subject:(Orbital Debris)

Georgia Tech

1. Long, Alexandra Cheryl. Passively stable pyramid sail to deorbit small satellites.

Degree: PhD, Aerospace Engineering, 2018, Georgia Tech

► Orbital debris is a growing problem in low-Earth orbit, especially with a number of commercial companies intending to launch hundreds to thousands of micro-satellites into… (more)

Subjects/Keywords: Orbital debris; Deorbit stategies; Drag sail

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APA (6^th Edition):

Long, A. C. (2018). Passively stable pyramid sail to deorbit small satellites. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/60269

Chicago Manual of Style (16^th Edition):

Long, Alexandra Cheryl. “Passively stable pyramid sail to deorbit small satellites.” 2018. Doctoral Dissertation, Georgia Tech. Accessed March 08, 2021. http://hdl.handle.net/1853/60269.

MLA Handbook (7^th Edition):

Long, Alexandra Cheryl. “Passively stable pyramid sail to deorbit small satellites.” 2018. Web. 08 Mar 2021.

Vancouver:

Long AC. Passively stable pyramid sail to deorbit small satellites. [Internet] [Doctoral dissertation]. Georgia Tech; 2018. [cited 2021 Mar 08]. Available from: http://hdl.handle.net/1853/60269.

Council of Science Editors:

Long AC. Passively stable pyramid sail to deorbit small satellites. [Doctoral Dissertation]. Georgia Tech; 2018. Available from: http://hdl.handle.net/1853/60269

Virginia Tech

2. Thurber, Andrew. Investigations of Hypervelocity Impact Physics.

Degree: PhD, Mechanical Engineering, 2014, Virginia Tech

URL: http://hdl.handle.net/10919/95298

► Spacecraft and satellites in orbit are under an increasing threat of impact from orbital debris and naturally occurring meteoroids. While objects larger than 10 cm… (more)

▼ Spacecraft and satellites in orbit are under an increasing threat of impact from orbital debris and naturally occurring meteoroids. While objects larger than 10 cm are routinely tracked and avoided, collisions inevitably occur with smaller objects at relative velocities exceeding 10 km/s. Such hypervelocity impacts (HVI) create immense shock pressures and can melt or vaporize aerospace materials, even inducing brief plasmas at higher speeds. Sacrificial shields have been developed to protect critical components from damage under these conditions, but the response of many materials in such an extreme event is still poorly understood. This work presents the summary of computational analysis methods to quantify the relevant physical mechanisms at play in a hypervelocity impact. Strain rate-dependent behavior was investigated using several models, and fluid material descriptions were used to draw parallels under high shear rate loading. The production and expansion of impact plasmas were modeled and compared to experimental evidence. Additionally, a parametric study was performed on a multitude of possible material candidates for sacrificial shield design, and new shielding configurations were proposed. A comparison of material models indicated that the Johnson-Cook and Steinberg-Cochran-Guinan-Lund metallic formulations yielded the most consistent results with the lowest deviation from experimental measures in the strain rate regime of interest. Both meshless Lagrangian and quasi-Eulerian meshed schemes approximated the qualitative and quantitative characteristics of HVI debris clouds with average measurable errors under 5%. While the meshless methods showed better resolution of interfaces and small details, the meshed methods were shown to converge faster under several metrics with fewer regions of spurious instability. Additionally, a new technique was introduced using hypothetical viscous fluids to approximate debris cloud behavior, which showed good correlation to experimental results when such models were constructed using the shear rates seen in hypervelocity impacts. Formulations using non-Newtonian fluids showed additional capability in approximating solid behavior, both quantitatively and qualitatively. Such fluid models are significant, in that they reproduced the qualitative and quantitative characteristics of evolving debris clouds with better fidelity than purely hydrodynamic models using inviscid fluids. This indicates that while inertial effects can dominate overdriven shock phenomena, neglecting shear forces invariably introduces errors; such forces can instead be simplistically approximated via viscous models. The viscous approximation also allowed for a successful scaling analysis using dimensionless Pi terms, which was unfeasible using solid constitutive relations. Attempts to model plasma dynamics saw success in the simulation of a laser ablation-driven flyer plate by using a hot gas with solid initial conditions; similar strategies were used to analyze plasma production in hypervelocity… Advisors/Committee Members: Bayandor, Javid (committeechair), Battaglia, Francine (committee member), O'Brien, Walter F. Jr. (committee member), Scales, Wayne A. (committee member), Samareh, Jamshid A. (committee member).

