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Delft University of Technology
1.
Engwerda, H.J.A. (author).
Remote Sensing for Spatial Electrostatic Characterization using the Multi-Sphere Method.
Degree: 2017, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:37ee82df-d533-41fb-b6b8-a803c939cc4f 
► Focusing on the rapidly increasing debris population around Earth as well as the scientific and corporate interest in Asteroids, multiple missions for interaction with non-cooperative…
(more)
▼ Focusing on the rapidly increasing debris population around Earth as well as the scientific and corporate interest in Asteroids, multiple missions for interaction with non-cooperative bodies have been proposed over the last years. Applications such as the Electrostatic Tractor (ET) aiming to reduce the debris populations and missions introducing close proximity or even berthing with bodies in space all require knowledge about the electrostatic characteristics of the target. In order to infer this information in a real-time manner, the Remote Sensing for Electrostatic Characterization (RSEC) method can be applied. By measuring the ambient potential with probes extended from a dedicated spacecraft, an optimization can be performed as to find a best-fit Multi-Sphere Method (MSM) model. onsisting of a set of spheres with a point charge in their middle, this model approximates both the charge and potential of the rotating target. Comparing the in-situ measured potential with the potential obtained from the MSM model, the accuracy of the MSM model can be found and with it the model can be optimized. This thesis provides an extension of the RSEC method to three-dimensional space allowing for multi-axis tumbling motions of the target. Furthermore, simplifications of the model allowing for greater computational speed and simpler application are discussed. In order to validate the model, a Finite Element Analysis (FEA) is performed allowing the RSEC method to be tested for a representative missions scenario where the ET is applied. Based on the results of the FEA simulation, a Surface-MSM (SMSM) is constructed, allowing for multi-axis rotations of the debris, where this would be too computationally expensive with a FEA. The accuracy of force prediction within the ET method is assessed for a representative debris model. Furthermore, insights are offered in the effect of varying model parameters, and the influence of force mis-prediction on reorbiting time and fuel cost is evaluated.
Aerospace Engineering
Space Engineering
Space Flight
Advisors/Committee Members: Sundaramoorthy, P.P. (mentor).
Subjects/Keywords: electrostatic; space debris; sensing
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APA (6th Edition):
Engwerda, H. J. A. (. (2017). Remote Sensing for Spatial Electrostatic Characterization using the Multi-Sphere Method. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:37ee82df-d533-41fb-b6b8-a803c939cc4f
Chicago Manual of Style (16th Edition):
Engwerda, H J A (author). “Remote Sensing for Spatial Electrostatic Characterization using the Multi-Sphere Method.” 2017. Masters Thesis, Delft University of Technology. Accessed March 06, 2021.
http://resolver.tudelft.nl/uuid:37ee82df-d533-41fb-b6b8-a803c939cc4f.
MLA Handbook (7th Edition):
Engwerda, H J A (author). “Remote Sensing for Spatial Electrostatic Characterization using the Multi-Sphere Method.” 2017. Web. 06 Mar 2021.
Vancouver:
Engwerda HJA(. Remote Sensing for Spatial Electrostatic Characterization using the Multi-Sphere Method. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Mar 06].
Available from: http://resolver.tudelft.nl/uuid:37ee82df-d533-41fb-b6b8-a803c939cc4f.
Council of Science Editors:
Engwerda HJA(. Remote Sensing for Spatial Electrostatic Characterization using the Multi-Sphere Method. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:37ee82df-d533-41fb-b6b8-a803c939cc4f
University of Florida
2.
Scruggs, Thomas A.
Average Cross-sectional Area Calculation of DebriSat Fragments.
Degree: MS, Aerospace Engineering - Mechanical and Aerospace Engineering, 2017, University of Florida
URL: https://ufdc.ufl.edu/UFE0051111
► DebriSat is an ongoing effort at the University of Florida whose goal is to update the satellite standard breakup model used by the DOD and…
(more)
▼ DebriSat is an ongoing effort at the University of Florida whose goal is to update the satellite standard breakup model used by the DOD and NASA. In 2014 a representative 50 kg class satellite was subjected to a hypervelocity impact and the
debris from the impact is currently being characterized by the University of Florida. One of the key parameters in the standard breakup model is average cross-sectional area due to its use in determining the orbit lifetime of
debris fragments. Average cross-sectional area is defined as the average projected surface area of an object when viewed equally over four pi steradians.
Advisors/Committee Members: FITZ-COY,NORMAN G (committee chair).
Subjects/Keywords: debris – debrisat – measurement – space
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APA (6th Edition):
Scruggs, T. A. (2017). Average Cross-sectional Area Calculation of DebriSat Fragments. (Masters Thesis). University of Florida. Retrieved from https://ufdc.ufl.edu/UFE0051111
Chicago Manual of Style (16th Edition):
Scruggs, Thomas A. “Average Cross-sectional Area Calculation of DebriSat Fragments.” 2017. Masters Thesis, University of Florida. Accessed March 06, 2021.
https://ufdc.ufl.edu/UFE0051111.
MLA Handbook (7th Edition):
Scruggs, Thomas A. “Average Cross-sectional Area Calculation of DebriSat Fragments.” 2017. Web. 06 Mar 2021.
Vancouver:
Scruggs TA. Average Cross-sectional Area Calculation of DebriSat Fragments. [Internet] [Masters thesis]. University of Florida; 2017. [cited 2021 Mar 06].
Available from: https://ufdc.ufl.edu/UFE0051111.
Council of Science Editors:
Scruggs TA. Average Cross-sectional Area Calculation of DebriSat Fragments. [Masters Thesis]. University of Florida; 2017. Available from: https://ufdc.ufl.edu/UFE0051111
Virginia Tech
3.
Ohriner, Ethan Benjamin Lewis.
Investigation of Orbital Debris Situational Awareness with Constellation Design and Evaluation.
Degree: MS, Aerospace Engineering, 2021, Virginia Tech
URL: http://hdl.handle.net/10919/102096
► Orbital debris is defined as all non-operational, man-made objects currently in space. US national space regulations require every new satellite to have a de-orbit plan…
(more)
▼ Orbital
debris is defined as all non-operational, man-made objects currently in
space. US national
space regulations require every new satellite to have a de-orbit plan to prevent the creation of new
debris, but fails to address the thousands of derelict objects currently hindering
space operations. As
space traffic increases, so does the economic impact of orbital
debris on the sustainability of systems that increasingly support national security and commercial growth. While orbital
debris is usually assessed by looking at the full volume of
space, most massive
debris objects are concentrated in high-density clusters with a higher than normal probability for collision. A potential solution to the growing orbital
debris problem is to place a group of observation satellites within these
debris clusters to both improve monitoring capabilities and provide a means for preventing potential collisions by engaging with
debris via Laser
Debris Removal (LDR). This research presents a methodology for comparing and contrasting different observer satellite constellation designs. Our results show that increasingly complex orbit designs improve various performance criteria, but ultimately orbits that more closely match those of the
debris objects provide the best coverage. The proposed method of observation and engagement could significantly reduce the threat orbital
debris poses to
space operations and economic growth.
Advisors/Committee Members: Black, Jonathan T. (committeechair), Shinpaugh, Kevin A. (committee member), VanDyke, Matthew Clark (committee member).
Subjects/Keywords: orbital debris; laser debris removal; constellation design; space situational awareness
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APA (6th Edition):
Ohriner, E. B. L. (2021). Investigation of Orbital Debris Situational Awareness with Constellation Design and Evaluation. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/102096
Chicago Manual of Style (16th Edition):
Ohriner, Ethan Benjamin Lewis. “Investigation of Orbital Debris Situational Awareness with Constellation Design and Evaluation.” 2021. Masters Thesis, Virginia Tech. Accessed March 06, 2021.
http://hdl.handle.net/10919/102096.
MLA Handbook (7th Edition):
Ohriner, Ethan Benjamin Lewis. “Investigation of Orbital Debris Situational Awareness with Constellation Design and Evaluation.” 2021. Web. 06 Mar 2021.
Vancouver:
Ohriner EBL. Investigation of Orbital Debris Situational Awareness with Constellation Design and Evaluation. [Internet] [Masters thesis]. Virginia Tech; 2021. [cited 2021 Mar 06].
Available from: http://hdl.handle.net/10919/102096.
Council of Science Editors:
Ohriner EBL. Investigation of Orbital Debris Situational Awareness with Constellation Design and Evaluation. [Masters Thesis]. Virginia Tech; 2021. Available from: http://hdl.handle.net/10919/102096
Columbia University
4.
Hendel, David Anthony.
Dynamics and Detection of Tidal Debris.
Degree: 2018, Columbia University
URL: https://doi.org/10.7916/D8475TJP
► Tidal debris structures are striking evidence of hierarchical assembly – the premise that the Milky Way and galaxies like it have been built over cosmic…
(more)
▼ Tidal debris structures are striking evidence of hierarchical assembly – the premise that the Milky Way and galaxies like it have been built over cosmic time through the coalescence of many smaller objects. In the prevailing Lambda – Cold Dark Matter cosmology, the vast majority of mergers by number are minor; one dark matter halo, hosting a larger galaxy, dominates the interaction and a smaller object, the satellite, is stripped of mass by tidal forces. When the luminous component of the satellite is disrupted the debris may form structures such as stellar tidal streams or shells, depending on the parameters of the interaction. In this Thesis we examine the properties of this debris left behind by minor mergers theoretically, computationally, and observationally, making strides towards a more complete understanding of what tidal debris can tell us about the history of galaxy formation in the Universe.
Around the Milky Way itself we have examined the properties of the Orphan Stream, a stellar tidal stream so named due to uncertainty about the position and current state of its progenitor. Using 3.6 um observations taken as part of the Spitzer Merger History and Shape of the Galactic Halo program, the latest period – luminosity – metallicity relations, and archival data, we compute precise distances to RR Lyrae stream members with state – of – the – art 2.5% relative uncertainties. Fitting an orbit to the data, we measure an enclosed mass for the Milky Way that is in good agreement with other recent results, once the biases in orbit fitting are taken into account. By applying the same technique to N – body simulations we determined that the Orphan progenitor is most likely similar to the classical dwarf spheroidal satellites.
We also examined tidal debris more generally, in particular by investigating the source of the morphological dichotomy between shells and streams. We find that the transition from a stream – like to a shell – like morphology occurs when the differential azimuthal precession between the orbits of stars exceeds the position angle subtended by individual petals of the progenitor orbit's rosette. This statement is cast more precisely in terms of scaling relations that control the dispersion of energy and angular momentum in the debris, and we find that the observed morphology can be predicted for a given host, orbit, and mass ratio. This leads us to the idea that the observed occurrence rates of different morphologies can be used to recover, at the population statistics level, the progenitor satellites' orbital infall distribution. This a part of the cosmological accretion history that is otherwise inaccessible. To achieve this in practice requires an unbiased and automated method to detect and classify substructure; we have developed just such a tool and demonstrate its effectiveness. In the upcoming era of LSST and WFIRST the methods and insights developed in this Thesis will be useful in decoding the information about the current state and assembly of galaxies encoded in tidal debris.
Subjects/Keywords: Astronomy; Astrophysics; Galaxies – Formation; Space debris
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APA (6th Edition):
Hendel, D. A. (2018). Dynamics and Detection of Tidal Debris. (Doctoral Dissertation). Columbia University. Retrieved from https://doi.org/10.7916/D8475TJP
Chicago Manual of Style (16th Edition):
Hendel, David Anthony. “Dynamics and Detection of Tidal Debris.” 2018. Doctoral Dissertation, Columbia University. Accessed March 06, 2021.
https://doi.org/10.7916/D8475TJP.
MLA Handbook (7th Edition):
Hendel, David Anthony. “Dynamics and Detection of Tidal Debris.” 2018. Web. 06 Mar 2021.
Vancouver:
Hendel DA. Dynamics and Detection of Tidal Debris. [Internet] [Doctoral dissertation]. Columbia University; 2018. [cited 2021 Mar 06].
Available from: https://doi.org/10.7916/D8475TJP.
Council of Science Editors:
Hendel DA. Dynamics and Detection of Tidal Debris. [Doctoral Dissertation]. Columbia University; 2018. Available from: https://doi.org/10.7916/D8475TJP
University of Colorado
5.
Albuja, Antonella A.
