first page of PDF file (viewed February 28, 2006). Available via ProQuest Digital Dissertations. Vita. Includes bibliographical references.

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6

Kaplan, Ceren. "Leo Satellites: Attitude Determination And Control Components." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/12607189/index.pdf.

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In this thesis, application of linear control methods to control the attitude of a Low-Earth Orbit satellite is studied. Attitude control subsystem is first introduced by explaining attitude determination and control components in detail. Satellite dynamic equations are derived and linearized for controller design. Linear controller and linear quadratic regulator are chosen as controllers for attitude control. The actuators used for control are reaction wheels and magnetic torquers. MATLAB-SIMULINK program is used in order to simulate satellite dynamical model (actual nonlinear model) and con

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7

Thorstenson, Stefan. "IMU-based enhancement of GPS attitude determination." Thesis, Linköpings universitet, Reglerteknik, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-79930.

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GPS carrier-phase measurements from two GPS antennas can be used to calculate the heading of the baseline that can be drawn between the two antennas. An integer ambiguity problem has to be solved, and the system is called GPS attitude determination (GPSAD). This way of calculating the heading is cheaper than the traditional ways to do it, but it requires GPS reception. This thesis investigates how and if an inertial measurement unit (IMU) can support the GPS-based system, and divides the question into four problems: heading estimate during GPS outages, reducing the ambiguity search space, cycl

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8

De, Ruiter Anton. "Nonlinear state-estimation for spacecraft attitude determination." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2001. http://www.collectionscanada.ca/obj/s4/f2/dsk3/ftp04/MQ62888.pdf.

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9

Dai, Zhen [Verfasser]. "On GPS based attitude determination / Zhen Dai." Siegen : Universitätsbibliothek der Universität Siegen, 2013. http://d-nb.info/1034425951/34.

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10

Scaccia, Milena. "Numerical algorithms for attitude determination using GPS." Thesis, McGill University, 2011. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=103616.

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Attitude determination involves the estimation of the orientation of a body (usually aircraft or satellite) with respect to a known frame of reference. It has important applicationsin areas spanning navigation and communication. There exist two main approaches for determining attitude using the Global Positioning System (GPS): (1) algorithms which determine attitude via baseline estimates in two frames, and (2) algorithms which solve for attitude by incorporating the attitude parameters directly into the state. For each approach, we propose an algorithm which aims to determine attitude in an e

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11

Gupta, Rishi Vijay. "A compressive sensing algorithm for attitude determination." Thesis, Massachusetts Institute of Technology, 2011. http://hdl.handle.net/1721.1/66422.

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Thesis (M. Eng.)--Massachusetts Institute of Technology, Dept. of Electrical Engineering and Computer Science, 2011.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (p. 29-30).<br>We propose a framework for compressive sensing of images with local distinguishable objects, such as stars, and apply it to solve a problem in celestial navigation. Specifically, let x [epsilon] RN be an N-pixel image, consisting of a small number of local distinguishable objects plus noise. Our goal is to design an m x N measurement matrix A with m << N, such that we can recover an ap

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12

Bylund, Oscar. "Attitude Determination and Control of a Cubesat." Thesis, KTH, Rymdteknik, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-231376.

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This report describes the feasibility of attitude determination and control of the student satellite MIST. It investigates the stability and controllability of the satellite system, it covers attitude determination based on magnetometer and sun sensor measurements available and finally compares two controllers and the resulting pointing accuracy of the satellite. The study shows that the pointing requirements can be met under nominal circumstances.<br>I denna rapport utreds hur noggrannt en studentsatellits attityd kan uppskattas och kontrolleras. Sensorerna och aktuatorerna består av en magne

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Sabala, Ryan J. "Satellite Attitude Determination Using Laser Communication Systems." Ohio University / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1218636153.

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14

Bowen, John Arthur. "On-Board Orbit Determination and 3-Axis Attitude Determination for Picosatellite Applications." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/131.

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This thesis outlines an orbit determination and 3-axis attitude determination system for use on orbit as applicable to 1U CubeSats and other picosatellites. The constraints imposed by the CubeSat form factor led to the need for a simple configuration and relaxed accuracy requirements. To design a system within the tight mass, volume, and power constraints inherent to CubeSats, a balance between hardware complexity, software complexity and accuracy is sought. The proposed solution consists of a simple orbit propagator, magnetometers with a magnetic field look-up table, Sun sensors with an analy

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Rohde, Jan. "Kalman filter for attitude determination of student satellite." Thesis, Norwegian University of Science and Technology, Department of Engineering Cybernetics, 2007. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-8823.