Subjects/Keywords: impact; orbital debris; finite element; shock physics

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APA (6^th Edition):

Thurber, A. (2014). Investigations of Hypervelocity Impact Physics. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/95298

Chicago Manual of Style (16^th Edition):

Thurber, Andrew. “Investigations of Hypervelocity Impact Physics.” 2014. Doctoral Dissertation, Virginia Tech. Accessed March 08, 2021. http://hdl.handle.net/10919/95298.

MLA Handbook (7^th Edition):

Thurber, Andrew. “Investigations of Hypervelocity Impact Physics.” 2014. Web. 08 Mar 2021.

Vancouver:

Thurber A. Investigations of Hypervelocity Impact Physics. [Internet] [Doctoral dissertation]. Virginia Tech; 2014. [cited 2021 Mar 08]. Available from: http://hdl.handle.net/10919/95298.

Council of Science Editors:

Thurber A. Investigations of Hypervelocity Impact Physics. [Doctoral Dissertation]. Virginia Tech; 2014. Available from: http://hdl.handle.net/10919/95298

University of Colorado

3. Anderson, Paul V. Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime.

Degree: PhD, Aerospace Engineering Sciences, 2010, University of Colorado

URL: https://scholar.colorado.edu/asen_gradetds/14

► The geosynchronous orbit (GEO) is a unique commodity of the satellite industry that is becoming increasingly contaminated with orbital debris, but is heavily populated… (more)

Subjects/Keywords: active debris removal; geostationary orbit; geosynchronous orbit; orbital debris; Aerospace Engineering

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APA (6^th Edition):

Anderson, P. V. (2010). Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/14

Chicago Manual of Style (16^th Edition):

Anderson, Paul V. “Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime.” 2010. Doctoral Dissertation, University of Colorado. Accessed March 08, 2021. https://scholar.colorado.edu/asen_gradetds/14.

MLA Handbook (7^th Edition):

Anderson, Paul V. “Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime.” 2010. Web. 08 Mar 2021.

Vancouver:

Anderson PV. Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime. [Internet] [Doctoral dissertation]. University of Colorado; 2010. [cited 2021 Mar 08]. Available from: https://scholar.colorado.edu/asen_gradetds/14.

Council of Science Editors:

Anderson PV. Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime. [Doctoral Dissertation]. University of Colorado; 2010. Available from: https://scholar.colorado.edu/asen_gradetds/14

University of Colorado

4. Anderson, Paul Vincent. Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime.

Degree: PhD, Aerospace Engineering Sciences, 2015, University of Colorado

URL: https://scholar.colorado.edu/asen_gradetds/91

► The geosynchronous orbit (GEO) is a unique commodity of the satellite industry that is becoming increasingly contaminated with orbital debris, but is heavily populated… (more)

▼ The geosynchronous orbit (GEO) is a unique commodity of the satellite industry that is becoming increasingly contaminated with orbital debris, but is heavily populated with high-value assets from the civil, commercial, and defense sectors. The GEO arena is home to hundreds of communications, data transmission, and intelligence satellites collectively insured for an estimated 18.3 billion USD. As the lack of natural cleansing mechanisms at the GEO altitude renders the lifetimes of GEO debris essentially infinite, conjunction and risk assessment must be performed to safeguard operational assets from debris collisions. In this thesis, longitude-dependent debris congestion is characterized by predicting the number of near-miss events per day for every longitude slot at GEO, using custom debris propagation tools and a torus intersection metric. Near-miss events with the present-day debris population are assigned risk levels based on GEO-relative position and speed, and this risk information is used to prioritize the population for debris removal target selection. Long-term projections of debris growth under nominal launch traffic, mitigation practices, and fragmentation events are also discussed, and latitudinal synchronization of the GEO debris population is explained via node variations arising from luni-solar gravity. In addition to characterizing localized debris congestion in the GEO ring, this thesis further investigates the conjunction risk to operational satellites or debris removal systems applying low-thrust propulsion to raise orbit altitude at end-of-life to a super-synchronous disposal orbit. Conjunction risks as a function of thrust level, miss distance, longitude, and semi-major axis are evaluated, and a guidance method for evading conjuncting debris with continuous thrust by means of a thrust heading change via single-shooting is developed. Advisors/Committee Members: Hanspeter Schaub, Brandon Jones, Jeffrey Parker, Juan Restrepo, Darren McKnight.