Rotational Dynamics of Inactive Satellites as a Result of the YORP Effect.
Degree: PhD, Aerospace Engineering Sciences, 2015, University of Colorado
URL: https://scholar.colorado.edu/asen_gradetds/113
► Observations of inactive satellites in Earth orbit show that these objects are generally rotating, some with very fast rotation rates. In addition, observations indicate…
(more)
▼ Observations of inactive satellites in Earth orbit show that these objects are generally rotating, some with very fast rotation rates. In addition, observations indicate that the rotation rate at which defunct satellites spin tends to evolve over time. However, the cause for this behavior is unknown. The observed secular change in the spin rate and spin axis orientation of asteroids is known to be caused by the Yarkovsky-O'Keefe-Radzievskii-Paddack (YORP) effect, which results in a torque that is created from reflected thermal energy and sunlight from the surface of an asteroid. This thesis explores the effect of YORP on defunct satellites in Earth orbit and offers this as a potential cause for the observed rotation states of inactive satellites. In this work, several different satellite models are developed to represent inactive satellites in Geostationary Earth Orbit (GEO). The evolution of the spin rate and obliquity for each satellite is then explored using Euler's equations of motion as well as spin and year averaged dynamics. This results in the dynamics being analyzed to understand the secular changes that occur, as well as the variations that result from short period terms over the course of a year. Some of the model satellites have asymmetric geometries, leading to the classical YORP effect as originally formulated for asteroids. One model satellite is geometrically symmetric, but relies on mass distribution asymmetry to generate the YORP effect. Because the YORP effect is directly dependent on geometric, optical and thermal properties of the satellite, varying these parameters can lead to different long-term rotational behavior. A sensitivity study is done by varying these parameters and analyzing its effect on the long-term dynamics of a satellite. Additionally, available observation data of inactive GEO satellites are used to estimate the YORP torque acting on those bodies. A comparison between this torque and the expected torque on a defunct satellite shows that the two are of the same order of magnitude, demonstrating that YORP could be a cause for the observed behavior.
Advisors/Committee Members: Daniel J. Scheeres, Hanspeter Schaub, Jay McMahon, James Meiss, Moriba Jah.
Subjects/Keywords: space debris; Co coefficient; GOES; Aerospace Engineering
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APA (6th Edition):
Albuja, A. A. (2015). Rotational Dynamics of Inactive Satellites as a Result of the YORP Effect. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/113
Chicago Manual of Style (16th Edition):
Albuja, Antonella A. “Rotational Dynamics of Inactive Satellites as a Result of the YORP Effect.” 2015. Doctoral Dissertation, University of Colorado. Accessed March 06, 2021.
https://scholar.colorado.edu/asen_gradetds/113.
MLA Handbook (7th Edition):
Albuja, Antonella A. “Rotational Dynamics of Inactive Satellites as a Result of the YORP Effect.” 2015. Web. 06 Mar 2021.
Vancouver:
Albuja AA. Rotational Dynamics of Inactive Satellites as a Result of the YORP Effect. [Internet] [Doctoral dissertation]. University of Colorado; 2015. [cited 2021 Mar 06].
Available from: https://scholar.colorado.edu/asen_gradetds/113.
Council of Science Editors:
Albuja AA. Rotational Dynamics of Inactive Satellites as a Result of the YORP Effect. [Doctoral Dissertation]. University of Colorado; 2015. Available from: https://scholar.colorado.edu/asen_gradetds/113
Delft University of Technology
6.
Srongprapa, P. (author).
Mapping the Effects of Earth’s Gravity Field on the Orbit Propagation of GTO Spacecraft: A study within the context of passive de-orbiting through the use of perturbations.
Degree: 2015, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:3170c8dc-d5b6-4d01-a03e-6b13cc2c5d1b
► A geostationary transfer orbit (GTO) is typically used to inject spacecraft into the geosta- tionary orbit. There are many inoperative launcher upper stages and other…
(more)
▼ A geostationary transfer orbit (GTO) is typically used to inject spacecraft into the geosta- tionary orbit. There are many inoperative launcher upper stages and other fragments or- biting in GTOs. These parts collide and disintegrate, becoming even smaller fragments and thereby worsening the problem of
space debris. The objects could also collide with op- erational spacecraft. For this reason, a cost-effective method to de-orbit launcher upper stages from GTOs after their end-of-life is needed. Passive de-orbiting using orbital pertur- bations is one such method. A previous work performed at the University of Southampton proposed the use of luni-solar perturbations and secular effects of Earth’s gravity field for passive de-orbiting from highly elliptical orbits (HEOs). A particular type of perturbation not yet investigated in the study of perturbations-enhanced de-orbiting is the periodic ef- fects in the spherical harmonics of Earth’s gravity field model. The thesis work is focused on studying the effect of the gravitational field of Earth (rep- resented by spherical harmonics) on the long-term evolution of upper stages. First, a reli- able and validated algorithm is needed to model the complete Earth’s spherical harmonics. For this purpose, different algorithms are discussed. It is found that Cunningham’s algo- rithm is more reliable for elliptical orbits, and also more computationally efficient, than Kaula’s algorithm. However, Kaula’s algorithm is more versatile and therefore codes based on Kaula’s algorithm were developed into different programs for different types of perturba- tions. These include the secular-only perturbations, zonal harmonics, tesseral harmonics, and averaged perturbations. Although Cunningham’s algorithm was chosen for mapping due to its efficiency, the implementations of Kaula’s algorithm provide an opportunity for future research on the propagation of orbital elements. After the perturbation models had been validated, maps were created for the purpose of investigating the effects of orbital perturbations on de-orbiting. Starting with luni-solar (third-body) and J2 perturbations, the secular effects from higher-order zonal harmonics were added. This increase in the order of spherical harmonics had no significant impact on the results (the difference in perigee altitude between J2 and order 6 zonal harmonics with only secular effects is in the order of 0.5 km). On top of these perturbations, it was found that the addition of periodic effects (as opposed to having only secular effects in the Earth’s spherical harmonics model) made a small difference in the simulated perigee alti- tude. Here, the difference in the perigee altitude between the secular and periodic effects is in the order of 5 km). Not including the non-secular perturbations would lead to a more conservative prediction of lifetime. Solar radiation pressure and drag perturbations were later added to the maps. Increas- ing the area-to-mass ratio of the spacecraft would increase the impact of solar radiation pressure and drag on…
Advisors/Committee Members: Noomen, R. (mentor).
Subjects/Keywords: deorbit; space; debris; perturbations; gravity; harmonics; lifetime
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APA (6th Edition):
Srongprapa, P. (. (2015). Mapping the Effects of Earth’s Gravity Field on the Orbit Propagation of GTO Spacecraft: A study within the context of passive de-orbiting through the use of perturbations. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:3170c8dc-d5b6-4d01-a03e-6b13cc2c5d1b
Chicago Manual of Style (16th Edition):
Srongprapa, P (author). “Mapping the Effects of Earth’s Gravity Field on the Orbit Propagation of GTO Spacecraft: A study within the context of passive de-orbiting through the use of perturbations.” 2015. Masters Thesis, Delft University of Technology. Accessed March 06, 2021.
http://resolver.tudelft.nl/uuid:3170c8dc-d5b6-4d01-a03e-6b13cc2c5d1b.
MLA Handbook (7th Edition):
Srongprapa, P (author). “Mapping the Effects of Earth’s Gravity Field on the Orbit Propagation of GTO Spacecraft: A study within the context of passive de-orbiting through the use of perturbations.” 2015. Web. 06 Mar 2021.
Vancouver:
Srongprapa P(. Mapping the Effects of Earth’s Gravity Field on the Orbit Propagation of GTO Spacecraft: A study within the context of passive de-orbiting through the use of perturbations. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Mar 06].
Available from: http://resolver.tudelft.nl/uuid:3170c8dc-d5b6-4d01-a03e-6b13cc2c5d1b.
Council of Science Editors:
Srongprapa P(. Mapping the Effects of Earth’s Gravity Field on the Orbit Propagation of GTO Spacecraft: A study within the context of passive de-orbiting through the use of perturbations. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:3170c8dc-d5b6-4d01-a03e-6b13cc2c5d1b
Cal Poly
7.
Jackson, Daniel J.
Formulation of an Optimal Search Strategy for Space Debris At GEO.
Degree: MS, Aerospace Engineering, 2011, Cal Poly
URL: https://digitalcommons.calpoly.edu/theses/656
;
10.15368/theses.2011.202
► The purpose of this thesis is to create a search strategy to find orbital debris when the object fails to appear in the sky…
(more)
▼ The purpose of this thesis is to create a search strategy to find orbital
debris when the object fails to appear in the sky at its predicted location. This project is for NASA Johnson
Space Center Orbital
Debris Program Office through the MODEST (Michigan Orbital
Debris Survey Telescope) program. This thesis will build upon the research already done by James Biehl in “Formulation of a Search Strategy for
Space Debris at GEO.” MODEST tracks objects at a specific right ascension and declination. A circular orbit assumption is then used to predict the location of the object at a later time. Another telescope performs a follow-up to the original observation to provide a more accurate orbit predication. This thesis develops a search strategy when the follow-up is not successful. A general search strategy for finding
space debris was developed based on previous observations. A GUI was also generated to find a search strategy in real-time for a specific object based upon previous observations of that object.
Search strategies were found by adding a 2% mean random error to the position and velocity vectors. Adding a random error allows for finding the most likely location of
space debris when the orbital elements are slightly incorrect. A bivariate kernel density estimator was used to find the probability density function. The probability density function was used to find the most probable location of an object. A correlation between error in the orbital elements and error in right ascension and declination root mean square (RMS) error was investigated. It was found that the orbital elements affect the RMS error nonlinearly, but the relation between orbital element and error depended on the object and no general pattern was found. It was found that how long after the original object was found until the follow-up was attempted did not have a large impact on the probability density function or the search strategy.
Advisors/Committee Members: Kira Abercromby.
Subjects/Keywords: aerospace; space; debris; GEO; telescope; MODEST; Astrodynamics
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APA (6th Edition):
Jackson, D. J. (2011). Formulation of an Optimal Search Strategy for Space Debris At GEO. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/656 ; 10.15368/theses.2011.202
Chicago Manual of Style (16th Edition):
Jackson, Daniel J. “Formulation of an Optimal Search Strategy for Space Debris At GEO.” 2011. Masters Thesis, Cal Poly. Accessed March 06, 2021.
https://digitalcommons.calpoly.edu/theses/656 ; 10.15368/theses.2011.202.
MLA Handbook (7th Edition):
Jackson, Daniel J. “Formulation of an Optimal Search Strategy for Space Debris At GEO.” 2011. Web. 06 Mar 2021.
Vancouver:
Jackson DJ. Formulation of an Optimal Search Strategy for Space Debris At GEO. [Internet] [Masters thesis]. Cal Poly; 2011. [cited 2021 Mar 06].
Available from: https://digitalcommons.calpoly.edu/theses/656 ; 10.15368/theses.2011.202.
Council of Science Editors:
Jackson DJ. Formulation of an Optimal Search Strategy for Space Debris At GEO. [Masters Thesis]. Cal Poly; 2011. Available from: https://digitalcommons.calpoly.edu/theses/656 ; 10.15368/theses.2011.202
University of Delaware
8.
Cwalina, Colin D.
Shear thickening fluids for enhanced protection from micrometeoroids and orbital debris.
Degree: PhD, University of Delaware, Department of Chemical and Biomolecular Engineering, 2016, University of Delaware
URL: http://udspace.udel.edu/handle/19716/17739
► In October 2015, after the discovery of liquid water on the surface of Mars, NASA declared that the coming decades will see a renewed push…
(more)
▼ In October 2015, after the discovery of liquid water on the surface of Mars, NASA declared that the coming decades will see a renewed push to establish “a sustainable human presence beyond Earth, not just to visit but to stay”. A challenge for deep-
space missions to Mars and beyond will be the construction of
space vehicles, habitats, and extra-vehicular activity (EVA) suits capable of withstanding the threats from micrometeoroids and orbital
debris (MMOD). MMOD particles, while typically small in size, travel at extraordinary velocities in low-earth orbit (LEO)—on the order of 1-15 km/s (~2,200-33,000 mph)—rendering them highly energetic and dangerous to exposed astronauts performing EVAs.
