subject:(Attitude AND Orbit Control)

University of Toronto

1. Ibrahim, Najmus. Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking.

Degree: 2013, University of Toronto

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Terrestrial target tracking using low Earth orbit satellites provides essential daily services and vital scientific data. In this thesis, the Attitude and Orbit Control System… (more)

Subjects/Keywords: satellite; attitude; attitude and orbit control; microsatellite; control; estimation; tracking; 0538

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APA (6^th Edition):

Ibrahim, N. (2013). Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/42965

Chicago Manual of Style (16^th Edition):

Ibrahim, Najmus. “Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking.” 2013. Masters Thesis, University of Toronto. Accessed March 07, 2021. http://hdl.handle.net/1807/42965.

MLA Handbook (7^th Edition):

Ibrahim, Najmus. “Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking.” 2013. Web. 07 Mar 2021.

Vancouver:

Ibrahim N. Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/1807/42965.

Council of Science Editors:

Ibrahim N. Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking. [Masters Thesis]. University of Toronto; 2013. Available from: http://hdl.handle.net/1807/42965

University of Toronto

2. Tarantini, Vincent. Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite.

Degree: 2012, University of Toronto

URL: http://hdl.handle.net/1807/33557

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Contributions to two missions are presented. The first is a demonstration mission called CanX-7 that uses a 4 square metre drag sail to de-orbit a… (more)

Subjects/Keywords: De-orbit; Drag sail; Thermal control; Attitude determination and control; 0538

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APA (6^th Edition):

Tarantini, V. (2012). Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/33557

Chicago Manual of Style (16^th Edition):

Tarantini, Vincent. “Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite.” 2012. Masters Thesis, University of Toronto. Accessed March 07, 2021. http://hdl.handle.net/1807/33557.

MLA Handbook (7^th Edition):

Tarantini, Vincent. “Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite.” 2012. Web. 07 Mar 2021.

Vancouver:

Tarantini V. Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/1807/33557.

Council of Science Editors:

Tarantini V. Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite. [Masters Thesis]. University of Toronto; 2012. Available from: http://hdl.handle.net/1807/33557

Delft University of Technology

3. Trullas Ballester, Marc (author). Asteroid Mission Guidance and Control using Dual Quaternions.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:49257a61-5d9e-402d-acde-e82ef5fa6ed8

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The investigation of small bodies in the Solar System such as asteroids and comets is of increasing interest to the space exploration community for scientific… (more)

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The investigation of small bodies in the Solar System such as asteroids and comets is of increasing interest to the space exploration community for scientific and security reasons. A key enabling technology is the availability to control position and attitude of spacecraft for asteroid close-proximity operations. Dynamics and control issues related to these operations have been investigated addressing the orbital and attitude motion of the spacecraft with no coupling between them assumed. In reality however, the translational and rotational dynamics of spacecraft are generally coupled. It is therefore desirable to simultaneously take into account the full six degrees of freedom problem when developing pose (position and orientation) control laws for practical applications. One way of doing that is by expressing the state variables with dual quaternions, a mathematical formulation that naturally couples both motions in an efficient and compact way. The goal of this thesis is to determine what advantages and disadvantages can a six degrees of freedom controller based on dual quaternions bring over classical methods regarding asteroid close-proximity operations. To do so, a simulator was developed in Matlab R2016b with the two different representations: the dual quaternion one and the classical one using vectors for position, velocity and angular velocity, and quaternions for the attitude. Then, a controller was designed and optimized for each representation to follow a reference trajectory in three different scenarios, such as orbiting, hovering and landing on the asteroid Bennu. The dual quaternion representation has only two equations of motion instead of the four required for the classical one because of its compactness and natural way of coupling rotational and translational motions. However, results show that the dual quaternion controller takes 15% more computational time to achieve the same level of accuracy and energy consumption as the classical controller for the nominal scenarios. The reason for that is because the total number of operations involved in the integration of the equations of motions is higher. Moreover, a stability analysis was carried out and showed that controllers based on dual quaternions can handle much larger perturbations than the classical ones. Specifically, between 23 and 227 times larger perturbations depending on the scenario. Apart from that, results also proved that dual quaternion controllers can correct trajectory perturbations in a much faster and efficient way than the classical ones. Specifically, they have a settling time between 29% and 92% shorter, accumulate between 2.6 and 19 times less error and consume between 3.2 and 9.3 times less energy, depending on the scenario.

Aerospace Engineering | Space Flight

Advisors/Committee Members: Mooij, Erwin (mentor), McMahon, Jay (mentor), Vermeersen, Bert (graduation committee), Chu, Q.P. (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: Asteroids; Dual Quaternions; Control; Attitude; Pose; Quaternions; Landing; Hover; Orbit

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APA (6^th Edition):

Trullas Ballester, M. (. (2018). Asteroid Mission Guidance and Control using Dual Quaternions. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:49257a61-5d9e-402d-acde-e82ef5fa6ed8

Chicago Manual of Style (16^th Edition):

Trullas Ballester, Marc (author). “Asteroid Mission Guidance and Control using Dual Quaternions.” 2018. Masters Thesis, Delft University of Technology. Accessed March 07, 2021. http://resolver.tudelft.nl/uuid:49257a61-5d9e-402d-acde-e82ef5fa6ed8.

MLA Handbook (7^th Edition):

Trullas Ballester, Marc (author). “Asteroid Mission Guidance and Control using Dual Quaternions.” 2018. Web. 07 Mar 2021.

Vancouver:

Trullas Ballester M(. Asteroid Mission Guidance and Control using Dual Quaternions. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Mar 07]. Available from: http://resolver.tudelft.nl/uuid:49257a61-5d9e-402d-acde-e82ef5fa6ed8.

Council of Science Editors:

Trullas Ballester M(. Asteroid Mission Guidance and Control using Dual Quaternions. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:49257a61-5d9e-402d-acde-e82ef5fa6ed8

Delft University of Technology

4. Crepy-Marglais, Jean-Daniel (author). Development of a Robust and Combined Controller for On-Orbit Servicing Missions.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:f163745c-e9d9-4b22-9e5b-1f4d3790ebf6

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Nowadays, a satellite is considered as out of range forever once it is launched. This may soon no longer hold thanks to on-orbit servicing. However,… (more)

Subjects/Keywords: space robotics; on-orbit servicing; Control; H-infinity control; Attitude control; Robotics; loop shaping; combined control; robust control

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APA (6^th Edition):

Crepy-Marglais, J. (. (2018). Development of a Robust and Combined Controller for On-Orbit Servicing Missions. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:f163745c-e9d9-4b22-9e5b-1f4d3790ebf6

Chicago Manual of Style (16^th Edition):

Crepy-Marglais, Jean-Daniel (author). “Development of a Robust and Combined Controller for On-Orbit Servicing Missions.” 2018. Masters Thesis, Delft University of Technology. Accessed March 07, 2021. http://resolver.tudelft.nl/uuid:f163745c-e9d9-4b22-9e5b-1f4d3790ebf6.

MLA Handbook (7^th Edition):

Crepy-Marglais, Jean-Daniel (author). “Development of a Robust and Combined Controller for On-Orbit Servicing Missions.” 2018. Web. 07 Mar 2021.

Vancouver:

Crepy-Marglais J(. Development of a Robust and Combined Controller for On-Orbit Servicing Missions. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Mar 07]. Available from: http://resolver.tudelft.nl/uuid:f163745c-e9d9-4b22-9e5b-1f4d3790ebf6.