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<p>In the autumn of 2006 a satellite project was started at NTNU. The goal of the project is two-folded, first it seeks to create more interest and expertise around the field of space technology, secondly to create a satellite platform which can be modified and equipped with different payloads to perform selected tasks in a Low Earth Orbit. For a satellite to be able to complete missions involving sensory and imaging, an attitude determination and control system is needed to give the satellite a stable attitude. In order to create a good attitude control system, a Gauss-Newton improved extend

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Schoonwinkel, Johannes. "Attitude determination and control system of a nanosatellite." Thesis, Link to the online version, 2007. http://hdl.handle.net/10019/708.

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17

Bamber, D. C. "Attitude determination through registration of earth observational imagery." Thesis, University of Surrey, 2008. http://epubs.surrey.ac.uk/770396/.

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With the increasing resolution of Earth observational sensors there is an increasing need for reliable, frequent and accurate attitude knowledge. Typically, high accuracy attitude systems incur large mass and costs, limiting the potential missions to which small or inexpensive satellites may apply. A neea tnererore exists tor low-mass, low-cost attitude systems capable or obtaining high accuracy attitude telemetry, especially during image capture and onboard small satellites. Towards such ends, this research investigates the potential use of a narrow stereo angle between pushbroom sensors for

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18

Maguire, Sean Thomas George. "Attitude determination using low frequency radio polarisation measurements." Thesis, University of Cambridge, 2015. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.708927.

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19

Zhou, Jiewei. "Attitude Determination and Control of the CubeSat MIST." Thesis, KTH, Farkost och flyg, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-203284.

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The ADCS concept in MIST reects the limitations of the CubeSat in terms of space, power and onboard computer computational capability. The control is constrained to the use of only magnetic torquers and the determination to magnetometers and Sun sensors in spite of the the under-actuation and underdetermination during eclipses. Usually small satellites with a similar ADCS and demanding requirements fail, therefore MIST would be a design reference for this kind of concept in the case it succeeds. The objectives of this thesis work are the feasibility assessment of the concept to meet the nomina

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20

Dever, Christopher W. (Christopher Walden) 1972. "Vehicle model-based filtering for spacecraft attitude determination." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/47801.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1998.<br>Includes bibliographical references (p. 166-170) and index.<br>This thesis investigates the use of vehicle model-based filtering for spacecraft attitude determination. Whereas traditional navigation filters typically rely only on the kinematic relations between body rate and attitude in their filter designs, the state estimator presented here expands the plant model to include rigid body effects and disturbance torques. When rate sensing gyroscope measurement error components are large, as is antici

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21

Rangel, Enger Eric. "Spacecraft attitude determination methods in an educational context." Thesis, KTH, Rymdteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-265612.

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This work has as an objective to structure the content of a course on Attitude determination methods, part of an Aerospace Engineering Master program. A selection of books, papers, theses, web sites and films was reviewed to identify the most relevant topics within the areas of Static and Dynamic Attitude Determination and the ways to present them in a educational context. Theory is presented in a simplified way and examples were gathered to illustrate the theoretical part. Finally, a discussion is carried out on the main learning goals and challenges, required time for instruction and exerci

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22

Hammer, Strand Mads Peter. "Phase detection for attitude determination In quadrotors or 'drones'." Thesis, Mittuniversitetet, Avdelningen för elektronikkonstruktion, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:miun:diva-29677.

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This thesis aims to prove that it is possible to use phase difference detection as a means of determining an objects attitude in relation to a signal source. A correlation between orientation and phase-detector output is proved, and it is concluded that with further work on algorithms and signal filtering, an attitude determination system could be made. As Quadrotors or ’drones’ are controlled by a system that could benefit by another reference system, accuracy of the phase-detector system is compared with the navigation systems currently used in drones.

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23

Travis, Henry D. "Attitude determination using Star Tracker Data with Kalman filters." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2001. http://handle.dtic.mil/100.2/ADA401577.

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Thesis (M.S. in Electrical Engineeirng)--Naval Postgraduate School, December 2001.<br>"December 2001". Thesis advisor(s): Titus, Harold A. Includes bibliographical references (p. 51-53). Also available online.

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Tønne, Karianne Knutsen. "Stability Analysis of EKF - based Attitude Determination and Control." Thesis, Norwegian University of Science and Technology, Department of Engineering Cybernetics, 2007. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-8720.