This dissertation explores using a novel soft body armor technology that intercalates colloidal shear thickening fluids (STFs) into protective textiles, i.e., STF-ArmorTTM, to improve the resistance of EVA suits to hypervelocity MMOD threats. STF-ArmorTM has previously been demonstrated to improve resistance to puncture, ballistic, and shock threats–all elements inherent to MMOD projectiles. Under the terrestrial testing conditions explored in this dissertation, incorporation of STF-ArmorTM into the EVA suit significantly enhanced the resistance to puncture threats and increased specific energy absorption when the projectile was traveling at velocities sufficiently high enough to induce fragmentation upon impact. These results demonstrate proof-of-concept and advance the Technology Readiness Level (TRL) of STF-ArmorTM to the point where the next step of technology validation will take place in the actual LEO environment on the exterior of the International
Space Station.
The intended application motivates some fundamental questions about the effect of confinement on the measured deviatoric stress—the shear stress and the first and second normal stress differences—within the underlying colloidal dispersion. Improved experimental measurements of these viscometric functions were obtained via controlled-stress rheometry. The magnitude and scaling of the viscometric functions were found to be consistent with expectations from Stokesian Dynamics simulations, Dissipative Particle Dynamics simulations, and theory that properly accounts for hydrodynamic interactions between particles at high shear rates. In STF-ArmorTM, concentrated colloidal dispersions are confined to micron-sized gaps between yarn fibrils, a degree of confinement not accessible with current rheometry techniques. A novel experimental approach was developed to study the effects of extreme confinement on the measured deviatoric stress, where the colloidal dispersion was confined not between the plates of a rheometer tooling, but rather between the surfaces of large, non-deformable non-Brownian particles at high packing fractions. At high shear rates, confinement was found to lead to stronger shear thickening and enhanced normal stress differences. Ultimately, the findings of this dissertation help to advance fundamental understanding of the flow behavior of…
Advisors/Committee Members: Wagner, Norman J..
Subjects/Keywords: Meteoroids.; Space debris.; Extravehicular space suits.; Colloids.; Textile fabrics.
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APA (6th Edition):
Cwalina, C. D. (2016). Shear thickening fluids for enhanced protection from micrometeoroids and orbital debris. (Doctoral Dissertation). University of Delaware. Retrieved from http://udspace.udel.edu/handle/19716/17739
Chicago Manual of Style (16th Edition):
Cwalina, Colin D. “Shear thickening fluids for enhanced protection from micrometeoroids and orbital debris.” 2016. Doctoral Dissertation, University of Delaware. Accessed March 06, 2021.
http://udspace.udel.edu/handle/19716/17739.
MLA Handbook (7th Edition):
Cwalina, Colin D. “Shear thickening fluids for enhanced protection from micrometeoroids and orbital debris.” 2016. Web. 06 Mar 2021.
Vancouver:
Cwalina CD. Shear thickening fluids for enhanced protection from micrometeoroids and orbital debris. [Internet] [Doctoral dissertation]. University of Delaware; 2016. [cited 2021 Mar 06].
Available from: http://udspace.udel.edu/handle/19716/17739.
Council of Science Editors:
Cwalina CD. Shear thickening fluids for enhanced protection from micrometeoroids and orbital debris. [Doctoral Dissertation]. University of Delaware; 2016. Available from: http://udspace.udel.edu/handle/19716/17739
Cranfield University
9.
Palla, Chiara.
Development of drag augmentation systems for de-orbiting small satellites.
Degree: 2017, Cranfield University
URL: http://dspace.lib.cranfield.ac.uk/handle/1826/14327
► The adoption of the ISO 24113 by ESA in 2014 has set an important milestone for the path towards an evolution and worldwide compliance of…
(more)
▼ The adoption of the ISO 24113 by ESA in 2014 has set an important milestone
for the path towards an evolution and worldwide compliance of the Space Debris
Mitigation (SDM) requirements.
Small spacecraft classes have limited propulsion capabilities or even they are
not provided with propulsion subsystem to achieve a controlled re-entry. This issue
brings the need to develop affordable de-orbiting technologies with a limited reliance
on the system level performance, ideally largely passive methods.
The main aim of this research is to develop passive drag augmentation systems
(DAS) for de-orbiting small spacecraft at the end of life, enabling them to comply
with SDM requirements.
After a feasibility study for the potential commercial use of DAS, the satellites’
need for passive de-orbiting technologies is investigated through market forecast and
future scenarios of spacecraft compliance to the 25 years re-entry requirement.
Spacecraft subsystems failures are analysed statistically to assess how they might
impact the end of mission phase and to guide in the de-orbiting strategy selection.
The applicability of current Cranfield DAS design is assessed by developing a
simple model for preliminary drag area calculation, validating it with STELA and
DRAMA, and calculating the additional area needed vs the area provided by DAS
for a spacecraft sample.
The requirements for DAS are analysed considering the customer’s needs with
respect to the internal design drivers. A design parameters analysis is performed to
evaluate the scalability of the DAS and their compatibility with satellite platforms.
The parametric study together with the requirements analysis provide useful input
to explore new concepts based on the heritage designs.
In parallel, the De-Orbit Mechanism (DOM) technological demonstrator is developed
from prototype model up to flight model, after undergoing qualification test
campaign. The DOM will fly on board the upcoming ESA ESEO mission.
This research will enable a commercial DAS products offering that will be an
attractive solution for small satellite integrators, allowing them to meet debris mitigation
requirements.
Subjects/Keywords: Space debris mitigation; clean space; de-orbiting; drag augmentation
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MLA ·
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CSE |
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APA (6th Edition):
Palla, C. (2017). Development of drag augmentation systems for de-orbiting small satellites. (Thesis). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/14327
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Palla, Chiara. “Development of drag augmentation systems for de-orbiting small satellites.” 2017. Thesis, Cranfield University. Accessed March 06, 2021.
http://dspace.lib.cranfield.ac.uk/handle/1826/14327.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Palla, Chiara. “Development of drag augmentation systems for de-orbiting small satellites.” 2017. Web. 06 Mar 2021.
Vancouver:
Palla C. Development of drag augmentation systems for de-orbiting small satellites. [Internet] [Thesis]. Cranfield University; 2017. [cited 2021 Mar 06].
Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/14327.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Palla C. Development of drag augmentation systems for de-orbiting small satellites. [Thesis]. Cranfield University; 2017. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/14327
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Cranfield University
10.
Palla, Chiara.
Development of drag augmentation systems for de-orbiting small satellites.
Degree: PhD, 2017, Cranfield University
URL: http://dspace.lib.cranfield.ac.uk/handle/1826/14327
;
https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783261
► The adoption of the ISO 24113 by ESA in 2014 has set an important milestone for the path towards an evolution and worldwide compliance of…
(more)
▼ The adoption of the ISO 24113 by ESA in 2014 has set an important milestone for the path towards an evolution and worldwide compliance of the Space Debris Mitigation (SDM) requirements. Small spacecraft classes have limited propulsion capabilities or even they are not provided with propulsion subsystem to achieve a controlled re-entry. This issue brings the need to develop affordable de-orbiting technologies with a limited reliance on the system level performance, ideally largely passive methods. The main aim of this research is to develop passive drag augmentation systems (DAS) for de-orbiting small spacecraft at the end of life, enabling them to comply with SDM requirements. After a feasibility study for the potential commercial use of DAS, the satellites' need for passive de-orbiting technologies is investigated through market forecast and future scenarios of spacecraft compliance to the 25 years re-entry requirement. Spacecraft subsystems failures are analysed statistically to assess how they might impact the end of mission phase and to guide in the de-orbiting strategy selection. The applicability of current Cranfield DAS design is assessed by developing a simple model for preliminary drag area calculation, validating it with STELA and DRAMA, and calculating the additional area needed vs the area provided by DAS for a spacecraft sample. The requirements for DAS are analysed considering the customer's needs with respect to the internal design drivers. A design parameters analysis is performed to evaluate the scalability of the DAS and their compatibility with satellite platforms. The parametric study together with the requirements analysis provide useful input to explore new concepts based on the heritage designs. In parallel, the De-Orbit Mechanism (DOM) technological demonstrator is developed from prototype model up to flight model, after undergoing qualification test campaign. The DOM will fly on board the upcoming ESA ESEO mission. This research will enable a commercial DAS products offering that will be an attractive solution for small satellite integrators, allowing them to meet debris mitigation requirements.
Subjects/Keywords: Space debris mitigation; clean space; de-orbiting; drag augmentation
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APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Palla, C. (2017). Development of drag augmentation systems for de-orbiting small satellites. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/14327 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783261
Chicago Manual of Style (16th Edition):
Palla, Chiara. “Development of drag augmentation systems for de-orbiting small satellites.” 2017. Doctoral Dissertation, Cranfield University. Accessed March 06, 2021.
http://dspace.lib.cranfield.ac.uk/handle/1826/14327 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783261.
MLA Handbook (7th Edition):
Palla, Chiara. “Development of drag augmentation systems for de-orbiting small satellites.” 2017. Web. 06 Mar 2021.
Vancouver:
Palla C. Development of drag augmentation systems for de-orbiting small satellites. [Internet] [Doctoral dissertation]. Cranfield University; 2017. [cited 2021 Mar 06].
Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/14327 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783261.
Council of Science Editors:
Palla C. Development of drag augmentation systems for de-orbiting small satellites. [Doctoral Dissertation]. Cranfield University; 2017. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/14327 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783261
11.
Madakat, Dalal.
Approches multicritères pour le traitement des débris spatiaux : Multicriteria approaches for space debris removal.
Degree: Docteur es, Informatique, 2014, Paris 9
URL: http://www.theses.fr/2014PA090019
► Les débris spatiaux constituent une menace pour l'exploration et l'exploitation de l'espace. Leur nombre ne cesse d'augmenter et continuera à grandir même si on arrête…
(more)
▼ Les débris spatiaux constituent une menace pour l'exploration et l'exploitation de l'espace. Leur nombre ne cesse d'augmenter et continuera à grandir même si on arrête toute activité spatiale, augmentant ainsi la probabilité d'entrer en collision avec un satellite actif. Le retrait des débris s'avère le seul moyen de protéger ces satellites. Le nombre des débris spatiaux étant très élevé, il convient préalablement de repérer les plus dangereux.Dans la première partie de la thèse, nous avons élaboré une approche multicritère afin de classer les débris selon leur degré de priorité d'enlèvement. Les débris de la classe la plus prioritaire, feront l'objet d'une mission spatiale de retrait de débris.La planification d'une telle mission est étudiée dans la deuxième partie de la thèse. Elle doit être réalisée en minimisant deux critères : le coût de la mission ainsi que la durée nécessaire pour traiter tous les débris.
Space debris are a threat for the space exploitation and exploration. Their number will continue to increase even if we stop all space activities, making collisions between debris and operational satellites more likely to happen. Debris removal proves necessary to protect active satellites. Since the number of space debris is very high, we should first deal with the most dangerous ones.In the first part of this thesis, we have developed a multicriteria approach to categorize debris depending on their removal priority degree. Debris belonging to the most urgent category will be dealt with during a space mission. The planning of such a space mission is studied in the second part of this thesis.The planning should be designed while optimizing two criteria: mission cost and mission duration.
Advisors/Committee Members: Vanderpooten, Daniel (thesis director).
Subjects/Keywords: Débris spatiaux; Catégorisation; Planification; Space debris; Categorization; Space missions planning; 003
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APA ·
Chicago ·
MLA ·
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CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Madakat, D. (2014). Approches multicritères pour le traitement des débris spatiaux : Multicriteria approaches for space debris removal. (Doctoral Dissertation). Paris 9. Retrieved from http://www.theses.fr/2014PA090019
Chicago Manual of Style (16th Edition):
Madakat, Dalal. “Approches multicritères pour le traitement des débris spatiaux : Multicriteria approaches for space debris removal.” 2014. Doctoral Dissertation, Paris 9. Accessed March 06, 2021.
http://www.theses.fr/2014PA090019.
MLA Handbook (7th Edition):
Madakat, Dalal. “Approches multicritères pour le traitement des débris spatiaux : Multicriteria approaches for space debris removal.” 2014. Web. 06 Mar 2021.