Council of Science Editors:

Crepy-Marglais J(. Development of a Robust and Combined Controller for On-Orbit Servicing Missions. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:f163745c-e9d9-4b22-9e5b-1f4d3790ebf6

University of Toronto

5. Hakima, Houman. A New Approach to Active Removal of Space Debris.

Degree: PhD, 2020, University of Toronto

URL: http://hdl.handle.net/1807/101359

► As a result of human space activities for over sixty years, there exist numerous man-made debris objects in the Earth orbits. Such objects not only… (more)

▼ As a result of human space activities for over sixty years, there exist numerous man-made debris objects in the Earth orbits. Such objects not only jeopardize current operations of important space assets, but can also seriously hinder future space missions through a potential chain reaction of colliding space debris. This research addresses mitigation and remediation of the space debris environment. The thesis entails research in four critical subject areas: i) characterization of the debris environment, ii) assessment of the active debris removal methods proposed in the literature, iii) detailed engineering of a novel removal concept using a CubeSat spacecraft, called Deorbiter CubeSat, for sizable debris objects in low-Earth orbit, and iv) design of attitude and orbit controllers for the proposed spacecraft. The research first develops a probabilistic method for the prioritization of debris objects to be consid- ered in near-future removal missions. Then, a comparative study and in-depth analysis is conducted on the removal methods proposed in the literature to investigate their viability, through a number of multi- criteria assessment techniques. A Monte Carlo analysis is used in the study to quantify the intrinsic uncertainty associated with the space debris population. Next, a new debris removal mission utilizing Deorbiter CubeSats is conceptualized, and the design of CubeSat subsystems is detailed. A mothership spacecraft carries and deploys a number of Deorbiter CubeSats into designated orbits near their target debris. Each CubeSat uses an eight-unit form factor, and consists of commercially-available components with substantial space heritage. The actual performance specifications of the components are used to examine the proposed space debris removal approach. Finally, control schemes are synthesized for the critical maneuvers in the mission, using a unilateral low-thrust propulsion and a three-axis reaction wheel systems onboard the CubeSat, namely, i) concurrent rendezvous and attitude synchronization maneuver for approaching and attaching to the debris, ii) detumbling maneuver for stabilizing the debris attitude motion, and iii) deorbiting maneuver for transferring the debris from its original orbit to a deorbit altitude along a time-optimal trajectory. Several numerical simulations verify and validate the proposed approach as well as the control schemes. Advisors/Committee Members: Emami, M. Reza, Aerospace Science and Engineering.

Subjects/Keywords: Active Debris Removal; Attitude and Orbit Control; Attitude Dynamics; Deorbiter CubeSat; Orbital Dynamics; Space Debris; 0538

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APA (6^th Edition):

Hakima, H. (2020). A New Approach to Active Removal of Space Debris. (Doctoral Dissertation). University of Toronto. Retrieved from http://hdl.handle.net/1807/101359

Chicago Manual of Style (16^th Edition):

Hakima, Houman. “A New Approach to Active Removal of Space Debris.” 2020. Doctoral Dissertation, University of Toronto. Accessed March 07, 2021. http://hdl.handle.net/1807/101359.

MLA Handbook (7^th Edition):

Hakima, Houman. “A New Approach to Active Removal of Space Debris.” 2020. Web. 07 Mar 2021.

Vancouver:

Hakima H. A New Approach to Active Removal of Space Debris. [Internet] [Doctoral dissertation]. University of Toronto; 2020. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/1807/101359.

Council of Science Editors:

Hakima H. A New Approach to Active Removal of Space Debris. [Doctoral Dissertation]. University of Toronto; 2020. Available from: http://hdl.handle.net/1807/101359

Virginia Tech

6. Keil, Elizabeth Marie. Kalman Filter Implementation to Determine Orbit and Attitude of a Satellite in a Molniya Orbit.

Degree: MS, Aerospace Engineering, 2014, Virginia Tech

URL: http://hdl.handle.net/10919/49102

► 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… (more)

▼ 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 implementation of site track measurements when the satellite was over the ground station. It is shown that large errors, upwards of ninety meters, grow as time from last measurement input increases. The next case studied was continuous measurement inputs from a GPS receiver on board the satellite throughout the orbit. This algorithm greatly decreased the errors seen in the orbit determining algorithm due to the accuracy of the sensor as well as the continuous measurement inputs throughout the orbit. It is shown that the accuracy of the orbit determining Kalman filter also depends on the length of time between each measurement update. The errors decrease as the time between measurement updates decreases. Next the Kalman filter is applied to determine the satellite attitude. The rotational equations of motion are propagated using Cowell's Formulation and numerical integration. To increase the fidelity of the model four disturbing torques are included in the rotational equations of motion model: gravity gradient torque, solar pressure torque, magnetic torque, and aerodynamic torque. Four cases were tested corresponding to four different on board attitude determining sensors: magnetometer, Earth sensor, sun sensor, and star tracker. A controlled altitude path was chosen to test the accuracy of each of these cases and it was shown that the algorithm using star tracker measurements was three hundred times more accurate than that of the magnetometer algorithm. Advisors/Committee Members: McGwier, Robert W. (committeechair), Woolsey, Craig A. (committee member), Sultan, Cornel (committee member).

Subjects/Keywords: Attitude; Orbit; Determination; Kalman Filter

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Keil, E. M. (2014). Kalman Filter Implementation to Determine Orbit and Attitude of a Satellite in a Molniya Orbit. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/49102

Chicago Manual of Style (16^th Edition):

Keil, Elizabeth Marie. “Kalman Filter Implementation to Determine Orbit and Attitude of a Satellite in a Molniya Orbit.” 2014. Masters Thesis, Virginia Tech. Accessed March 07, 2021. http://hdl.handle.net/10919/49102.

MLA Handbook (7^th Edition):

Keil, Elizabeth Marie. “Kalman Filter Implementation to Determine Orbit and Attitude of a Satellite in a Molniya Orbit.” 2014. Web. 07 Mar 2021.

Vancouver:

Keil EM. Kalman Filter Implementation to Determine Orbit and Attitude of a Satellite in a Molniya Orbit. [Internet] [Masters thesis]. Virginia Tech; 2014. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/10919/49102.

Council of Science Editors:

Keil EM. Kalman Filter Implementation to Determine Orbit and Attitude of a Satellite in a Molniya Orbit. [Masters Thesis]. Virginia Tech; 2014. Available from: http://hdl.handle.net/10919/49102

7. Quinsac, Gary. From commercials off-the-shelf to expected propulsion in nanosatellites : Utilisation de composants sur étagère pour la propulsion des nanosatellites : à quel prix ?.

Degree: Docteur es, Astronomie et Astrophysique, 2019, Paris Sciences et Lettres (ComUE)

URL: http://www.theses.fr/2019PSLEO004

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L’apparition du standard CubeSat a profondément modifié le domaine des nano/microsatellites, notamment en promouvant la standardisation, des développements plus courts et des lancements partagés. L’intérêt… (more)

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L’apparition du standard CubeSat a profondément modifié le domaine des nano/microsatellites, notamment en promouvant la standardisation, des développements plus courts et des lancements partagés. L’intérêt combiné des agences spatiales et des entreprises a permis une forte croissance des lancements de CubeSats depuis vingt ans. De nombreux « composants sur étagère » sont maintenant développés dans le respect de ce standard. Pourtant, les contraintes importantes résultant de ce format réduit en termes de masse, volume et puissance disponibles ont jusqu’à présent limité l’envoi de CubeSats aux orbites terrestres basses. Des progrès sont en cours pour ce qui concerne le contrôle orbital et doivent permettre d’offrir à ces satellites plus de flexibilité, et notamment ouvrir la porte à des missions plus exotiques telles que des missions interplanétaires.Cette thèse s’intéresse aux difficultés d’application de la philosophie des CubeSats au Système de Contrôle d’Attitude et d’Orbite (SCAO). L’utilisation de « composants sur étagère » pousse à considérer chaque sous-système indépendamment, pouvant conduire à des performances dégradées au niveau du satellite. En particulier, la distinction entre le système de contrôle d’attitude et celui d’orbite (SCA/GNC) cache des impacts mutuels non négligeables. Ce travail développe une analyse de haut niveau sur différents cas d’étude représentatifs des besoins identifiés tels que la désorbitation depuis une orbite basse, la sortie de l’orbite terrestre ou encore les opérations de proximité. Une analyse fonctionnelle met l’accent sur les connexions entre les différents sous-systèmes nécessaires à la réussite de ces manœuvres orbitales. Il en ressort que l’approche conventionnelle a tendance à considérer que le contrôle de la direction de poussée ne nécessite pas de sous-système dédié. Les indices de performance usuels des systèmes de propulsions sont quant à eux lacunaires. Ils mettent l’accent sur la masse de carburant au dépend de la masse sèche du système, et ils omettent la masse supplémentaire que représentent les besoins électriques et thermiques, conduisant parfois à des propositions infaisables au format CubeSat. L’impact des propulseurs sur le design du SCA est quantifié à travers le développement d’un environnement de simulation du SCAO. On y observe d’importantes augmentations de la durée des manœuvres et de la consommation de carburant, voire une perte du satellite. En conséquence, des propositions sont faites pour permettre la réalisation du contrôle orbital souhaité. La description classique des systèmes de propulsion est quant à elle revisitée afin de fournir un indice prenant en compte l’ensemble des effets liés à l’intégration de propulseurs.