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<p>This thesis is a part of the SSETI (Student Space Exploration Technology Initiative) project, where students from several universities around Europe work together with the European Space Agency (ESA) with designing, building, testing and launching an Earth-Moon satellite orbiter (European Student Moon Orbiter (ESMO). A satellite model with reaction wheels placed in tetrahedron was deduced in a preliminary study together with an extended Kalman filter to estimate the attitude from star measurements. The stability and convergence properties of this system are studied in this thesis. Previou

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25

Waarum, Ivar-Kristian. "Stability Analysis of Nonlinear Attitude Determination and Control Systems." Thesis, Norwegian University of Science and Technology, Department of Engineering Cybernetics, 2007. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-8729.

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<p>This report describes the modelling and performance of an attitude determination and control system (ADCS) for a small satellite in lunar orbit. The focus is on stability analyses of each of the components in the system, and of the system as a whole. In connection to this, the separation principle for nonlinear systems is investigated. Central background information is presented, covering necessary rigid body dynamics and stability properties. Three different controller types are analysed and compared herein, namely a model-dependent linearizing controller, a robust controller and a standa

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26

Rinnan, Toril Bye. "Development and Comparison of Estimation Methods for Attitude Determination." Thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for teknisk kybernetikk, 2012. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-18421.

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The NTNU Test Satellite (NUTS) project, is part of the Norwegian Student Satellite programANSAT. The goal of the project is to design and launch a double CubeSat by the endof 2014. During earlier satellite projects at NTNU, solid work on design of the attitudedetermination and control for a small satellite has been done.One of the considered estimation methods for the attitude determination is the extendedquaternion estimation method (EQUEST). Further development and testing of themethod is described in this thesis. In addition to the new EQUEST method, a nonlinearobserver has been implemented

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27

Scott-Young, Stephen. "Integrated position and attitude determination for augmented reality systems /." Connect, 2004. http://eprints.unimelb.edu.au/archive/00000827.

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28

Quine, Ben. "Spacecraft guidance systems : attitude determination using star camera data." Thesis, University of Oxford, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.360417.

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29

Duncan, Stuart. "Development and exploitation of GPS attitude determination for microsatellites." Thesis, University of Surrey, 2010. http://epubs.surrey.ac.uk/804951/.

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30

Pinchin, James Thomas. "GNSS Based Attitude Determination for Small Unmanned Aerial Vehicles." Thesis, University of Canterbury. Mechanical Engineering, 2011. http://hdl.handle.net/10092/5759.

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This thesis is concerned with determining the orientation of small Unmanned Aerial Vehicles(UAVs). To make commercial use of these aircraft in aerial surveying markets their attitude needs to be determined accurately and precisely throughout a survey flight. Traditionally inertial sensors have been used on larger aircraft to estimate both position and orientation in combination with Global Navigation Satellite Systems (GNSS). High quality inertial sensors have many downsides when used on the small UAV. They are expensive, power hungry and often heavy. Inertial sensors are vulnerable to vibra

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31

Puri, Varun. "Tightly coupled GPS-gyro integration for spacecraft attitude determination." Thesis, Massachusetts Institute of Technology, 1997. http://hdl.handle.net/1721.1/50315.

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Ntsimane, M. H. (Mpho Hendrick). "The attitude determination and control systems (ADCS) task scheduler." Thesis, Stellenbosch : Stellenbosch University, 2001. http://hdl.handle.net/10019.1/52487.

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Thesis (MScEng)--University of Stellenbosch, 2001.<br>ENGLISH ABSTRACT: A new task scheduler for the Attitude Determination and Control System (ADCS) of the Stellenbosch University Satellite (SUNSAT) has been designed and tested on a personal computer. This new scheduler is capable of uploading new control tasks, or changing existing control tasks, on an individual basis. This is an improvement on the current ADCS task scheduler, where the control tasks are hard-coded in the scheduler, requiring the entire software image of the scheduler to be uploaded if a new task is to be added, or a

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33

Larsson, Lasse. "Design of spacecraft attitude determination system using MEMS sensors." Thesis, KTH, Skolan för elektro- och systemteknik (EES), 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-187663.