Vancouver:
Madakat D. Approches multicritères pour le traitement des débris spatiaux : Multicriteria approaches for space debris removal. [Internet] [Doctoral dissertation]. Paris 9; 2014. [cited 2021 Mar 06].
Available from: http://www.theses.fr/2014PA090019.
Council of Science Editors:
Madakat D. Approches multicritères pour le traitement des débris spatiaux : Multicriteria approaches for space debris removal. [Doctoral Dissertation]. Paris 9; 2014. Available from: http://www.theses.fr/2014PA090019
University of Colorado
12.
Jasper, Lee E.Z.
Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects.
Degree: PhD, Aerospace Engineering Sciences, 2014, University of Colorado
URL: https://scholar.colorado.edu/asen_gradetds/82
► Towing objects in space has become an increasingly researched mission concept. Active debris removal, satellite servicing, and asteroid retrieval concepts in many cases rely…
(more)
▼ Towing objects in
space has become an increasingly researched mission concept. Active
debris removal, satellite servicing, and asteroid retrieval concepts in many cases rely on a thrusting vehicle to redirect and steer a passive object. Focus is often placed on the method of attachment, considering techniques such as grappling or netting the passive object. However, the actual process of towing, once capture has occurred, has not yet received much attention. This research considers the process of towing in
space with the tug and passive object attached by a tether. Tethers are not only an effective way of transmitting forces, but they are utilized on many of the towing concepts considered, especially in orbital
debris removal.
Because the two end bodies are tethered, there is a potential for collision after any maneuver. To avoid collisions, the maneuver, and therefore thrust profile, must be designed in such a way as to limit separation distance reduction between the end bodies. Open-loop input shaping techniques are developed and employed in order to control the flexible system in both deep
space and on-orbit environments. To study the behavior, an active
debris removal system is proposed as a case study. This system, called the tethered-tug, considers using the reserve fuel from a recently launched upper stage rocket to rendezvous with, capture, and tow a near-by
debris object.
The system’s performance is considered for five distinct open-loop thrust control profiles including on-off/step, frequency notched, discretized notch, Posicast, and bang-off-bang. Tether property variations are also considered along with off-axis towing, slack tethers, and
debris with initial rotation rates. Input shaping is not only necessary but, it can be robust to unknown system properties while nearly zeroing relative motion between the end bodies. When considering on-orbit behavior specifically, the system settles into a tumbling or gravity gradient oscillation formation. This is highly advantageous because the orbital dynamics keep the end bodies separated. While the study focuses on the
debris problem, conclusions from this dissertation are applicable to general tethered towing mission concepts.
Advisors/Committee Members: Hanspeter Schaub, John K. Bennett, Brandon Jones, Jeffrey Parker, Daniel Scheeres.
Subjects/Keywords: active debris removal; input shaping; orbital debris; space tether; tethered towing; Aerospace Engineering
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APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Jasper, L. E. Z. (2014). Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/82
Chicago Manual of Style (16th Edition):
Jasper, Lee E Z. “Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects.” 2014. Doctoral Dissertation, University of Colorado. Accessed March 06, 2021.
https://scholar.colorado.edu/asen_gradetds/82.
MLA Handbook (7th Edition):
Jasper, Lee E Z. “Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects.” 2014. Web. 06 Mar 2021.
Vancouver:
Jasper LEZ. Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects. [Internet] [Doctoral dissertation]. University of Colorado; 2014. [cited 2021 Mar 06].
Available from: https://scholar.colorado.edu/asen_gradetds/82.
Council of Science Editors:
Jasper LEZ. Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects. [Doctoral Dissertation]. University of Colorado; 2014. Available from: https://scholar.colorado.edu/asen_gradetds/82
Delft University of Technology
13.
Singh, Sunayna (author).
Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages.
Degree: 2019, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:625c408b-97ae-47a5-90c9-493dc4bc0224
► The space environment is ever-changing with space structures getting larger and the orbits getting increasingly crowded with time. This creates a need for removal of…
(more)
▼ The space environment is ever-changing with space structures getting larger and the orbits getting increasingly crowded with time. This creates a need for removal of large defunct satellites to avoid the disastrous Kessler syndrome, which poses a major threat to the future of space exploration. This research examines the dynamics and control involved in the active removal of a large space debris - Envisat. European Space Agency's e.deorbit mission aims to de-orbit Envisat using a chaser satellite, which synchronises, docks, detumbles and deorbits it. The presence of large flexible appendages makes the configuration prone to elastic perturbations leading to complex dynamics that cannot be represented using rigid body dynamics. Therefore, a unique multibody approach based on the absolute interface coordinates in the floating frame formulation is used to model the Flexible Multibody Dynamics. The novel method proves to provide a good balance between computation time and efficiency for the control application. The controllability characteristics of two phases of the e.deorbit mission are analysed using a linear PD controller and an Incremental Nonlinear Dynamic Inversion controller. For the first phase, both controllers successfully synchronise the chaser with the target debris tumbling at the rate of 3.5 deg/s about all axes. However, during the detumbling phase, the large appendage (14.2 m) in the stacked configuration introduces complex dynamics, which could not be stabilised completely by applied controllers. Nonetheless, interesting relationships could be established between the dynamics and control of the system, which will facilitate robust control design in future work.
Aerospace Engineering
Advisors/Committee Members: Mooij, Erwin (mentor), Gransden, Derek (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: Space debris; multibody dynamics; Flexible structures; Control; Active debris removal; floating frames
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APA ·
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Export
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Manager
APA (6th Edition):
Singh, S. (. (2019). Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:625c408b-97ae-47a5-90c9-493dc4bc0224
Chicago Manual of Style (16th Edition):
Singh, Sunayna (author). “Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages.” 2019. Masters Thesis, Delft University of Technology. Accessed March 06, 2021.
http://resolver.tudelft.nl/uuid:625c408b-97ae-47a5-90c9-493dc4bc0224.
MLA Handbook (7th Edition):
Singh, Sunayna (author). “Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages.” 2019. Web. 06 Mar 2021.
Vancouver:
Singh S(. Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages. [Internet] [Masters thesis]. Delft University of Technology; 2019. [cited 2021 Mar 06].
Available from: http://resolver.tudelft.nl/uuid:625c408b-97ae-47a5-90c9-493dc4bc0224.
Council of Science Editors:
Singh S(. Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages. [Masters Thesis]. Delft University of Technology; 2019. Available from: http://resolver.tudelft.nl/uuid:625c408b-97ae-47a5-90c9-493dc4bc0224
University of the Western Cape
14.
Logday, Ayesha.
Space Debris and the BRICS countries: The role of international Environmental Law.
Degree: 2019, University of the Western Cape
URL: http://hdl.handle.net/11394/7579
► Environmental Law is at the forefront of the global community and environmental protection and conservation is regarded as of the utmost importance.1 Outer Space is…
(more)
▼ Environmental Law is at the forefront of the global community and environmental
protection and conservation is regarded as of the utmost importance.1 Outer
Space is
a unique, limited, and valuable resource. Outer
space allows states to utilise
thousands of satellites for research, national defence, and communications. At the
inception of
space law, only a few states dominated
space activities and all human
space activities were so challenging that nearly any method seemed acceptable for
placing objects in outer
space, currently more countries have
space industries and
launch capabilities
Advisors/Committee Members: Scholtz, Werner (advisor).
Subjects/Keywords: Space Debris;
Orbital Debris;
Developing states;
BRICS (Brazil, Russia, India, China and South Africa);
Space junk
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APA ·
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Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Logday, A. (2019). Space Debris and the BRICS countries: The role of international Environmental Law.
(Thesis). University of the Western Cape. Retrieved from http://hdl.handle.net/11394/7579
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Logday, Ayesha. “Space Debris and the BRICS countries: The role of international Environmental Law.
” 2019. Thesis, University of the Western Cape. Accessed March 06, 2021.
http://hdl.handle.net/11394/7579.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Logday, Ayesha. “Space Debris and the BRICS countries: The role of international Environmental Law.
” 2019. Web. 06 Mar 2021.
Vancouver:
Logday A. Space Debris and the BRICS countries: The role of international Environmental Law.
[Internet] [Thesis]. University of the Western Cape; 2019. [cited 2021 Mar 06].
Available from: http://hdl.handle.net/11394/7579.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Logday A. Space Debris and the BRICS countries: The role of international Environmental Law.
[Thesis]. University of the Western Cape; 2019. Available from: http://hdl.handle.net/11394/7579
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Penn State University
15.
Bolden, Mark Patrick.
PROBABILISTIC REAL-TIME DOMAIN AWARENESS LEVERAGING COMPUTER VISION AND COMPUTATIONAL INTELLIGENCE.
Degree: 2018, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/12603mpb212
► In tactical operations, decision making must exceed the speed of events. In the space domain, events, such as a satellite break-up event, can occur unexpectedly…
(more)
▼ In tactical operations, decision making must exceed the speed of events. In the
space domain, events, such as a satellite break-up event, can occur unexpectedly creating large fields of
debris objects. These
debris objects are uncontrolled and pose an immediate threat to other satellites. Satellite operators must quickly decide whether or not to maneuver their satellites. If a maneuver is necessary, the operator must also decide where to maneuver the satellite to avoid a probable collision. Due to the complexity of this challenge, traditional statistical approaches struggle to fuse information to track
debris clouds on a timeline that exceeds the speed of events. This thesis presents an alternative approach to statistical filters for real-time
debris cloud tracking. The approach produces the same level of accuracy in the same amount of time across the entire domain independently from the number of objects in the domain. The approach relies on a new computer vision transform coupled with a new computational intelligence cluster detection algorithm. Combining these techniques enables real-time (millisecond) updates using information from any modality where the uncertainty can be approximated or bounded, ranging from sensing to anecdotal sources. It is capable of ingesting observations that do not meet the typical observability criterion, to include negative detections. It provides real-time state estimates in addition to a full domain population distribution assessment. This includes knowledge of where there is an object, where there is not, and where there is not enough evidence to make a determination. Ultimately, the approach enables the scalable real-time domain awareness required for a decision maker to understand the domain risks and the uncertainties for tactical decision-making. More background on
space debris is discussed as the motivation for the technical challenges tackled by this research. Applying computational intelligence with computer vision is presented as a novel approach to solving these challenges in real-time. The concept is first explained on a simple example that leverages a standard computer vision technique known as the Hough transform. Next, the hardware and software design leveraged for testing is described along with performance results on the simple one-dimensional tracking example. How to apply this technique to the
space domain is discussed in detail with a proof of concept for the computer vision transform. Potential applications of the computational intelligence algorithm to other domains are discussed. The technique appears to be a viable alternative to statistical filter approaches with significant theoretical advantages, however no direct comparison is presented in this thesis.
Advisors/Committee Members: David Spencer, Thesis Advisor/Co-Advisor.
Subjects/Keywords: domain awareness; space domain; space debris; real-time; debris tracking; computer vision; computational intelligence; tactical object tracking; clustering; break-up event tracking; debris cloud tracking
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APA (6th Edition):
Bolden, M. P. (2018). PROBABILISTIC REAL-TIME DOMAIN AWARENESS LEVERAGING COMPUTER VISION AND COMPUTATIONAL INTELLIGENCE. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/12603mpb212
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Bolden, Mark Patrick. “PROBABILISTIC REAL-TIME DOMAIN AWARENESS LEVERAGING COMPUTER VISION AND COMPUTATIONAL INTELLIGENCE.” 2018. Thesis, Penn State University. Accessed March 06, 2021.
https://submit-etda.libraries.psu.edu/catalog/12603mpb212.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Bolden, Mark Patrick. “PROBABILISTIC REAL-TIME DOMAIN AWARENESS LEVERAGING COMPUTER VISION AND COMPUTATIONAL INTELLIGENCE.” 2018. Web. 06 Mar 2021.
Vancouver:
Bolden MP. PROBABILISTIC REAL-TIME DOMAIN AWARENESS LEVERAGING COMPUTER VISION AND COMPUTATIONAL INTELLIGENCE. [Internet] [Thesis]. Penn State University; 2018. [cited 2021 Mar 06].
Available from: https://submit-etda.libraries.psu.edu/catalog/12603mpb212.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Bolden MP. PROBABILISTIC REAL-TIME DOMAIN AWARENESS LEVERAGING COMPUTER VISION AND COMPUTATIONAL INTELLIGENCE. [Thesis]. Penn State University; 2018. Available from: https://submit-etda.libraries.psu.edu/catalog/12603mpb212
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
RMIT University
16.