The domain of nano/microsatellites has been irreversibly modified by the apparition of the CubeSat standard. The exponential growth of CubeSat launches during the past 20 years, combined with the growing interest of private companies and space agencies has confirmed the sustainability of a new approach to space missions:…

Advisors/Committee Members: Mosser, Benoît (thesis director).

Subjects/Keywords: CubeSat; Nanosatellite; Propulsion; Attitude; Orbite; Scao; Cubesat; Nanosatellite; Propulsion; Attitude; Orbit; Aocs; 520

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APA (6^th Edition):

Quinsac, G. (2019). From commercials off-the-shelf to expected propulsion in nanosatellites : Utilisation de composants sur étagère pour la propulsion des nanosatellites : à quel prix ?. (Doctoral Dissertation). Paris Sciences et Lettres (ComUE). Retrieved from http://www.theses.fr/2019PSLEO004

Chicago Manual of Style (16^th Edition):

Quinsac, Gary. “From commercials off-the-shelf to expected propulsion in nanosatellites : Utilisation de composants sur étagère pour la propulsion des nanosatellites : à quel prix ?.” 2019. Doctoral Dissertation, Paris Sciences et Lettres (ComUE). Accessed March 07, 2021. http://www.theses.fr/2019PSLEO004.

MLA Handbook (7^th Edition):

Quinsac, Gary. “From commercials off-the-shelf to expected propulsion in nanosatellites : Utilisation de composants sur étagère pour la propulsion des nanosatellites : à quel prix ?.” 2019. Web. 07 Mar 2021.

Vancouver:

Quinsac G. From commercials off-the-shelf to expected propulsion in nanosatellites : Utilisation de composants sur étagère pour la propulsion des nanosatellites : à quel prix ?. [Internet] [Doctoral dissertation]. Paris Sciences et Lettres (ComUE); 2019. [cited 2021 Mar 07]. Available from: http://www.theses.fr/2019PSLEO004.

Council of Science Editors:

Quinsac G. From commercials off-the-shelf to expected propulsion in nanosatellites : Utilisation de composants sur étagère pour la propulsion des nanosatellites : à quel prix ?. [Doctoral Dissertation]. Paris Sciences et Lettres (ComUE); 2019. Available from: http://www.theses.fr/2019PSLEO004

Linköping University

8. Elfving, Jonas. Attitude and Orbit Control for Small Satellites.

Degree: Electrical Engineering, 2002, Linköping University

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-1407

► A satellite in orbit about a planet needs some means of attitude control in order to, for instance, get as much sun into its… (more)

Subjects/Keywords: Reglerteknik; satellites; attitude; orbit; control; Kalman estimation filters; quaternions; stabilization; pointing accuracy; Reglerteknik; Automatic control; Reglerteknik

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APA (6^th Edition):

Elfving, J. (2002). Attitude and Orbit Control for Small Satellites. (Thesis). Linköping University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-1407

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Elfving, Jonas. “Attitude and Orbit Control for Small Satellites.” 2002. Thesis, Linköping University. Accessed March 07, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-1407.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Elfving, Jonas. “Attitude and Orbit Control for Small Satellites.” 2002. Web. 07 Mar 2021.

Vancouver:

Elfving J. Attitude and Orbit Control for Small Satellites. [Internet] [Thesis]. Linköping University; 2002. [cited 2021 Mar 07]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-1407.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Elfving J. Attitude and Orbit Control for Small Satellites. [Thesis]. Linköping University; 2002. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-1407

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

9. Flodin, Linus. Attitude and Orbit Control During Deorbit of Tethered Space Debris.

Degree: Aeronautical and Vehicle Engineering, 2015, KTH

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-166824

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Due to the unsustainable space debris environment in Low Earth Orbit, debris objects must be removed to ensure future safe satellite operations. One proposed… (more)

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Due to the unsustainable space debris environment in Low Earth Orbit, debris objects must be removed to ensure future safe satellite operations. One proposed concept for deorbiting larger space debris objects, such as decommissioned satellites or spent upper rocket stages, is to use a chaser spacecraft connected to the debris object by an elastic tether, but the required technology is immature and there is a lack of flight experience. The inoperable satellite, Envisat, has been chosen as a representative object for controlled re-entry by performing several high thrust burns. The aim of this paper is to develop a control system for the deorbit phase of such a mission. Models of the spacecraft dynamics, the tether, and sensors are developed to create a simulator. Two different tether models are considered: the massless model and the lumped mass model. A switched linear-quadratic-Gaussian (LQG) controller is designed to control the relative position of the debris object, and a switched proportional-integral-derivative (PID) controller is designed for attitude control. Feedforward compensation is used to counteract the couplings between relative position and attitude dynamics. An analysis of the system suggests that the tether should be designed in regard to the control system and it is found that the lumped mass model comes with higher cost than reward compared to the massless tether model in this case. Simulations show that the control system is able to control the system under the influence of modeling errors during a multi-burn deorbit strategy and even though more extensive models are suggested to enable assessment of the feasibility to perform this mission in reality, this study has resulted in extensive knowledge and valuable progress in the technical development.

En ökande mängd rymdskrot har lett till en ohållbar miljö i låga omloppsbanor och föremål måste nu tas bort för att säkerställa framtida satellitverksamhet. En föreslagen metod för att avlägsna större skrotföremål, såsom avvecklade satelliter och använda övre raketsteg, är att koppla en jagande rymdfarkost till föremålet med en elastisk lina. Dock är den teknik som behövs inte mogen och det finns en brist på praktisk erfarenhet. Den obrukbara satelliten Envisat har valts som representativt objekt för kontrollerat återinträde genom flera perigeumsänkande raketmanövrar. Syftet med detta arbete är att utveckla ett system för att kontrollera de två sammankopplade rymdfarkosterna under avlägsningsfasen under ett sådant uppdrag. Modeller för farkosternas dynamik, den sammankopplande linan och sensorer byggs för att utveckla en simulator. Två olika modeller för linan undersöks: den masslösa modellen och den klumpade nodmassmodellen. En omkopplande regulator designas genom minimering av kvadratiska kriterier för att kontrollera skrotföremålets relativa position till den jagande farkosten. Vidare designas en omkopplande proportionerlig-integrerande-deriverande (PID) regulator för att reglera pekningen hos den jagande farkosten. Kompensering genom…

Subjects/Keywords: space debris mitigation; deorbit; tethered satellites; mathematical modeling; attitude and orbit control system; LQG control; PID control; switched control

…converted to the SCB frame to be properly saturated. B. Attitude control The main purpose of the… …Figure 13. The discrete time PID controller used for attitude control. Chaser FME x Ftether… …feedforward control is required both in the relative position controller and in the attitude… …in the simulator. 2) Attitude control: Feedforward in the attitude controller is… …engines used for deorbit burns, the chaser is equipped with a Reaction Control System (RCS…

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APA (6^th Edition):

Flodin, L. (2015). Attitude and Orbit Control During Deorbit of Tethered Space Debris. (Thesis). KTH. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-166824

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Flodin, Linus. “Attitude and Orbit Control During Deorbit of Tethered Space Debris.” 2015. Thesis, KTH. Accessed March 07, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-166824.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Flodin, Linus. “Attitude and Orbit Control During Deorbit of Tethered Space Debris.” 2015. Web. 07 Mar 2021.