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The CubeProp module is a propulsion module developed by NanoSpace AB that will ﬂy on-board the MIST CubeSat in 2017. NanoSpace is interested in developing an attitude determination system for the Cube-Prop module that also can be used to measure the performance of the thrusters in space. In this thesis such a system is designed and the performance is validated through numerical simulation. A method for testing the system is also chosen. The ﬁrst step in designing the system is to perform a requirement analysis. This analysis leads to the decision of using only commercially available MEMS senso

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SUN, Tao. "Stereo vision–based navigation and attitude determination for CubeSat." Thesis, The University of Sydney, 2019. https://hdl.handle.net/2123/21578.

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Recently, vision-based navigation systems for space manipulators have attracted a number of researchers working in this field. The technique could be used to deal with several space missions, including space debris classification and cleaning, small satellite capturing, space docking and formation flying. To generate a more accurate location and attitude, this advanced technique can be combined with other navigation methods, such as inertial measurement unit or global positioning system through a Kalman filter. The stereo vision–based navigation system is presented in this thesis. After the c

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Gudmundson, Karl. "Ground Based Attitude Determination Using a SWIR Star Tracker." Thesis, Linköpings universitet, Reglerteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-158129.

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This work investigates the possibility of obtaining attitude estimates by capturing images of stars using a SWIR camera. Today, many autonomous systems rely on the measurements from a GPS to obtain accurate position and attitude estimates. However, the GPS signals are vulnerable to both jamming and spoofing, making any system reliant on only GPS signals insecure. To make the navigation systems more robust, other sensors can be added to acquire a multisensor system. One of these sensors might be a ground based SWIR star camera that is able to provide accurate attitude estimates. To investigate

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36

Park, Keun Joo. "GPS receiver self survey and attitude determination using pseudolite signals." Diss., Texas A&M University, 2004. http://hdl.handle.net/1969.1/1250.

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This dissertation explores both the estimation of various parameters from a multiple antenna GPS receiver, which is used as an attitude sensor, and attitude determination using GPS-like Pseudolite signals. To use a multiple antenna GPS receiver as an attitude sensor, parameters such as baselines, integer ambiguities, line biases, and attitude, should be resolved beforehand. Also, due to a cycle slip problem a subsystem to correct this problem should be implemented. All of these tasks are called a self survey. A new algorithm to estimate these parameters from a GPS receiver is developed usingno

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37

Mumtaz, Rafia. "Attitude Determination by Exploiting Geometric Distortions in Stero Earth Images." Thesis, University of Surrey, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.518706.

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Sheridan, Kevin Francis. "GPS based position and attitude determination for airborne remote sensing." Thesis, University College London (University of London), 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.271175.

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Sullivan, Wendy I. (Wendy Ilene). "Performance analysis of an integrated GPS/inertial attitude determination system." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/47359.

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40

Skinner, Robert Edmid. "Feasibility study of a moon sensor for satellite attitude determination." Thesis, Stellenbosch : Stellenbosch University, 2005. http://hdl.handle.net/10019.1/50356.

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Thesis (MScEng)--University of Stellenbosch, 2005.<br>ENGLISH ABSTRACT: The purpose of this study was to investigate the feasibility of a moon sensor as an alternative or supplemental sensor to supply attitude information to a satellite. The visibility of the moon was evaluated with regards to that of the sun from a satellite (i.e. the feasibility of the moon sensor is compared to that of a sun sensor). An algorithm was developed to calculate the center of the moon, regardless of phase or rotation, to offer increased accuracy of the center of the moon. The accuracy of this algorithm and

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Tuthill, Jason D. "Design and simulation of a nano-satellite attitude determination system." Thesis, Monterey, California : Naval Postgraduate School, 2009. http://edocs.nps.edu/npspubs/scholarly/theses/2009/Dec/09Dec%5FTuthill.pdf.

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Thesis (Astronautical Engineer and M.S. in Astronautical Engineering)--Naval Postgraduate School, December 2009.<br>Thesis Advisor(s): Romano, Marcello ; Woo, Hyunwook. Second Reader: Newman, James. "December 2009." Joint authors: Description based on title screen as viewed on January 27, 2010. Author(s) subject terms: Kalman filter, Attitude determination, CubeSat, Nano-satellite, IMU, Magnetometer,Star tracker, Gyroscope. Includes bibliographical references (p. 125-128). Also available in print.

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ALI, ANWAR. "Power Management, Attitude Determination and COntrol Systems of Small Satellites." Doctoral thesis, Politecnico di Torino, 2014. http://hdl.handle.net/11583/2535715.