Wong, B.
The enhancement of atmospheric drag prediction using space-tracking data for accurate debris surveillance and collision warning.
Degree: 2012, RMIT University
URL: http://researchbank.rmit.edu.au/view/rmit:160226
► This research investigates the temporal variation of the coefficient of atmospheric drag value (CD) and its subsequent effects on orbit prediction. Atmospheric drag is one…
(more)
▼ This research investigates the temporal variation of the coefficient of atmospheric drag value (CD) and its subsequent effects on orbit prediction. Atmospheric drag is one of the most dominant forces exerted to space objects at altitudes below approximately 1500 km in the Low Earth Orbit (LEO). Its accuracy is governed primarily by the accuracy of the atmospheric mass density modelling, area-to-mass ratio and the CD value. Traditionally, the tracking of space objects is conducted using the radar method and the optical approach. Recently, Satellite Laser Ranging (SLR) technique is being developed to track space debris. However, it is still limited by the most fundamental problem of unable to accurately predict the motion of space objects, which is largely due to the insufficient accuracy of determining the atmospheric drag. The focus of this research is to investigate viable approaches to enhance the prediction of the CD value for higher accuracy prediction of orbits of space objects. The conventional CD value prediction approaches, i.e., the fix 2.2 CD and variable CD methods, are investigated. The more accurate variable CD approach has presented a repetitive cyclical change in the estimated CD values over the study period from 2004 to 2006 using Stella as the experimental satellite. This suggests a different scenario to the fixed value of 2.2 approach commonly adopted by the space industry. Due to the repetitive cycle of the CD variations, Fourier series are selected to fit the estimated CD values over the study period. The fitting function is extrapolated to predict CD values for 2007, which are subsequently applied to the subsequent orbit prediction process using the fix CD value method. This implies that the predicted CD values are pre-determined prior to the orbit determination and prediction, similar to the fix 2.2 method that adopts a fixed value of 2.2. The orbit prediction results using the fitting function have demonstrated significant improvements over the traditional fixed 2.2 CD value method. The fitting function approach is also verified by performing the same experiments to satellites Starlette and ERS-2, where noticeable improvements in the orbit predictions are also achieved. For orbit prediction, the fixed value method has shown to be more computationally efficient since approximate 20% reduction in data processing time is achieved compared to the more accurate variable CD approach. This is one of the fundamental reasons for the space industry to adopt the fixed value method, especially when timely prediction of orbits is the primary goal to many orbit applications. This research has presented the fitting function approach for CD value prediction and the results have demonstrated that higher accuracy orbit predictions without degradation to the efficiency are achieved compared to the fix 2.2 CD method. Thus, this research will provide a valuable performance assessment of the conventional and the fitting function CD value estimation/prediction approaches for atmospheric research. In addition,…
Subjects/Keywords: Fields of Research; Atmospheric Drag; Coefficient of Drag; Space Debris
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APA (6th Edition):
Wong, B. (2012). The enhancement of atmospheric drag prediction using space-tracking data for accurate debris surveillance and collision warning. (Thesis). RMIT University. Retrieved from http://researchbank.rmit.edu.au/view/rmit:160226
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Wong, B. “The enhancement of atmospheric drag prediction using space-tracking data for accurate debris surveillance and collision warning.” 2012. Thesis, RMIT University. Accessed March 06, 2021.
http://researchbank.rmit.edu.au/view/rmit:160226.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Wong, B. “The enhancement of atmospheric drag prediction using space-tracking data for accurate debris surveillance and collision warning.” 2012. Web. 06 Mar 2021.
Vancouver:
Wong B. The enhancement of atmospheric drag prediction using space-tracking data for accurate debris surveillance and collision warning. [Internet] [Thesis]. RMIT University; 2012. [cited 2021 Mar 06].
Available from: http://researchbank.rmit.edu.au/view/rmit:160226.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Wong B. The enhancement of atmospheric drag prediction using space-tracking data for accurate debris surveillance and collision warning. [Thesis]. RMIT University; 2012. Available from: http://researchbank.rmit.edu.au/view/rmit:160226
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
17.
Aheieva, Kateryna.
Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発.
Degree: 博士（工学）, 2017, Kyushu Institute of Technology / 九州工業大学
URL: http://hdl.handle.net/10228/5971
九州工業大学博士学位論文 学位記番号:工博甲第422号 学位授与年月日:平成28年9月23日
1. Introduction|2. Experimental apparatus and test setup|3. Vacuum Arc Thruster|4. Satellite deorbit system based on the Vacuum Arc Thruster|5. Vacuum Arc Thruster on-board satellite Horyu-4|6. Conclusions
平成28年度
Advisors/Committee Members: 豊田, 和弘.Subjects/Keywords: Electric propulsion; Nanosatellites; Plasma; Space debris; deorbiting; Vacuum arc thruster
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APA (6th Edition):
Aheieva, K. (2017). Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発. (Thesis). Kyushu Institute of Technology / 九州工業大学. Retrieved from http://hdl.handle.net/10228/5971
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Aheieva, Kateryna. “Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発.” 2017. Thesis, Kyushu Institute of Technology / 九州工業大学. Accessed March 06, 2021.
http://hdl.handle.net/10228/5971.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Aheieva, Kateryna. “Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発.” 2017. Web. 06 Mar 2021.
Vancouver:
Aheieva K. Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発. [Internet] [Thesis]. Kyushu Institute of Technology / 九州工業大学; 2017. [cited 2021 Mar 06].
Available from: http://hdl.handle.net/10228/5971.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Aheieva K. Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発. [Thesis]. Kyushu Institute of Technology / 九州工業大学; 2017. Available from: http://hdl.handle.net/10228/5971
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Toronto
18.
Sears, McGrath Casey Thomas.
Sail, Deployment, and Imaging Technology for a Nanosatellite Deorbit System Demonstration on CanX-7.
Degree: 2014, University of Toronto
URL: http://hdl.handle.net/1807/68060
► The widespread adoption of nanosatellites will drastically increase space debris if end-of-life disposal is not performed. As the natural deorbit lifetime of these satellites can…
(more)
▼ The widespread adoption of nanosatellites will drastically increase space debris if end-of-life disposal is not performed. As the natural deorbit lifetime of these satellites can be over 100 years, a deorbit system is needed to ensure the small satellite community will comply with international standards. This thesis discusses the design and testing of the drag sail module – a device that will deploy a thin film sail to increase atmospheric drag experienced by a spacecraft – to be demonstrated as the primary payload on the CanX-7 satellite. Sail and boom technology, which includes environmental analysis, material selection, and testing, are presented in this context. Furthermore, deployment dynamics have been characterized through extensive testing prior to qualification testing. Lastly, design and testing of a miniature imaging system is presented. Imagery will be used to verify sail deployment on the inaugural flight of the drag sail module on CanX-7.
M.A.S.
Advisors/Committee Members: Zee, E Robert, Aerospace Science and Engineering.
Subjects/Keywords: CanX-7; Deorbit sail; Drag sail; Sail material; Space debris; 0538
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APA (6th Edition):
Sears, M. C. T. (2014). Sail, Deployment, and Imaging Technology for a Nanosatellite Deorbit System Demonstration on CanX-7. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/68060
Chicago Manual of Style (16th Edition):
Sears, McGrath Casey Thomas. “Sail, Deployment, and Imaging Technology for a Nanosatellite Deorbit System Demonstration on CanX-7.” 2014. Masters Thesis, University of Toronto. Accessed March 06, 2021.
http://hdl.handle.net/1807/68060.
MLA Handbook (7th Edition):
Sears, McGrath Casey Thomas. “Sail, Deployment, and Imaging Technology for a Nanosatellite Deorbit System Demonstration on CanX-7.” 2014. Web. 06 Mar 2021.
Vancouver:
Sears MCT. Sail, Deployment, and Imaging Technology for a Nanosatellite Deorbit System Demonstration on CanX-7. [Internet] [Masters thesis]. University of Toronto; 2014. [cited 2021 Mar 06].
Available from: http://hdl.handle.net/1807/68060.
Council of Science Editors:
Sears MCT. Sail, Deployment, and Imaging Technology for a Nanosatellite Deorbit System Demonstration on CanX-7. [Masters Thesis]. University of Toronto; 2014. Available from: http://hdl.handle.net/1807/68060
University of Washington
19.
Barker, Adam.
Glaciers, erosion and climate change in the Himalaya and St. Elias Range, SE Alaska.
Degree: PhD, 2017, University of Washington
URL: http://hdl.handle.net/1773/38518
► The important roles of glaciers in topographic evolution, relief development, and sediment production are well recognized but understanding remains rather limited largely because of the…
(more)
▼ The important roles of glaciers in topographic evolution, relief development, and sediment production are well recognized but understanding remains rather limited largely because of the inherent complexity of glacial erosion in diverse terrains, the lack of validated glacial erosion models, and the sparse nature of the data available on erosion rates. The primary focus of this research is defining and understanding rates of glacial erosion and their spatio-temporal variation at the scales of single glacier basins and entire orogens. I study glacial erosion in two tectonically active mountain ranges, the Himalaya and the St. Elias Range (Alaska), ideally suited for this study because of the wealth of pertinent data already available, and because they represent a broad range of climates and glacier types. In the Himalaya study, I also examine the impact of the
debris produced by glacial erosion that accumulates on the glacier surface on glacier mass balance and the response of the glacier to climate change. In the SE Alaska study, I model the spatial pattern of erosion rates over an entire glacial cycle, and compare the temporally averaged rates to published rates of exhumation to validate and calibrate an erosion model. These model results illuminate the source region and temporal aspects of the offshore sediment record that have received considerable attention in the context of climate-driven modulation of erosion and sediment production. Large data sets on exhumation rates spanning the entire Himalayan arc have documented spatial and temporal variations in erosion rates; however, data on glacial erosion rates at the heavily glaciated crest of the Himalaya are very sparse. In light of this weakness in the knowledge base, I integrate several types of field research to investigate rates of erosion for a single glaciated basin at the base of Mt. Everest. I found that erosion rates for two timescales, contemporary (101 yr) and over the Holocene (104 yr), are similar to published long-term (O ~ 107 yr) exhumation rates (~1 mm/yr) derived from thermochronometric data in the region. The apparent uniformity of erosion and exhumation rates over a large range of time implies a surprising insensitivity to likely variations in climate, structural development, and relief evolution; it also contrasts with recent studies emphasizing the variation of rates over different timescales. Moreover, measurements of the suspended sediment flux out of the proglacial stream suggest that the fluvial evacuation rate of suspended sediments is ~50x less than the contemporary sediment production rate. This, together with the known time over which sediment has accumulated in the basin, the downglacier decrease in sediment flux, and evidence that the contemporary glacier is perched on a 20–100 m thick
debris edifice, implies that most of the eroded
debris remains within the basin. This result provides new insights into the geomorphic development of the high relief in the Himalaya, and the episodic nature of the downstream transfer of…
Advisors/Committee Members: Hallet, Bernard (advisor).
Subjects/Keywords: Debris-Covered Glaciers; Glacial Erosion; Geology; Geomorphology; Earth and space sciences
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APA (6th Edition):
Barker, A. (2017). Glaciers, erosion and climate change in the Himalaya and St. Elias Range, SE Alaska. (Doctoral Dissertation). University of Washington. Retrieved from http://hdl.handle.net/1773/38518
Chicago Manual of Style (16th Edition):
Barker, Adam. “Glaciers, erosion and climate change in the Himalaya and St. Elias Range, SE Alaska.” 2017. Doctoral Dissertation, University of Washington. Accessed March 06, 2021.
http://hdl.handle.net/1773/38518.
MLA Handbook (7th Edition):
Barker, Adam. “Glaciers, erosion and climate change in the Himalaya and St. Elias Range, SE Alaska.” 2017. Web. 06 Mar 2021.
Vancouver:
Barker A. Glaciers, erosion and climate change in the Himalaya and St. Elias Range, SE Alaska. [Internet] [Doctoral dissertation]. University of Washington; 2017. [cited 2021 Mar 06].
Available from: http://hdl.handle.net/1773/38518.