Vancouver:

Flodin L. Attitude and Orbit Control During Deorbit of Tethered Space Debris. [Internet] [Thesis]. KTH; 2015. [cited 2021 Mar 07]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-166824.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Flodin L. Attitude and Orbit Control During Deorbit of Tethered Space Debris. [Thesis]. KTH; 2015. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-166824

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

10. Adriano Marto Reis. Simulação distribuída em tempo-real de um sistema de controle de atitude e órbita para a plataforma multi-missão utilizando a arquitetura HLA.

Degree: 2009, Instituto Nacional de Pesquisas Espaciais

URL: http://urlib.net/sid.inpe.br/[email protected]/2009/03.02.22.17

►

Neste trabalho apresenta-se o estudo e o desenvolvimento de uma simulação distribuída em Tempo Real de um Sistema de Controle de Atitude e de Órbita… (more)

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Neste trabalho apresenta-se o estudo e o desenvolvimento de uma simulação distribuída em Tempo Real de um Sistema de Controle de Atitude e de Órbita (SCAO) para a Plataforma Multi-Missão (PMM) em seu Modo Nominal de Operação utilizando a arquitetura HLA (High Level Architecture). A PMM é uma plataforma atualmente em desenvolvimento no Instituto Nacional de Pesquisas Espaciais (INPE) seguindo um paradigma moderno no desenvolvimento de satélites artificiais, onde uma plataforma base será desenvolvida para a utilização em diversas missões. A HLA é uma arquitetura de propósito geral para reutilização e interoperabilidade de simulações. Esta arquitetura foi desenvolvida por encomenda do DMSO (Defense Modeling and Simulation Office) com o objetivo de possibilitar o reuso e a interoperabilidade entre os diversos tipos de simulação desenvolvidos e mantidos pelo DoD (Department of Defense) dos EUA. Para cumprir os objetivos deste trabalho foram realizadas as seguintes atividades: (1) seleção do esquema de sincronização e do mecanismo de troca de dados mais apropriados para a aplicação proposta; (2) desenvolvimento de uma interface SystemBuild/HLA; (3) adaptação de uma simulação stand-alone existente à arquitetura HLA; (4) simulação em um computador sem e com restrições de Tempo Real; (5) simulação em dois computadores sem e com restrições de tempo real e (6) validação dos resultados frente à simulação original. Os resultados obtidos mostram que os objetivos deste trabalho foram alcançados e que a arquitetura HLA é aplicável a simulações distribuídas em Tempo Real de sistemas espaciais, especialmente de SCAOs de satélites artificiais.

This work presents the study and the development of a real-time distributed simulation of an Attitude and Orbit Control System (AOCS) for the Multi-Mission Platform (MMP) in its Nominal Mode of Operation by using the High Level Architecture (HLA). The MMP is a platform being developed at the National Institute of Space Research (INPE) following a modern paradigm of artificial satellite development that proposes the development of a basic platform which is used in several missions. The HLA is a general-purpose architecture for simulation reuse and interoperability. This architecture was developed under the leadership of the Defense Modeling and Simulation Office (DMSO) to support reuse and interoperability across the large numbers of different types of simulations developed and maintained by the Department of Defense (DoD) of USA. To accomplish the goals of this work, the following activities were performed: (1) selection of the synchronisation schema and the data exchange method more suitable for the proposed application; (2) development of a SystemBuild/HLA interface; (3) adaptation of an existing stand-alone simulation to the HLA; (4) simulation in a single computer without and with real-time constraints; (5) simulation in two computers without and with real-time constraints and (6) validation of the obtained results by comparing them with the results of the stand-alone simulation. The…

Advisors/Committee Members: Paulo Giácomo Milani, Marcelo Lopes de Oliveira e Souza, Ijar Milagre da Fonseca, Valdemir Carrara, Gilberto da Cunha Trivelato.

Subjects/Keywords: simulação distribuída; simulação em tempo real; high level architecture (HLA); controle de atitude; órbita; plataforma multi-missão; distributed simulation; real time simulation; high level archicture (HLA); attitude control; orbit; multi-mission platform

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Reis, A. M. (2009). Simulação distribuída em tempo-real de um sistema de controle de atitude e órbita para a plataforma multi-missão utilizando a arquitetura HLA. (Thesis). Instituto Nacional de Pesquisas Espaciais. Retrieved from http://urlib.net/sid.inpe.br/[email protected]/2009/03.02.22.17

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Reis, Adriano Marto. “Simulação distribuída em tempo-real de um sistema de controle de atitude e órbita para a plataforma multi-missão utilizando a arquitetura HLA.” 2009. Thesis, Instituto Nacional de Pesquisas Espaciais. Accessed March 07, 2021. http://urlib.net/sid.inpe.br/[email protected]/2009/03.02.22.17.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Reis, Adriano Marto. “Simulação distribuída em tempo-real de um sistema de controle de atitude e órbita para a plataforma multi-missão utilizando a arquitetura HLA.” 2009. Web. 07 Mar 2021.

Vancouver:

Reis AM. Simulação distribuída em tempo-real de um sistema de controle de atitude e órbita para a plataforma multi-missão utilizando a arquitetura HLA. [Internet] [Thesis]. Instituto Nacional de Pesquisas Espaciais; 2009. [cited 2021 Mar 07]. Available from: http://urlib.net/sid.inpe.br/[email protected]/2009/03.02.22.17.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Reis AM. Simulação distribuída em tempo-real de um sistema de controle de atitude e órbita para a plataforma multi-missão utilizando a arquitetura HLA. [Thesis]. Instituto Nacional de Pesquisas Espaciais; 2009. Available from: http://urlib.net/sid.inpe.br/[email protected]/2009/03.02.22.17

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Cal Poly

11. Bowen, John Arthur. On-Board Orbit Determination and 3-Axis Attitude Determination for Picosatellite Applications.

Degree: MS, Aerospace Engineering, 2009, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/131 ; 10.15368/theses.2009.114

► 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… (more)

▼ 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 analytic Sun direction model, and the TRIAD method to combine vector observations into attitude information. The orbit propagator is a simple model of a circular trajectory with several frequently updated parameters and can provide orbital position data with average and maximum errors—when compared to SGP4—of less than 3.7km and 10.7km for 14 days. The magnetic field look up table provides useful information from a small memory footprint; only 480 data points provide a mean error of approximately 0.2° and a maximum error of approximately 2°—when compared to the IGRF model. The Sun’s direction is modeled, and as expected, can be modeled simply and accurately. Combining the magnetic field and Sun direction models with inaccurate sensors and the TRIAD method results in useful attitude information from a very simple system. A system with Sun sensor error standard deviation of 1° and magnetometer error standard deviation of 5° yields results with average error of only 2.74°, and 99% of the errors in this case are less than approximately 13°. The system outlined provides crude attitude determination with software and hardware requirements that are well within the capabilities of current 1U CubeSats—something that many other systems, such as Kalman filters or star trackers, cannot do. It also provides an excellent starting point for future ADCS systems, which will significantly increase the ability of CubeSats. Advisors/Committee Members: Jordi Puig-Suari.

Subjects/Keywords: orbit determination; attitude determination; CubeSat; picosatellite; IGRF; TRIAD; Navigation, Guidance, Control and Dynamics; Space Vehicles

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Bowen, J. A. (2009). On-Board Orbit Determination and 3-Axis Attitude Determination for Picosatellite Applications. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/131 ; 10.15368/theses.2009.114

Chicago Manual of Style (16^th Edition):

Bowen, John Arthur. “On-Board Orbit Determination and 3-Axis Attitude Determination for Picosatellite Applications.” 2009. Masters Thesis, Cal Poly. Accessed March 07, 2021. https://digitalcommons.calpoly.edu/theses/131 ; 10.15368/theses.2009.114.