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Satellites have always been considered to be extremely expensive and risky business, which not only requires extensive knowledge and expertise in this field but also huge budget. Primarily, this concept was based on initial development and launching cost. Secondly, it was also impossible to repair and substitute parts (this was true up to 1993: the first Hubble Space Telescope servicing mission), which makes design more tough because it requires advanced fault tolerance solutions and extreme reliability. But with the passage of time many space actors entered in this market. Low cost design te

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Keil, Elizabeth Marie. "Kalman Filter Implementation to Determine Orbit and Attitude of a Satellite in a Molniya Orbit." Thesis, Virginia Tech, 2014. http://hdl.handle.net/10919/49102.

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This thesis details the development and implementation of an attitude and orbit determining Kalman filter algorithm for a satellite in a Molniya orbit. To apply the Kalman Filter for orbit determination, the equations of motion of the two body problem were propagated using Cowell's formulation. Four types of perturbing forces were added to the propagated model in order to increase the accuracy of the orbit prediction. These four perturbing forces are Earth oblateness, atmospheric drag, lunar gravitational forces and solar radiation pressure. Two cases were studied, the first being the implemen

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Vogt, Jay D. "Attitude determination of a three-axis stabilized spacecraft using star sensors." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1999. http://handle.dtic.mil/100.2/ADA374426.

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Thesis (M.S. in Astronautical Engineering) Naval Postgraduate School, December 1999.<br>"December 1999". Thesis advisor(s): Titus, Harold A. ; Agrawal, Brij. Includes bibliographical references (p. 67). Also available online.

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Purivigraipong, S. "Study of spacecraft attitude determination from phase information of GPS signals." Thesis, University of Surrey, 2000. http://epubs.surrey.ac.uk/843145/.

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In this research study, several new algorithms are developed to achieve spacecraft attitude determination from carrier phase information of GPS (Global Positioning System) signals. The first focus is on resolving integer ambiguity in carrier phase difference measurements. A newly developed algorithm based on Gram-Schmidt Orthonormalisation (GSO) is proposed for medium length baseline observations. Using this newly developed attitude algorithm from vector observations, an instantaneous estimated attitude solution is obtained, which we call 'coarse attitude', from only four phase measurements co

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Marreiros, Joao Paulo Ramalho. "Performance analysis of GPS attitude determination in a hydrographic survey launch." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1997. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp01/MQ30020.pdf.

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Greenfield, Nathan Joseph. "Low cost range and attitude determination solution for small satellite platforms." Thesis, Montana State University, 2009. http://etd.lib.montana.edu/etd/2009/greenfield/GreenfieldN0509.pdf.

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The ability to determine the range and attitude between two satellites can be a challenging venture. It can be made more challenging when considering the use of such a system on a small satellite. Successful implementation of a small and low power range and attitude sensor could open potential doors to multiple small satellite constellations and formation flying maneuvers. After successfully demonstrating an electromagnetic docking system on a one-dimensional air track, it was determined that continued work into two and three-dimensional systems would require a more functional range and attitu

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48

Awuah-Baffour, Robert. "Investigation on kinematic determination of highway geometric characteristics by attitude GPS." Diss., Georgia Institute of Technology, 1997. http://hdl.handle.net/1853/21657.

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49

Steyn, Willem Hermanus. "A multi-mode attitude determination and control system for small satellites." Thesis, Stellenbosch : Stellenbosch University, 1995. http://hdl.handle.net/10019.1/54640.

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Thesis (PhD)--Stellenbosch University, 1995.<br>ENGLISH ABSTRACT: New advanced control techniques for attitude determination and control of small (micro) satellites are presented. The attitude sensors and actuators on small satellites are limited in accuracy and performance due to physical limitations, e.g. volume, mass and power. To enhance the application of sophisticated payloads such as high resolution imagers within these confinements, a multi-mode control approach is proposed, whereby various optimized controller functions are utilized during the orbital life of the satellite. To

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Boldu, O. Farrill Treviño Joan Jordi. "Attitude Determination and Control System of a CubeSat in Suborbital Flight." Thesis, KTH, Skolan för elektroteknik och datavetenskap (EECS), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-292503.

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Abstract:

The Bistable Boom Dynamic Deployment (B2D2) experiment aims to successfully demonstrate the deployment of a 2 meter self-deployable boom in order to offer an efficient alternative for small satellites to conduct higher quality magnetic field measurements. The boom will be placed in a free falling unit, following the CubeSat standard. To obtain reliable results from the deployment, the tumbling rate of the free falling unit must be reduced to acceptable levels. Two cameras located in the free falling unit will record the boom deployment, meaning that they will need to be pointed in the opposite

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