Council of Science Editors:
Barker A. Glaciers, erosion and climate change in the Himalaya and St. Elias Range, SE Alaska. [Doctoral Dissertation]. University of Washington; 2017. Available from: http://hdl.handle.net/1773/38518
Delft University of Technology
20.
Habets, J.M.G. (author).
Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft.
Degree: 2015, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8
► Space debris has become a major issue for the space industry over the last couple of years. The increasing number of uncontrolled objects in space…
(more)
▼ Space debris has become a major issue for the
space industry over the last couple of years. The increasing number of uncontrolled objects in
space increases the chance of collision with a spacecraft. The unexpected loss of contact with ENVISAT, the European
Space Agency’s largest environmental spacecraft, added one more piece of
debris to the list. It also sparked ESA’s interest in the active removal of
space debris. Numerous removal methods are being investigated, one of which uses a chaser spacecraft that will attach itself to the
debris by means of a robot arm and tentacles and will then perform a series of braking manoeuvres to re-enter the Earth’s atmosphere. The proximity operations require an accurate attitude control system. In this thesis, these operations have been divided into three phases: an unconnected phase in which the chaser spacecraft synchronises its motion with that of the (spinning) target
debris; a semi-connected phase, where the robot arm and tentacles form a flexible connection between the chaser and target; a connected phase, where the two spacecraft are assumed to be rigidly attached to each other (and form a stack). The objective of this thesis is to investigate the stability and controllability of the system in these three phases. Because the system changes in configuration during its mission, it can be classified as an Evolving System; a system with actively controlled components that "mate" to form a single connected system. The connection between components becomes stronger during the evolution and can be represented by connection forces and moments. In this thesis, the connection is modelled as a rotational spring and damper acting between the chaser spacecraft and ENVISAT. By developing a representative simulator environment the stability and controllability of the system is assessed. Two major parts of the simulator comprise the attitude control algorithms and control actuators. The latter consists of a Reaction Control System, reaction wheels, and a control allocation algorithm. The attitude control algorithms that are investigated are a Linear Quadratic Regulator and a model reference adaptive controller. A linear stability analysis of the system showed that the system remains stable during its evolution when the chaser is actively controlled. This is partly because the motion of the chaser has little effect on the motion of ENVISAT due to the large size difference between the two spacecraft. However, for a system with equally sized spacecraft, the linear stability analysis showed that instability can occur. Furthermore, in stack configuration, a gravity-gradient stable attitude was found when the minor axis of the system is parallel to the Earth radial. Moreover, for a suitable deorbit attitude and an unobstructed view to the Earth, the only stable attitude is one which has a roll angle of -90 deg. Next, results of the nonlinear simulations revealed that the combination of reaction wheels and attitude thrusters gives worse performance than when only thrusters are used. This is…
Advisors/Committee Members: Mooij, E. (mentor).
Subjects/Keywords: attitude control; space debris; adaptive control; evolving systems; ENVISAT
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APA (6th Edition):
Habets, J. M. G. (. (2015). Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8
Chicago Manual of Style (16th Edition):
Habets, J M G (author). “Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft.” 2015. Masters Thesis, Delft University of Technology. Accessed March 06, 2021.
http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8.
MLA Handbook (7th Edition):
Habets, J M G (author). “Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft.” 2015. Web. 06 Mar 2021.
Vancouver:
Habets JMG(. Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Mar 06].
Available from: http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8.
Council of Science Editors:
Habets JMG(. Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8
Delft University of Technology
21.
Lopez Jimenez, Sergi (author).
New techniques for uncertainty realism improvement in Space Surveillance and Tracking orbit determination processes.
Degree: 2020, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:c9c99702-aff5-40fd-b155-07a169281843
► The future space environment is predicted to grow in number of both operational and inactive man-made objects and the era of constellations is expected to…
(more)
▼ The future
space environment is predicted to grow in number of both operational and inactive man-made objects and the era of constellations is expected to arrive during the following years, with many telecom companies launching constellations of up to 12000 satellites. This situation will inevitably lead to over-population of the most demanded orbits making its exploitation a challenge to the scientific community as well as spacecraft operators. Regular products within the field of
Space Surveillance and Tracking (SST) and
Space Traffic Management (STM), such as high-risk collisions, upcoming re-entries or fragmentations, rely both on the estimated state and associated uncertainty of detectable Resident
Space Objects (RSOs). Orbit Determination (OD) algorithms provide the required estimations, assuming that the uncertainty in the state of the object is properly characterized by its state vector covariance and assuming Gaussian processes. However, a common problem of OD processes is the misrepresentation of the RSOs uncertainty through the estimated and predicted covariance. Ultimately, this causes a great impact in the quality and accuracy of SST products as the covariance is overly optimistic (too small) and the true uncertainty of the object is not properly captured. The aim of this work is to devise a novel methodology to improve the covariance realism of OD and orbit propagation processes through the classical theory of consider parameters of batch least-squares estimators. The outcome of this project is a software application integrated as part of the GMV’s SST software suite that can deliver efficient and effective covariance realism improvement for a more accurate provision of SST products.
Advisors/Committee Members: Schrama, Ernst (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: Space Debris; SST; orbit determination; Covariance Analysis; covariance realism
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APA (6th Edition):
Lopez Jimenez, S. (. (2020). New techniques for uncertainty realism improvement in Space Surveillance and Tracking orbit determination processes. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:c9c99702-aff5-40fd-b155-07a169281843
Chicago Manual of Style (16th Edition):
Lopez Jimenez, Sergi (author). “New techniques for uncertainty realism improvement in Space Surveillance and Tracking orbit determination processes.” 2020. Masters Thesis, Delft University of Technology. Accessed March 06, 2021.
http://resolver.tudelft.nl/uuid:c9c99702-aff5-40fd-b155-07a169281843.
MLA Handbook (7th Edition):
Lopez Jimenez, Sergi (author). “New techniques for uncertainty realism improvement in Space Surveillance and Tracking orbit determination processes.” 2020. Web. 06 Mar 2021.
Vancouver:
Lopez Jimenez S(. New techniques for uncertainty realism improvement in Space Surveillance and Tracking orbit determination processes. [Internet] [Masters thesis]. Delft University of Technology; 2020. [cited 2021 Mar 06].
Available from: http://resolver.tudelft.nl/uuid:c9c99702-aff5-40fd-b155-07a169281843.
Council of Science Editors:
Lopez Jimenez S(. New techniques for uncertainty realism improvement in Space Surveillance and Tracking orbit determination processes. [Masters Thesis]. Delft University of Technology; 2020. Available from: http://resolver.tudelft.nl/uuid:c9c99702-aff5-40fd-b155-07a169281843
Delft University of Technology
22.
Lagaune, B.F. (author).
Determination of the attitude state of space debris objects based on Satellite Laser Ranging, using Envisat as a test case.
Degree: 2016, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:245b8941-08f3-4322-a442-d50e174e3c05
► The attitude state of the passive Envisat satellite (ESA) has been estimated before using various techniques like Satellite Laser Ranging, radar and using light-curves. This…
(more)
▼ The attitude state of the passive Envisat satellite (ESA) has been estimated before using various techniques like Satellite Laser Ranging, radar and using light-curves. This research focusses on the use of Satellite Laser Ranging. Due to the relatively large (meter scale) offset between the center-of-mass of the satellite and the reflector where the laser signal is reflected back to the transmitting and receiving ground station, large oscillations in the range residuals are visible. These oscillations show the rotating behaviour of Envisat, and can be translated to its rotational state by re-producing this signal using a corresponding attitudemodel and the offset between the reflector and the center-of-mass. First a purely theoretical case was considered where a known simulated orbit and attitude where estimated for various cases in order to validate the use of the estimation scheme. Afterwords, the real Satellite Laser Ranging data of Envisat was used for the time period 2013-2015.
Aerospace Engineering
Astrodynamics and Space Missions
Advisors/Committee Members: Doornbos, E.N. (mentor).
Subjects/Keywords: SLR; attitude; estimation; determination; Envisat; space debris; simulation; GEODYN; tumbling
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APA (6th Edition):
Lagaune, B. F. (. (2016). Determination of the attitude state of space debris objects based on Satellite Laser Ranging, using Envisat as a test case. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:245b8941-08f3-4322-a442-d50e174e3c05
Chicago Manual of Style (16th Edition):
Lagaune, B F (author). “Determination of the attitude state of space debris objects based on Satellite Laser Ranging, using Envisat as a test case.” 2016. Masters Thesis, Delft University of Technology. Accessed March 06, 2021.
http://resolver.tudelft.nl/uuid:245b8941-08f3-4322-a442-d50e174e3c05.
MLA Handbook (7th Edition):
Lagaune, B F (author). “Determination of the attitude state of space debris objects based on Satellite Laser Ranging, using Envisat as a test case.” 2016. Web. 06 Mar 2021.
Vancouver:
Lagaune BF(. Determination of the attitude state of space debris objects based on Satellite Laser Ranging, using Envisat as a test case. [Internet] [Masters thesis]. Delft University of Technology; 2016. [cited 2021 Mar 06].
Available from: http://resolver.tudelft.nl/uuid:245b8941-08f3-4322-a442-d50e174e3c05.
Council of Science Editors:
Lagaune BF(. Determination of the attitude state of space debris objects based on Satellite Laser Ranging, using Envisat as a test case. [Masters Thesis]. Delft University of Technology; 2016. Available from: http://resolver.tudelft.nl/uuid:245b8941-08f3-4322-a442-d50e174e3c05
University of New Mexico
23.
Shubert, Matthew.
Computing the Reach-Avoid Set for Space Vehicle Maneuvering in the Presence of Debris.
Degree: Electrical and Computer Engineering, 2017, University of New Mexico
URL: https://digitalrepository.unm.edu/ece_etds/341
► The ability to guarantee the safety of autonomously controlled space vehicles is of great importance to help avoid accidents and ensure mission success. In…
(more)
▼ The ability to guarantee the safety of autonomously controlled
space vehicles is of great importance to help avoid accidents and ensure mission success. In this paper we investigate the safety verification of a satellite attempting to maneuver to a new position while avoiding multiple pieces of
debris. We assume that the satellite, desired rendezvous point, and all
debris are near the same circular orbit with dynamics modeled by Clohessy-Wiltshire-Hill (CWH) equations. We will use reachability methods to guarantee the satellite is able to reach a desired point while avoiding all
debris. We will first develop a computationally efficient method for computing the Reach-Avoid set for a system modeled by CWH dynamics, and then extend this method to the minimal and maximal reach calculations. We then review a system decomposition method for computing reach sets in large dimensions and apply the methods to the
debris avoidance problem. Finally, we develop computationally efficient methods to compute an under-approximation of the Reach-Avoid set and present numerical examples for single and multiple
debris scenarios.
Advisors/Committee Members: Meeko Oishi, Rafael Fierro, R. Scott Erwin.
Subjects/Keywords: reach-avoid; reachability; space vehicle; debris avoidance; Electrical and Computer Engineering
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APA (6th Edition):
Shubert, M. (2017). Computing the Reach-Avoid Set for Space Vehicle Maneuvering in the Presence of Debris. (Masters Thesis). University of New Mexico. Retrieved from https://digitalrepository.unm.edu/ece_etds/341
Chicago Manual of Style (16th Edition):
Shubert, Matthew. “Computing the Reach-Avoid Set for Space Vehicle Maneuvering in the Presence of Debris.” 2017. Masters Thesis, University of New Mexico. Accessed March 06, 2021.
https://digitalrepository.unm.edu/ece_etds/341.
MLA Handbook (7th Edition):
Shubert, Matthew. “Computing the Reach-Avoid Set for Space Vehicle Maneuvering in the Presence of Debris.” 2017. Web. 06 Mar 2021.
Vancouver:
Shubert M. Computing the Reach-Avoid Set for Space Vehicle Maneuvering in the Presence of Debris. [Internet] [Masters thesis]. University of New Mexico; 2017. [cited 2021 Mar 06].
Available from: https://digitalrepository.unm.edu/ece_etds/341.
Council of Science Editors:
Shubert M. Computing the Reach-Avoid Set for Space Vehicle Maneuvering in the Presence of Debris. [Masters Thesis]. University of New Mexico; 2017. Available from: https://digitalrepository.unm.edu/ece_etds/341
University of Arizona
24.
Gaspar, Andras.
Observations and Models of Infrared Debris Disk Signatures and their Evolution
.