MLA Handbook (7^th Edition):

Bowen, John Arthur. “On-Board Orbit Determination and 3-Axis Attitude Determination for Picosatellite Applications.” 2009. Web. 07 Mar 2021.

Vancouver:

Bowen JA. On-Board Orbit Determination and 3-Axis Attitude Determination for Picosatellite Applications. [Internet] [Masters thesis]. Cal Poly; 2009. [cited 2021 Mar 07]. Available from: https://digitalcommons.calpoly.edu/theses/131 ; 10.15368/theses.2009.114.

Council of Science Editors:

Bowen JA. On-Board Orbit Determination and 3-Axis Attitude Determination for Picosatellite Applications. [Masters Thesis]. Cal Poly; 2009. Available from: https://digitalcommons.calpoly.edu/theses/131 ; 10.15368/theses.2009.114

Stellenbosch University

12. Kearney, Mike-Alec. A thermal simulation tool for CubeSats for dynamic in-orbit scenarios, verified with flight data from the nSight-1 mission.

Degree: MEng, Mechanical and Mechatronic Engineering, 2020, Stellenbosch University

URL: http://hdl.handle.net/10019.1/108309

►

ENGLISH ABSTRACT: Thermal analysis is one of the aspects of designing CubeSats that has historically received less attention than more directly mission critical aspects such… (more)

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ENGLISH ABSTRACT: Thermal analysis is one of the aspects of designing CubeSats that has historically received less attention than more directly mission critical aspects such as power and communications budgets, and attitude control performance. The reasons for this neglect are partly due to the complexities of doing detailed thermal analyses, and partly because of the high cost of thermal simulation software that is tailored for the unique environment of space. Typically, CubeSat teams will do simplified steady state thermal analyses for a particular satellite orientation and particular orbit. However, these analyses generally only account for the original orbit a satellite is launched in, which proves problematic. Given the fact that much of these orbits are not Sun-synchronous, and that in Low Earth Orbit (LEO) these orbits decay rapidly, these simplified analyses are only valid for a small portion of the satellite’s mission lifetime. With this in mind, this study created a method to integrate a lumped-capacitance thermal model with a high accuracy Attitude Determination and Control System (ADCS) simulation program in order to simulate the temperature of a CubeSat for dynamic orientation and orbital scenarios. To supplement this simulation, a software tool was created to simplify the process of creating a numerical model of the surfaces of a satellite, which includes geometry, links between the surfaces and lumped thermal nodes, as well as the thermal properties of the surfaces. The study discusses the key elements of the thermal environment in Space such as direct sunlight, reflected sunlight off of the Earth (albedo), Earth infrared (IR), as well as radiation to deep space. Ray tracing capability of the ADCS program is used to simulate shadowing of parts of the satellite by deployable solar panels. A method of calculating the view factor (VF) between surfaces of the satellite and the Earth is also discussed, since this has a significant effect on the heat transferred to a satellite with varying orientation. The validity of the simulation was tested using a thermal model of the South African built satellite nSight-1, by comparing simulation outputs with in-orbit temperature measurements. The simulation tool was used to analyse the temperature of the nSight-1 subsystems for varying orbits, in order to identify problematic cases where subsystems exceed their maximum/minimum operational temperatures. Suggestions were then made for improvements to the thermal design in order to manage these problematic temperatures, and the suggested changes were simulated to verify their effects.

AFRIKAANSE OPSOMMING: Termiese analise is een van die aspekte van die ontwerp van CubeSats wat histories minder aandag geniet as meer direkte, missie-kritieke aspekte, soos krag- en komunikasie begrotings en orientasie beheer. Die redes hiervoor is deels as gevolg van die kompleksiteit van gedetailleerde termiese ontledings, en deels as gevolg van die hoë koste van sagteware vir termiese simulasie wat spesifiek aangepas is vir die…

Advisors/Committee Members: Venter, Gerhard, Dobson, Robert, Stellenbosch University. Faculty of Engineering. Dept. of Mechanical and Mechatronic Engineering..

Subjects/Keywords: Cubesats; Artificial satellites – Attitude; Thermal analysis – Simulation methods; Temperature measurements; nSight-1 – Orbit; UCTD

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Kearney, M. (2020). A thermal simulation tool for CubeSats for dynamic in-orbit scenarios, verified with flight data from the nSight-1 mission. (Thesis). Stellenbosch University. Retrieved from http://hdl.handle.net/10019.1/108309

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Kearney, Mike-Alec. “A thermal simulation tool for CubeSats for dynamic in-orbit scenarios, verified with flight data from the nSight-1 mission.” 2020. Thesis, Stellenbosch University. Accessed March 07, 2021. http://hdl.handle.net/10019.1/108309.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Kearney, Mike-Alec. “A thermal simulation tool for CubeSats for dynamic in-orbit scenarios, verified with flight data from the nSight-1 mission.” 2020. Web. 07 Mar 2021.

Vancouver:

Kearney M. A thermal simulation tool for CubeSats for dynamic in-orbit scenarios, verified with flight data from the nSight-1 mission. [Internet] [Thesis]. Stellenbosch University; 2020. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/10019.1/108309.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Kearney M. A thermal simulation tool for CubeSats for dynamic in-orbit scenarios, verified with flight data from the nSight-1 mission. [Thesis]. Stellenbosch University; 2020. Available from: http://hdl.handle.net/10019.1/108309

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

13. Carmen Miranda de Lira Silva. Estimação conjunta de órbita e atitude de satélites artificiais estabilizados por rotação utilizando observações do magnetômetro e sensor solar.

Degree: 2005, Instituto Nacional de Pesquisas Espaciais (INPE)

URL: http://urlib.net/sid.inpe.br/jeferson/2005/06.15.17.32

►

Neste trabalho desenvolve-se e testa-se, sistematicamente, um procedimento de estimação conjunta de órbita e atitude destinado a satélites artificiais estabilizados por rotação em órbitas baixas.… (more)

▼

Neste trabalho desenvolve-se e testa-se, sistematicamente, um procedimento de estimação conjunta de órbita e atitude destinado a satélites artificiais estabilizados por rotação em órbitas baixas. Para tanto, utiliza-se em técnicas ótimas de estimação de estados, medidas fornecidas por dois tipos de sensores, convencionais para determinação apenas de atitude. Este procedimento utiliza as técnicas Mínimos Quadrados e Filtro Estendido de Kalman para processar as medidas: ângulo do aspecto solar, fornecido por dois sensores solares e componentes axial e radial do campo geomagnético, fornecidas por um magnetômetro. Para a sua sistemática tal procedimento é dividido em pré-processamento e processo de estimação, e subdividido em curto, médio e longo períodos. Um algoritmo para a geração das informações a priori da órbita e da atitude de um satélite artificial foi desenvolvido e implementado em linguagem it{Matlab}registered, assim como os estimadores. Este algoritmo é fundamentalmente inspirado nas passagens do satélite pela sombra da Terra e nas observações do campo geomagnético. O procedimento é testado com observações simuladas, com dados simulados e reais de órbita e atitude do satélite nacional de coleta de dados ambientais SCD-1, cuja órbita é quase circular, com altitude de 750 km e inclinação de 25°. O modelo da dinâmica orbital é o Kepleriano e o satélite é considerado inercialmente estabilizado. O modelo do campo geomagnético é considerado de ordem e grau 10, com coeficientes dados pelo IGRF-95. A convergência do processo foi alcançada com sucesso pelo Mínimos Quadrados e refinada pelo Filtro Estendido de Kalman. As estimativas obtidas indicam que o procedimento tem condições de fornecer, dentro da tolerante precisão de até 100 km a informação da órbita, conjuntamente com a atitude de um satélite artificial cujas características sejam equivalentes ao que foi utilizado nos testes do procedimento.