Degree: 2011, University of Arizona
URL: http://hdl.handle.net/10150/202982
► In my thesis I investigate the occurrence of mid-infrared excess around stars and their evolution. Since the launch of the first infrared satellite, IRAS, we…
(more)
▼ In my thesis I investigate the occurrence of mid-infrared excess around stars and their evolution. Since the launch of the first infrared satellite, IRAS, we have known that a large fraction of stars exhibit significant levels of infrared emission above their predicted photospheric level. Resolved optical and infrared images have revealed the majority of these excesses to arise from circumstellar disk structures, made up of distributions of planetesimals, rocks, and dust. These structures are descriptively called
debris disks. The first part of my thesis analyzes the Spitzer
Space Telescope Observations of δ Velorum. The 24 μm Spitzer images revealed a bow shock structure in front of the star. My analysis showed that this is a result of the star’s high speed interaction with the surrounding interstellar medium. We place this observation and model in context of
debris disk detections and the origin of λ Boötis stars. The second part of my thesis summarizes our observational results on the open cluster Praesepe. Using 24 μm data, I investigated the fraction of stars with mid-infrared excess, likely to have
debris disks. I also assembled all results from previous
debris disk studies and followed the evolution of the fraction of stars with
debris disks. The majority of
debris disks systems are evolved, few hundred million or a Gyr old. Since the dissipation timescale for the emitting dust particles is less than the age of these systems, they have to be constantly replenished through collisional grinding of the larger bodies. The last two chapters of my thesis is a theoretical analysis of the collisional cascade in
debris disks, the process that produces the constant level of dust particles detected. I introduce a numerical model that takes into account all types of destructive collisions in the systems and solves the full scattering equation. I show results of comparisons between my and other published models and extensive verification tests of my model. I also analyze the evolution of the particle size distribution as a function of the variables in my model and show that the model itself is quite robust against most variations.
Advisors/Committee Members: Rieke, George H (advisor), Psaltis, Dimitrios (committeemember), Özel, Feryal (committeemember), Apai, Dániel (committeemember), Su, Kate Y. L. (committeemember).
Subjects/Keywords: Modeling;
Planetary Systems;
Spitzer Space Telescope;
Stars;
Astronomy;
Debris Disks;
Infrared
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APA (6th Edition):
Gaspar, A. (2011). Observations and Models of Infrared Debris Disk Signatures and their Evolution
. (Doctoral Dissertation). University of Arizona. Retrieved from http://hdl.handle.net/10150/202982
Chicago Manual of Style (16th Edition):
Gaspar, Andras. “Observations and Models of Infrared Debris Disk Signatures and their Evolution
.” 2011. Doctoral Dissertation, University of Arizona. Accessed March 06, 2021.
http://hdl.handle.net/10150/202982.
MLA Handbook (7th Edition):
Gaspar, Andras. “Observations and Models of Infrared Debris Disk Signatures and their Evolution
.” 2011. Web. 06 Mar 2021.
Vancouver:
Gaspar A. Observations and Models of Infrared Debris Disk Signatures and their Evolution
. [Internet] [Doctoral dissertation]. University of Arizona; 2011. [cited 2021 Mar 06].
Available from: http://hdl.handle.net/10150/202982.
Council of Science Editors:
Gaspar A. Observations and Models of Infrared Debris Disk Signatures and their Evolution
. [Doctoral Dissertation]. University of Arizona; 2011. Available from: http://hdl.handle.net/10150/202982
25.
Graham, Giles Andrew.
The mineralogy and chemistry of micrometeorites.
Degree: PhD, 2000, Open University
URL: http://oro.open.ac.uk/19214/
;
https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.310007
► Prior to their retrieval from low Earth orbit (LEO), the individual solar cells that make up the 'V2' solar array panel from the Huhble Space…
(more)
▼ Prior to their retrieval from low Earth orbit (LEO), the individual solar cells that make up the 'V2' solar array panel from the Huhble Space Telescope (HST) were prone to hypervelocity (>5 km/s ) impact damage from micrometeoroids and space debris. The analysis of such passive collector surfaces allows sampling of micrometeoroids that have not undergone any terrestrial atmospheric alteration and better defines the population of space debris particles below the lmm size range. Herein a new approach has been taken to try and identify the nature atid origin of impact derived residues generated in the individual solar cells from the HST. A total of 25 solar cells were selected on the basis that they contained impact craters (100-1000?n diameter) rather than larger impact holes (1-3mm diameter), as preliminary studies indicated that they were more likely to retain impact residues. These were subsequently analysed using digitised hack-scattered electron imaging, coupled with digitised x-ray elemental mapping and micro-spot analysis to locate, identify and classify the residues. 29 impact craters were located on solar cells. In the analysis of the residues; 3 were identified residues as space debris in origin, 6 unclassified and 20 as micrometeoroid. The space debris derived residues were identified as remnants of a paint fragment, a stainless steel particle and a fragment of a printed circuit board. The micrometeoroid derived residues were sub-classified in terms of mineral chemistry, with apparent mafic- and phyllo- silicates being the dominant components, with minor iron-nickel metal and iron sulfides, suggesting a broadly chondritic origin. Fe-Ni rich residue was also identified that would appear to belong to a group of non-chondritic particles previously unrecognised. Possible refractory or Ca/Al rich inclusions from a primitive micrometeoroid were also observed as near intact Ca-rich fragments, the textures of the individual grains suggested that they were not merely terrestrial contamination. Laboratory impact studies, using a light-gas-gun to accelerate small fragments (125- 250?m) of known meteorite mineralogies up to 5km/s, and then impact them into solar cells have generated a suite of residues that are analogues of those observed from LEO studies. The silicate minerals generated residues that were intimately associated with the host melt glass. Metallic sulfides and metals generated surface and sub-surface immiscible droplets. Several craters also contained near-intact fragments of minerals. Overall. despite the small sample set examined. the observed dominance of micrometeoroid to space debris residue chemistry (correlating to particle size range of 8-80 ?m) corresponds well to the accepted flux models.
Subjects/Keywords: 559.9; Meteorites; Space debris
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APA (6th Edition):
Graham, G. A. (2000). The mineralogy and chemistry of micrometeorites. (Doctoral Dissertation). Open University. Retrieved from http://oro.open.ac.uk/19214/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.310007
Chicago Manual of Style (16th Edition):
Graham, Giles Andrew. “The mineralogy and chemistry of micrometeorites.” 2000. Doctoral Dissertation, Open University. Accessed March 06, 2021.
http://oro.open.ac.uk/19214/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.310007.
MLA Handbook (7th Edition):
Graham, Giles Andrew. “The mineralogy and chemistry of micrometeorites.” 2000. Web. 06 Mar 2021.
Vancouver:
Graham GA. The mineralogy and chemistry of micrometeorites. [Internet] [Doctoral dissertation]. Open University; 2000. [cited 2021 Mar 06].
Available from: http://oro.open.ac.uk/19214/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.310007.
Council of Science Editors:
Graham GA. The mineralogy and chemistry of micrometeorites. [Doctoral Dissertation]. Open University; 2000. Available from: http://oro.open.ac.uk/19214/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.310007
26.
Kebe, Fatoumata.
Etude de l'influence des incréments de vitesse impulsionnels sur les trajectoires de débris spatiaux : Study of the influence of the velocity increment on the trajectories of space debris.
Degree: Docteur es, Astronomie et Astrophysique, 2016, Université Pierre et Marie Curie – Paris VI
URL: http://www.theses.fr/2016PA066669
► En 1957, la conquête de l'espace par l'homme commença avec le succès de la mise en orbite du premier satellite artificiel ; Spoutnik 1. Ce…
(more)
▼ En 1957, la conquête de l'espace par l'homme commença avec le succès de la mise en orbite du premier satellite artificiel ; Spoutnik 1. Ce fut le début de l'exploitation de l'orbite terrestre caractérisée par une centaine de lancements de fusées partant de Kourou, Baïkonour et autres bases de lancement. Aujourd'hui, l'orbite terrestre a une population composée en majeure partie de débris spatiaux. Ces derniers regroupent des étages supérieurs de fusée, des satellites ayant fini leur mission et autre petits objets artificiels dont l'origine n'est pas forcément identifiable. Leur nombre est devenu si important, allant même jusqu'à remettre en cause la viabilité des activités spatiales que leur étude est devenu incontournable. La génération de nouveaux débris se traduit majoritairement par l'avènement d'une collision ou d'une explosion. Une meilleure connaissance de ces évènements dits évènements de fragmentation permettra une meilleure lutte contre la prolifération des débris spatiaux. Afin d'optimiser l'étude d'un nuage de débris, il est nécessaire de développer de nouveaux outils. Dans la première partie de la thèse, nous élaborons un modèle de fragmentation permettant de créer des nuages de débris spatiaux générés à la suite d'une explosion ou d'une collision. Pour cela, nous partons du modèle de fragmentation de la NASA, Evolve ainsi que d'autres fonctions de distribution issus de diverses expériences de fragmentation. Grâce à ce modèle, nous obtenons des paramètres géométriques et également en termes de vitesse dont nous chercherons à déterminer leur influence sur le mouvement du nuage.
In 1957, the space conquest by man began with the successful launch into orbit of the first artificial satellite; Sputnik 1. This was the beginning of the exploitation of the earth's orbit characterized by a hundred of rocket launches starting from several launchpad such as Kourou or Baikonur. Today, the Earth's orbit has a population composed mostly of space debris. These include upper rocket stages, satellites which have ended their mission and other small artificial objects whose origin is not necessarily recognizable. Their number has become so important that it question the sustainability of space activities. In this thesis we figure out the difficulties to handle the issue posed by the space debris. In the first part of the thesis, we develop a fragmentation model to generate clouds of space debris as a result of an explosion or collision in space. For this, we mainly used the fragmentation model of NASA, Evolve, and other distribution functions from diverse experiences of fragmentation. Thanks to this model, we know the geometric parameters and also in terms of speed which we will seek to determine their influence on the movement of the cloud. Thus, in the second part of the thesis, we study the motion of space debris evolving initially in low Earth orbit.
Advisors/Committee Members: Dudeck, Michel (thesis director), Hestroffer, Daniel (thesis director).
Subjects/Keywords: Débris spatiaux; Fragmentation; Explosion; Collision; Trajectoire; Space debris; Fragmentation; Collision; 523.01
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APA (6th Edition):
Kebe, F. (2016). Etude de l'influence des incréments de vitesse impulsionnels sur les trajectoires de débris spatiaux : Study of the influence of the velocity increment on the trajectories of space debris. (Doctoral Dissertation). Université Pierre et Marie Curie – Paris VI. Retrieved from http://www.theses.fr/2016PA066669
Chicago Manual of Style (16th Edition):
Kebe, Fatoumata. “Etude de l'influence des incréments de vitesse impulsionnels sur les trajectoires de débris spatiaux : Study of the influence of the velocity increment on the trajectories of space debris.” 2016. Doctoral Dissertation, Université Pierre et Marie Curie – Paris VI. Accessed March 06, 2021.
http://www.theses.fr/2016PA066669.
MLA Handbook (7th Edition):
Kebe, Fatoumata. “Etude de l'influence des incréments de vitesse impulsionnels sur les trajectoires de débris spatiaux : Study of the influence of the velocity increment on the trajectories of space debris.” 2016. Web. 06 Mar 2021.
Vancouver:
Kebe F. Etude de l'influence des incréments de vitesse impulsionnels sur les trajectoires de débris spatiaux : Study of the influence of the velocity increment on the trajectories of space debris. [Internet] [Doctoral dissertation]. Université Pierre et Marie Curie – Paris VI; 2016. [cited 2021 Mar 06].
Available from: http://www.theses.fr/2016PA066669.
Council of Science Editors:
Kebe F. Etude de l'influence des incréments de vitesse impulsionnels sur les trajectoires de débris spatiaux : Study of the influence of the velocity increment on the trajectories of space debris. [Doctoral Dissertation]. Université Pierre et Marie Curie – Paris VI; 2016. Available from: http://www.theses.fr/2016PA066669
Delft University of Technology
27.
Schild, Maarten (author).
Sun-synchronous Spacecraft Compliance with International Space Debris Guidelines.