In this work it is developed and it is tested, systematically, a procedure for joint estimation of orbit and attitude destined to artificial satellites stabilized by rotation in low orbits. For that, it is used optimal state estimation techniques, measures supplied for two types of sensors, conventionally used for attitude determination only. This procedure uses the Least Squares and the Extended Kalman Filter techniques to process the measures: of solar angle aspect, supplied by two solar sensors; and axial and radial components of the geomagnetic field, supplied by a magnetometer. For its systematics such procedure is divided in daily pre-processing and estimation process, and subdivided in short, mean and long periods. An algorithm for the generation of the a priori information of the orbit and attitude of an artificial satellite was developed and implemented in the it{Matlab} registered language, as well as the estimators. This algorithm is basically inspired on the passage of the satellite on Earth´s shadow and in the geomagnetic field observations. The procedure is tested with simulated…

Advisors/Committee Members: Valcir Orlando, Hélio Koiti Kuga, Roberto Vieira da Fonseca Lopes, Maria Cecília França de Paula Zanardi.

Subjects/Keywords: satélite artificiais; magnetômetros; sensor solar; órbita; atitude; filtro kalman; artificial satellites; magnetometer; solar sensors; orbit; attitude; filter of Kalman

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Silva, C. M. d. L. (2005). Estimação conjunta de órbita e atitude de satélites artificiais estabilizados por rotação utilizando observações do magnetômetro e sensor solar. (Thesis). Instituto Nacional de Pesquisas Espaciais (INPE). Retrieved from http://urlib.net/sid.inpe.br/jeferson/2005/06.15.17.32

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Silva, Carmen Miranda de Lira. “Estimação conjunta de órbita e atitude de satélites artificiais estabilizados por rotação utilizando observações do magnetômetro e sensor solar.” 2005. Thesis, Instituto Nacional de Pesquisas Espaciais (INPE). Accessed March 07, 2021. http://urlib.net/sid.inpe.br/jeferson/2005/06.15.17.32.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Silva, Carmen Miranda de Lira. “Estimação conjunta de órbita e atitude de satélites artificiais estabilizados por rotação utilizando observações do magnetômetro e sensor solar.” 2005. Web. 07 Mar 2021.

Vancouver:

Silva CMdL. Estimação conjunta de órbita e atitude de satélites artificiais estabilizados por rotação utilizando observações do magnetômetro e sensor solar. [Internet] [Thesis]. Instituto Nacional de Pesquisas Espaciais (INPE); 2005. [cited 2021 Mar 07]. Available from: http://urlib.net/sid.inpe.br/jeferson/2005/06.15.17.32.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Silva CMdL. Estimação conjunta de órbita e atitude de satélites artificiais estabilizados por rotação utilizando observações do magnetômetro e sensor solar. [Thesis]. Instituto Nacional de Pesquisas Espaciais (INPE); 2005. Available from: http://urlib.net/sid.inpe.br/jeferson/2005/06.15.17.32

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

York University

14. Wright, Thomas Jonathan. Development of Magnetometer-Based Orbit and Attitude Determination for Nanosatellites.

Degree: MSc -MS, Earth & Space Science, 2015, York University

URL: http://hdl.handle.net/10315/28288

► Attitude and orbit determination are critical parts of nanosatellite mission operations. The ability to perform attitude and orbit determination autonomously could lead to a wider… (more)

Subjects/Keywords: Aerospace engineering; SGP4; Orbit determination; Attitude determination; Nanosatellite; Satellite; Extended Kalman Filter; Magnetometer; Magnetic field; IGRF

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Wright, T. J. (2015). Development of Magnetometer-Based Orbit and Attitude Determination for Nanosatellites. (Masters Thesis). York University. Retrieved from http://hdl.handle.net/10315/28288

Chicago Manual of Style (16^th Edition):

Wright, Thomas Jonathan. “Development of Magnetometer-Based Orbit and Attitude Determination for Nanosatellites.” 2015. Masters Thesis, York University. Accessed March 07, 2021. http://hdl.handle.net/10315/28288.

MLA Handbook (7^th Edition):

Wright, Thomas Jonathan. “Development of Magnetometer-Based Orbit and Attitude Determination for Nanosatellites.” 2015. Web. 07 Mar 2021.

Vancouver:

Wright TJ. Development of Magnetometer-Based Orbit and Attitude Determination for Nanosatellites. [Internet] [Masters thesis]. York University; 2015. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/10315/28288.

Council of Science Editors:

Wright TJ. Development of Magnetometer-Based Orbit and Attitude Determination for Nanosatellites. [Masters Thesis]. York University; 2015. Available from: http://hdl.handle.net/10315/28288

15. Garcia, Erick Flores. Simulation of attitude and orbital disturbances acting on ASPECT satellite in the vicinity of the binary asteroid Didymos.

Degree: Space Technology, 2017, Luleå University of Technology

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-62007

► Asteroid missions are gaining interest from the scientific community and many new missions are planned. The Didymos binary asteroid is a Near-Earth Object and… (more)

Subjects/Keywords: Solar System; Small celestial bodies; CubeSat; Attitude Determination Control Systems; Orbit Disturbances; Other Electrical Engineering, Electronic Engineering, Information Engineering; Annan elektroteknik och elektronik

…qn Abbreviations ADCS Attitude Determination and Control System AIDA Asteroid Impact and… …attitude accuracy and orbit stability to successfully complete its objective. A preliminary study… …maneuvering, observational filtering, spacecraft guidance and attitude control for deep space… …consists of determining the orbit and attitude of a spacecraft at any time, as well as the… …and attitude control of a spacecraft. [27, 9] An example, capable of supporting…

10 more images…

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Garcia, E. F. (2017). Simulation of attitude and orbital disturbances acting on ASPECT satellite in the vicinity of the binary asteroid Didymos. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-62007

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Garcia, Erick Flores. “Simulation of attitude and orbital disturbances acting on ASPECT satellite in the vicinity of the binary asteroid Didymos.” 2017. Thesis, Luleå University of Technology. Accessed March 07, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-62007.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Garcia, Erick Flores. “Simulation of attitude and orbital disturbances acting on ASPECT satellite in the vicinity of the binary asteroid Didymos.” 2017. Web. 07 Mar 2021.

Vancouver:

Garcia EF. Simulation of attitude and orbital disturbances acting on ASPECT satellite in the vicinity of the binary asteroid Didymos. [Internet] [Thesis]. Luleå University of Technology; 2017. [cited 2021 Mar 07]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-62007.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Garcia EF. Simulation of attitude and orbital disturbances acting on ASPECT satellite in the vicinity of the binary asteroid Didymos. [Thesis]. Luleå University of Technology; 2017. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-62007

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Cornell University

16. Jung, Hee. ESTIMATION PROBLEMS FOR SATELLITE ORBIT AND ATTITUDE DETERMINATION AND FOR GPS-BASED REMOTE IONOSPHERIC SENSING.

Degree: 2005, Cornell University

URL: http://hdl.handle.net/1813/2097

► Three separate applications of estimation problems in satellite navigation and attitude determination and in ionospheric scintillation monitoring have been solved numerically. The first application is… (more)

▼ Three separate applications of estimation problems in satellite navigation and attitude determination and in ionospheric scintillation monitoring have been solved numerically. The first application is magnetometer-based autonomous orbit determination, the second application is attitude determination using a GPS antenna on a turntable, and the third application is ionospheric scintillation monitoring using semi-codeless dual-frequency GPS techniques. As the first application, a magnetometer-based orbit determination batch filter has been improved and tested with real flight data to determine the performance of a low-cost autonomous orbit determination system. The spacecraft?s orbit, magnetometer biases, and correction terms to the Earth?s magnetic field are estimated by this filter. The maximum position error of this filter for a 24-hour batch of ?rsted data is 59.50 km without field model corrections, but is only 2.19 km with 10th order/degree field model corrections. The second application develops the signal processing algorithm for a prototype of a new attitude sensor, one that uses a single GPS antenna mounted on a rotating turntable, and evaluates its accuracy using real data. The goal of this study is to experimentally validate this new concept. The new attitude sensor measures attitude by using the sinusoidal phase modulation of the GPS carrier signal that is caused by turntable rotation. The new sensor system has been demonstrated to work in practice, and its peak attitude error is between 0.4 and 1.9 deg for a 15 cm antenna mounting radius and a rotation rate of 1000 rpm. The third application is to develop optimal semi-codeless algorithms to track weak dual-frequency P(Y) GPS signals during strong ionospheric scintillations and to test them with real and simulated RF data. The goal of this work is to determine whether these new algorithms are less prone to loss of lock during strong scintillations than are other semi-codeless algorithms. The tracking algorithms use extended Kalman filter (EKF) and smoother methods as part of a semi-codeless technique that performs maximum a posteriori estimation of the W encryption bits of the unknown P(Y) code, which are known to chip at approximately 480 KHz. The algorithms have been successfully tested with real wide-band dual-frequency GPS data under normal signal strength and simulated scintillation conditions with strong amplitude and phase fluctuations. The C/N0 thresholds above which the Kalman-filter algorithm and the smoother algorithm can still track without losing lock are found based on the computed steady-state standard deviation of the L2 carrier phase error from steady-state covariance analysis. This threshold roughly agrees with the tracking results for the simulation data and can be used to predict the possibility of loss of lock.

Subjects/Keywords: Optimal Estimation; GPS; Orbit Determination; Attitude Determination; Extended Kalman Filter; Semi-Codeless Algorithm

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APA (6^th Edition):

Jung, H. (2005). ESTIMATION PROBLEMS FOR SATELLITE ORBIT AND ATTITUDE DETERMINATION AND FOR GPS-BASED REMOTE IONOSPHERIC SENSING. (Thesis). Cornell University. Retrieved from http://hdl.handle.net/1813/2097

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Jung, Hee. “ESTIMATION PROBLEMS FOR SATELLITE ORBIT AND ATTITUDE DETERMINATION AND FOR GPS-BASED REMOTE IONOSPHERIC SENSING.” 2005. Thesis, Cornell University. Accessed March 07, 2021. http://hdl.handle.net/1813/2097.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Jung, Hee. “ESTIMATION PROBLEMS FOR SATELLITE ORBIT AND ATTITUDE DETERMINATION AND FOR GPS-BASED REMOTE IONOSPHERIC SENSING.” 2005. Web. 07 Mar 2021.

Vancouver:

Jung H. ESTIMATION PROBLEMS FOR SATELLITE ORBIT AND ATTITUDE DETERMINATION AND FOR GPS-BASED REMOTE IONOSPHERIC SENSING. [Internet] [Thesis]. Cornell University; 2005. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/1813/2097.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Jung H. ESTIMATION PROBLEMS FOR SATELLITE ORBIT AND ATTITUDE DETERMINATION AND FOR GPS-BASED REMOTE IONOSPHERIC SENSING. [Thesis]. Cornell University; 2005. Available from: http://hdl.handle.net/1813/2097

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Delft University of Technology

17. Chaves Jimenez, A. On the Coupling of Orbit and Attitude Determination of Satellite Formations from Atmospheric Drag: Observability and Estimation Performance.

Degree: 2020, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; urn:NBN:nl:ui:24-uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; c333497d-05ac-422f-9688-31246a6fa7b1 ; 10.4233/uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; urn:isbn:978-94-028-2095-9 ; urn:NBN:nl:ui:24-uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; http://resolver.tudelft.nl/uuid:c333497d-05ac-422f-9688-31246a6fa7b1

► Spacecraft orbit and attitude dynamics have been classically seen as two separated subjects, since the effect of attitude in orbit dynamics was deemed too small… (more)

Subjects/Keywords: Orbit attitude coupling; estimation; spacecraft relative dynamics; Observability Gramian; Extended Kalman Filter

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Chaves Jimenez, A. (2020). On the Coupling of Orbit and Attitude Determination of Satellite Formations from Atmospheric Drag: Observability and Estimation Performance. (Doctoral Dissertation). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; urn:NBN:nl:ui:24-uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; c333497d-05ac-422f-9688-31246a6fa7b1 ; 10.4233/uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; urn:isbn:978-94-028-2095-9 ; urn:NBN:nl:ui:24-uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; http://resolver.tudelft.nl/uuid:c333497d-05ac-422f-9688-31246a6fa7b1

Chicago Manual of Style (16^th Edition):

Chaves Jimenez, A. “On the Coupling of Orbit and Attitude Determination of Satellite Formations from Atmospheric Drag: Observability and Estimation Performance.” 2020. Doctoral Dissertation, Delft University of Technology. Accessed March 07, 2021. http://resolver.tudelft.nl/uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; urn:NBN:nl:ui:24-uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; c333497d-05ac-422f-9688-31246a6fa7b1 ; 10.4233/uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; urn:isbn:978-94-028-2095-9 ; urn:NBN:nl:ui:24-uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; http://resolver.tudelft.nl/uuid:c333497d-05ac-422f-9688-31246a6fa7b1.

MLA Handbook (7^th Edition):

Chaves Jimenez, A. “On the Coupling of Orbit and Attitude Determination of Satellite Formations from Atmospheric Drag: Observability and Estimation Performance.” 2020. Web. 07 Mar 2021.

Vancouver:

Chaves Jimenez A. On the Coupling of Orbit and Attitude Determination of Satellite Formations from Atmospheric Drag: Observability and Estimation Performance. [Internet] [Doctoral dissertation]. Delft University of Technology; 2020. [cited 2021 Mar 07]. Available from: http://resolver.tudelft.nl/uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; urn:NBN:nl:ui:24-uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; c333497d-05ac-422f-9688-31246a6fa7b1 ; 10.4233/uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; urn:isbn:978-94-028-2095-9 ; urn:NBN:nl:ui:24-uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; http://resolver.tudelft.nl/uuid:c333497d-05ac-422f-9688-31246a6fa7b1.

Council of Science Editors:

Chaves Jimenez A. On the Coupling of Orbit and Attitude Determination of Satellite Formations from Atmospheric Drag: Observability and Estimation Performance. [Doctoral Dissertation]. Delft University of Technology; 2020. Available from: http://resolver.tudelft.nl/uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; urn:NBN:nl:ui:24-uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; c333497d-05ac-422f-9688-31246a6fa7b1 ; 10.4233/uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; urn:isbn:978-94-028-2095-9 ; urn:NBN:nl:ui:24-uuid:c333497d-05ac-422f-9688-31246a6fa7b1 ; http://resolver.tudelft.nl/uuid:c333497d-05ac-422f-9688-31246a6fa7b1

Delft University of Technology

18. Andrés de la Fuente, J.I. Enhanced modelling of LAGEOS non-gravitational perturbations.

Degree: 2007, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; urn:NBN:nl:ui:24-uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; urn:NBN:nl:ui:24-uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; http://resolver.tudelft.nl/uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62

Subjects/Keywords: attitude dynamics; plasma physics; radiation theory; heat transfer; perturbation theory; orbit determination

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Andrés de la Fuente, J. I. (2007). Enhanced modelling of LAGEOS non-gravitational perturbations. (Doctoral Dissertation). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; urn:NBN:nl:ui:24-uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; urn:NBN:nl:ui:24-uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; http://resolver.tudelft.nl/uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62

Chicago Manual of Style (16^th Edition):

Andrés de la Fuente, J I. “Enhanced modelling of LAGEOS non-gravitational perturbations.” 2007. Doctoral Dissertation, Delft University of Technology. Accessed March 07, 2021. http://resolver.tudelft.nl/uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; urn:NBN:nl:ui:24-uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; urn:NBN:nl:ui:24-uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; http://resolver.tudelft.nl/uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62.