Degree: 2021, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:f105b7fc-b9d6-484e-9c70-c76ba994d0a4
► Due to ever increasing accessibility, recent years have seen a fast growing number of launches to space, especially to Sun-synchronous orbit. The spent rocket parts,…
(more)
▼ Due to ever increasing accessibility, recent years have seen a fast growing number of launches to
space, especially to Sun-synchronous orbit. The spent rocket parts, payload fairings and eventually non-functioning payloads of these launches remain in orbit. It is well-established that this accumulation of
space debris over time is quickly making this the most severe threat to future spaceflight operations. To address and mitigate this problem a set of internationally agreed guidelines were established including a maximum of 25-year remaining orbital lifetime in this region after end-of-life. This study evaluates if Sun-synchronous satellite operators adhere to this guideline. To determine this compliance, the operational status of the satellites with orbital control capabilities is established using a maneuver detection algorithm. For satellites without the capability to maneuver a model is created based on mass and design lifetime to determine the duration of the operational phase. Using a semi-analytic propagation method the remaining orbital lifetimes is determined. The results show an overall compliance of 59% with an increasing trend starting around 2014, before which compliance was 20 to 40 %, to approximately 95% in 2017 and 2018. A large difference is observed for different mass categories, where satellites with a mass lower than 10 kg have a compliance of 86.4% compared to approximately 35% for heavier satellites. Analysis shows that this is mainly due to the lower orbits the former satellites were launched in. No large differences are observed between satellites with or without orbital control capabilities. These results reveal that compliance with the guidelines has been poor in the past but is increasing in recent years. This is mostly a result of operators choosing an orbit with a low altitude to have sufficient natural decay, and less of operators choosing to perform altitude lowering maneuvers at the end of operational phase to achieve compliance.
Advisors/Committee Members: Noomen, R. (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: Space Debris; Sun-synchronous; Maneuver Detection; Semi-analytical Propagation; Compliance
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APA (6th Edition):
Schild, M. (. (2021). Sun-synchronous Spacecraft Compliance with International Space Debris Guidelines. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:f105b7fc-b9d6-484e-9c70-c76ba994d0a4
Chicago Manual of Style (16th Edition):
Schild, Maarten (author). “Sun-synchronous Spacecraft Compliance with International Space Debris Guidelines.” 2021. Masters Thesis, Delft University of Technology. Accessed March 06, 2021.
http://resolver.tudelft.nl/uuid:f105b7fc-b9d6-484e-9c70-c76ba994d0a4.
MLA Handbook (7th Edition):
Schild, Maarten (author). “Sun-synchronous Spacecraft Compliance with International Space Debris Guidelines.” 2021. Web. 06 Mar 2021.
Vancouver:
Schild M(. Sun-synchronous Spacecraft Compliance with International Space Debris Guidelines. [Internet] [Masters thesis]. Delft University of Technology; 2021. [cited 2021 Mar 06].
Available from: http://resolver.tudelft.nl/uuid:f105b7fc-b9d6-484e-9c70-c76ba994d0a4.
Council of Science Editors:
Schild M(. Sun-synchronous Spacecraft Compliance with International Space Debris Guidelines. [Masters Thesis]. Delft University of Technology; 2021. Available from: http://resolver.tudelft.nl/uuid:f105b7fc-b9d6-484e-9c70-c76ba994d0a4
North-West University
28.
Dupper, Dawid.
An analysis of the international and South African legal framework relating to outer space pollution / Dawid Dupper
.
Degree: 2013, North-West University
URL: http://hdl.handle.net/10394/11542
► Since the start of the space race in the 1950‟s the outer space environment has significantly changed due to human expansion and the subsequent by-products…
(more)
▼ Since the start of the space race in the 1950‟s the outer space environment has significantly changed due to human expansion and the subsequent by-products known as outer space pollution/debris. As outer space rapidly evolved from a military high-ground into a commercialised asset exploited by private and state owned enterprises, the treaties negotiated in the 1960‟s and 1970‟s quickly became out-dated. As a result outer space, especially the orbits around the Earth are occupied by countless masses of non-functional manmade objects, some expected to remain for millions of years. This dissertation argues that the current national and international legal framework will be inadequate to address the problem of outer space pollution and that legal and political action will be necessary on a global scale. With the planned developments as set out in the National Space Policy, South Africa is set on becoming a leading provider of outer space services on the African continent and will, as a consequence, have a progressively bigger impact on the outer space environment. With a growing dependence on outer space technologies, developed and developing economies around the world cannot ignore the immense negative consequences that outer space debris could pose to their development. This study will thus, by examining the international and national legal framework regarding outer space pollution, provide legal recommendations pertaining to the principles and obligations that the South African legal framework will have to make provision for, in order to minimise the negative effect on the outer space environment.
Subjects/Keywords: Outer space law;
Environmental law;
Outer space pollution;
Outer space debris;
Outer space;
Ruimtereg;
Omgewingsreg;
Besoedeling;
Afval;
Buitenste ruim
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APA (6th Edition):
Dupper, D. (2013). An analysis of the international and South African legal framework relating to outer space pollution / Dawid Dupper
. (Thesis). North-West University. Retrieved from http://hdl.handle.net/10394/11542
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Dupper, Dawid. “An analysis of the international and South African legal framework relating to outer space pollution / Dawid Dupper
.” 2013. Thesis, North-West University. Accessed March 06, 2021.
http://hdl.handle.net/10394/11542.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Dupper, Dawid. “An analysis of the international and South African legal framework relating to outer space pollution / Dawid Dupper
.” 2013. Web. 06 Mar 2021.
Vancouver:
Dupper D. An analysis of the international and South African legal framework relating to outer space pollution / Dawid Dupper
. [Internet] [Thesis]. North-West University; 2013. [cited 2021 Mar 06].
Available from: http://hdl.handle.net/10394/11542.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Dupper D. An analysis of the international and South African legal framework relating to outer space pollution / Dawid Dupper
. [Thesis]. North-West University; 2013. Available from: http://hdl.handle.net/10394/11542
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Colorado
29.
Rao, Akhil.
The Economics of Orbit Use: Theory, Policy, and Measurement.
Degree: PhD, 2019, University of Colorado
URL: https://scholar.colorado.edu/econ_gradetds/98
► Earth's orbits are a congestible resource with novel dynamic externalities. In this dissertation my coauthors and I examine the nature of orbit use externalities, study…
(more)
▼ Earth's orbits are a congestible resource with novel dynamic externalities. In this dissertation my coauthors and I examine the nature of orbit use externalities, study the policy choice
space to classify existing policies and identify a class of optimal policies, consider the extent to which technological advancements can mitigate these externalities, and calculate the magnitude and time path of both an optimal satellite tax and the welfare gains from implementing it. Three key results emerge. First, open access to Earth's orbits drive the problems of excess collision risk and
debris production. Left to their own devices, profit-maximizing firms may collapse the resource for generations by triggering a cascade of hazardous-fragment-producing collisions. Second, though the majority of extant policy discussions have focused on instruments targeting satellite launches, optimal policies will target satellites in orbit rather than the act of launching satellites. Despite physical uncertainty over collisions, price or quantity policy implementations are equivalent and either can maximize social welfare.
Debris removal technologies cannot obviate the need for policy; they can only reduce equilibrium collision risk to the extent that satellite-owning firms pay for removal. Third, an optimal satellite tax (or orbit rental fee) for low-Earth orbit beginning in 2020 would start at approximately 40,000 USD per satellite per year, and grow at approximately 5.2% per year to preserve resource rents. The tax would increase the net present value of the satellite industry by around 1.75 trillion USD in 2020, and by over 4 trillion by 2040. Delaying action may be very costly: relative to a baseline of having begun optimal management in 2015, beginning optimal management in 2035 forgoes on the order of 4.6 trillion USD of permanent orbit use value in 2040.
Advisors/Committee Members: Daniel Kaffine, Jonathan Hughes, Martin Boileau, Miles Kimball, Matthew Burgess.
Subjects/Keywords: common resource; open access; pigouvian tax; policy choice; satellites; space debris; Environmental Policy; Space Vehicles
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APA (6th Edition):
Rao, A. (2019). The Economics of Orbit Use: Theory, Policy, and Measurement. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/econ_gradetds/98
Chicago Manual of Style (16th Edition):
Rao, Akhil. “The Economics of Orbit Use: Theory, Policy, and Measurement.” 2019. Doctoral Dissertation, University of Colorado. Accessed March 06, 2021.
https://scholar.colorado.edu/econ_gradetds/98.
MLA Handbook (7th Edition):
Rao, Akhil. “The Economics of Orbit Use: Theory, Policy, and Measurement.” 2019. Web. 06 Mar 2021.
Vancouver:
Rao A. The Economics of Orbit Use: Theory, Policy, and Measurement. [Internet] [Doctoral dissertation]. University of Colorado; 2019. [cited 2021 Mar 06].
Available from: https://scholar.colorado.edu/econ_gradetds/98.
Council of Science Editors:
Rao A. The Economics of Orbit Use: Theory, Policy, and Measurement. [Doctoral Dissertation]. University of Colorado; 2019. Available from: https://scholar.colorado.edu/econ_gradetds/98
University of Colorado
30.
Ingram, Gabriel J.
Development and Analysis of Volume Multi-Sphere Method Model Generation Using Electric Field Fitting.
Degree: MS, Aerospace Engineering Sciences, 2017, University of Colorado
URL: https://scholar.colorado.edu/asen_gradetds/175
► Electrostatic modeling of spacecraft has wide-reaching applications such as detumbling space debris in the Geosynchronous Earth Orbit regime before docking, servicing and tugging space debris…
(more)
▼ Electrostatic modeling of spacecraft has wide-reaching applications such as detumbling
space debris in the Geosynchronous Earth Orbit regime before docking, servicing and tugging
space debris to graveyard orbits, and Lorentz augmented orbits. The viability of electrostatic actuation control applications relies on faster-than-realtime characterization of the electrostatic interaction. The Volume Multi-Sphere Method (VMSM) seeks the optimal placement and radii of a small number of equipotential spheres to accurately model the electrostatic force and torque on a conducting
space object. Current VMSM models tuned using force and torque comparisons with commercially available finite element software are
subject to the modeled probe size and numerical errors of the software. This work first investigates fitting of VMSM models to Surface-MSM (SMSM) generated electrical field data, removing modeling dependence on probe geometry while significantly increasing performance and speed. A proposed electric field matching cost function is compared to a force and torque cost function, the inclusion of a self-capacitance constraint is explored and 4 degree-of-freedom VMSM models generated using electric field matching are investigated. The resulting E-field based VMSM development framework is illustrated on a box-shaped hub with a single solar panel, and convergence properties of select models are qualitatively analyzed. Despite the complex non-symmetric spacecraft geometry, elegantly simple 2-sphere VMSM solutions provide force and torque fits within a few percent.
Advisors/Committee Members: Hanspeter Schaub, Daniel Kubitschek, Robert Marshall.
Subjects/Keywords: Electrostatic Modeling; Multi-Sphere Method; spacecraft; space debris; Aerospace Engineering; Space Vehicles
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APA ·
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APA (6th Edition):
Ingram, G. J. (2017). Development and Analysis of Volume Multi-Sphere Method Model Generation Using Electric Field Fitting. (Masters Thesis). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/175
Chicago Manual of Style (16th Edition):
Ingram, Gabriel J. “Development and Analysis of Volume Multi-Sphere Method Model Generation Using Electric Field Fitting.” 2017. Masters Thesis, University of Colorado. Accessed March 06, 2021.
https://scholar.colorado.edu/asen_gradetds/175.
MLA Handbook (7th Edition):
Ingram, Gabriel J. “Development and Analysis of Volume Multi-Sphere Method Model Generation Using Electric Field Fitting.” 2017. Web. 06 Mar 2021.
Vancouver:
Ingram GJ. Development and Analysis of Volume Multi-Sphere Method Model Generation Using Electric Field Fitting. [Internet] [Masters thesis]. University of Colorado; 2017. [cited 2021 Mar 06].
Available from: https://scholar.colorado.edu/asen_gradetds/175.
Council of Science Editors:
Ingram GJ. Development and Analysis of Volume Multi-Sphere Method Model Generation Using Electric Field Fitting. [Masters Thesis]. University of Colorado; 2017. Available from: https://scholar.colorado.edu/asen_gradetds/175
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Open Access Theses and Dissertations