MLA Handbook (7^th Edition):

Andrés de la Fuente, J I. “Enhanced modelling of LAGEOS non-gravitational perturbations.” 2007. Web. 07 Mar 2021.

Vancouver:

Andrés de la Fuente JI. Enhanced modelling of LAGEOS non-gravitational perturbations. [Internet] [Doctoral dissertation]. Delft University of Technology; 2007. [cited 2021 Mar 07]. Available from: http://resolver.tudelft.nl/uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; urn:NBN:nl:ui:24-uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; urn:NBN:nl:ui:24-uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; http://resolver.tudelft.nl/uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62.

Council of Science Editors:

Andrés de la Fuente JI. Enhanced modelling of LAGEOS non-gravitational perturbations. [Doctoral Dissertation]. Delft University of Technology; 2007. Available from: http://resolver.tudelft.nl/uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; urn:NBN:nl:ui:24-uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; urn:NBN:nl:ui:24-uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62 ; http://resolver.tudelft.nl/uuid:bc15128e-6bfe-4992-962e-3c5f0a22ac62

York University

19. Dave, Siddharth Ghanshyam. Design and Prototype of a Phased-Array Antenna for Nanosatellite Radar and Communication Applications.

Degree: MSc -MS, Earth & Space Science, 2018, York University

URL: http://hdl.handle.net/10315/35523

► Reconfigurable software defined radios are capable of altering radio frequency parameters of a transceiver to add functionality and improve performance. Initially static by design, reconfigurable… (more)

Subjects/Keywords: Engineering; Alternating Current; Attitude Control System; Analog to Digital Converter; Antenna Under Test; Digital to Analog Converter; Decibels; Direct Current; Electromagnetic waves; Field Programmable Gate Array; Global Positioning System; High Frequency Simulation Software; Integrated Circuits; Intermediate Frequency; Low Earth Orbit; Left Hand Circular Polarization; Linear Polarization; Micro-electromechanical Systems; Phased Array Antenna; Printed Circuit Board; Reference Antenna; Radio Frequency; Right Hand Circular Polarization; Resident Space Objects; Space based Space Surveillance; Software-defined Radio; Satellite Laser Ranging; Sub-miniature version A connector; Signal to Noise Ratio; Space Surveillance Network; Ultra High Frequencies; Very High Frequency; Vector Network Analyzer; Reconfigurability; Micro-strip; Substrate; Array; Feed network; Centre Frequency; Relative Dielectric Permittivity; Speed of Light; Wave Factor; Wavelength; Conductivity; Impedance Function; Impedance; Voltage; Current; Length of Micro-strip; Width of Micro-strip

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Dave, S. G. (2018). Design and Prototype of a Phased-Array Antenna for Nanosatellite Radar and Communication Applications. (Masters Thesis). York University. Retrieved from http://hdl.handle.net/10315/35523

Chicago Manual of Style (16^th Edition):

Dave, Siddharth Ghanshyam. “Design and Prototype of a Phased-Array Antenna for Nanosatellite Radar and Communication Applications.” 2018. Masters Thesis, York University. Accessed March 07, 2021. http://hdl.handle.net/10315/35523.

MLA Handbook (7^th Edition):

Dave, Siddharth Ghanshyam. “Design and Prototype of a Phased-Array Antenna for Nanosatellite Radar and Communication Applications.” 2018. Web. 07 Mar 2021.

Vancouver:

Dave SG. Design and Prototype of a Phased-Array Antenna for Nanosatellite Radar and Communication Applications. [Internet] [Masters thesis]. York University; 2018. [cited 2021 Mar 07]. Available from: http://hdl.handle.net/10315/35523.

Council of Science Editors:

Dave SG. Design and Prototype of a Phased-Array Antenna for Nanosatellite Radar and Communication Applications. [Masters Thesis]. York University; 2018. Available from: http://hdl.handle.net/10315/35523

20. Hawe, Benjamin. Analysis of Passive Attitude Stabilisation and Deorbiting of Satellites in Low Earth Orbit.

Degree: Electrical and Space Engineering, 2016, Luleå University of Technology

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-60323

► Orbital debris poses a serious threat to ongoing operations in space. Recognising this threat, the European Commission has funded the three-year Technology for Self… (more)

▼ Orbital debris poses a serious threat to ongoing operations in space. Recognising this threat, the European Commission has funded the three-year Technology for Self Removal (TeSeR) project with the goal of developing a standard scalable Post Mission Disposal (PMD) module to remove satellites from orbit following the completion of their mission. As the project coordinator and key member of the TeSeR Project, Airbus Defence and Space Germany will invest significant resources in achieving this goal over the course of the project. This thesis details the initial analysis of potential PMD module designs conducted by the author during an internship within the AOCS/GNC department of Airbus Defence and Space Friedrichshafen between 1 April 2016 and 31 August 2016. Three main concepts, drag sails, drag balloons and Electrodynamic Tethers (EDTs), were evaluated during this time with an emphasis on determining the ability of each design to permit passive attitude stabilisation of the satellite during PMD. Following the required modification of a pre-existing MATLAB/Simulink model, several key findings were made for each device concept. It was found that no drag sail designs investigated permitted passive aerodynamic attitude stabilisation at orbit heights above 550 km. When deorbiting from 800 km, however, the lack of the desired and stable attitude was not found to have a significant increase on the deorbit time or the area‑time product. Drag balloon designs were predicted to be comparatively unstable and less mass efficient for deorbiting purposes, with area‑time products up to approximately 50 per cent higher than the equivalent mass drag sail designs. In spite of this, unstable drag balloons were found to provide shorter deorbit times than stable balloons due to the contribution of the satellite body and solar array to the total frontal area of the satellite. This indicated that attitude stabilisation is not required for satellites equipped with drag balloon devices. Modelling of bare EDTs suggested that tethers with lengths of 1000 metres or more would not permit passive attitude stabilisation at an orbit height of 800 km. Simulation of a 500 metre EDT, however, indicated that passive attitude stabilisation can be achieved with EDT devices and proved that EDTs can generate significantly higher drag forces than aerodynamic devices while possessing a significantly lower device mass. Following the analysis of these results, a recommendation was made for future work to be aimed at improving the EDT model used in this investigation.

Subjects/Keywords: electrodynamic; electrodynamic tether; EDT; drag augmentation; drag sail; drag balloon; passive attitude stabilisation; passive; attitude; stability; low earth orbit; LEO; deorbit; de-orbit; Post Mission Disposal; TeSeR; Aerospace Engineering; Rymd- och flygteknik

…the author’s internship within the Attitude and Orbit Control Systems/Guidance Navigation… …suggesting that active current control circuitry is required to prevent in-orbit-plane libration… …attitude stabilisation of the test satellite, the possibility to actively control the satellite… …4.3. EDTs Figure 5 shows the attitude of the satellite in an 800 km orbit with a 500 metre… …satellite in an 800 km equatorial orbit with a 500 metre EDT. Figure 6: Attitude of satellite in…

12 more images…

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Hawe, B. (2016). Analysis of Passive Attitude Stabilisation and Deorbiting of Satellites in Low Earth Orbit. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-60323

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Hawe, Benjamin. “Analysis of Passive Attitude Stabilisation and Deorbiting of Satellites in Low Earth Orbit.” 2016. Thesis, Luleå University of Technology. Accessed March 07, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-60323.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Hawe, Benjamin. “Analysis of Passive Attitude Stabilisation and Deorbiting of Satellites in Low Earth Orbit.” 2016. Web. 07 Mar 2021.

Vancouver:

Hawe B. Analysis of Passive Attitude Stabilisation and Deorbiting of Satellites in Low Earth Orbit. [Internet] [Thesis]. Luleå University of Technology; 2016. [cited 2021 Mar 07]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-60323.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Hawe B. Analysis of Passive Attitude Stabilisation and Deorbiting of Satellites in Low Earth Orbit. [Thesis]. Luleå University of Technology; 2016. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-60323

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

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