Subjects/Keywords: active debris removal; geostationary orbit; geosynchronous orbit; orbital debris; Aerospace Engineering

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APA (6^th Edition):

Anderson, P. V. (2015). Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/91

Chicago Manual of Style (16^th Edition):

Anderson, Paul Vincent. “Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime.” 2015. Doctoral Dissertation, University of Colorado. Accessed March 08, 2021. https://scholar.colorado.edu/asen_gradetds/91.

MLA Handbook (7^th Edition):

Anderson, Paul Vincent. “Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime.” 2015. Web. 08 Mar 2021.

Vancouver:

Anderson PV. Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime. [Internet] [Doctoral dissertation]. University of Colorado; 2015. [cited 2021 Mar 08]. Available from: https://scholar.colorado.edu/asen_gradetds/91.

Council of Science Editors:

Anderson PV. Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime. [Doctoral Dissertation]. University of Colorado; 2015. Available from: https://scholar.colorado.edu/asen_gradetds/91

Virginia Tech

5. 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)

Subjects/Keywords: orbital debris; laser debris removal; constellation design; space situational awareness

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APA (6^th 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 (16^th Edition):

Ohriner, Ethan Benjamin Lewis. “Investigation of Orbital Debris Situational Awareness with Constellation Design and Evaluation.” 2021. Masters Thesis, Virginia Tech. Accessed March 08, 2021. http://hdl.handle.net/10919/102096.

MLA Handbook (7^th Edition):

Ohriner, Ethan Benjamin Lewis. “Investigation of Orbital Debris Situational Awareness with Constellation Design and Evaluation.” 2021. Web. 08 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 08]. 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

University of Colorado

6. 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 (6^th 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 (16^th 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 08, 2021. https://scholar.colorado.edu/asen_gradetds/82.

MLA Handbook (7^th Edition):

Jasper, Lee E Z. “Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects.” 2014. Web. 08 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 08]. 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

University of Manitoba

7. Cherniaev, Aleksandr. Design and analysis of orbital debris protection for spacecraft composite pressure vessels.

Degree: Mechanical Engineering, 2016, University of Manitoba

URL: http://hdl.handle.net/1993/31949

► Being parts of spacecraft systems, composite overwrapped pressure vessels (COPVs) are exposed to orbital debris environment. In the case of impact of orbital debris on… (more)

▼ Being parts of spacecraft systems, composite overwrapped pressure vessels (COPVs) are exposed to orbital debris environment. In the case of impact of orbital debris on a composite vessel, the vessel may fail non-catastrophically, possibly resulting in the loss of spacecraft, or catastrophically, producing numerous non-trackable fragments, which may result in the loss of spacecraft and also affect and destroy other active and future spacecraft in neighbor orbits. Consequences of orbital debris impacts, therefore, must be minimized with the use of an appropriate design strategy. For a weight-efficient design providing high level of protection for spacecraft composite pressure vessels, the following design strategy is suggested in this study: • Exclude any involvement of the pressure wall in resisting orbital debris impacts by means of an external shielding designed for the same tolerable risk of penetration as the shielding of any other critical subsystem of the spacecraft (R1tol; typically, 1-5%); • Ensure that the shielded COPV will not fail catastrophically under conditions corresponding to even stricter tolerable risk of penetration (R2tol), such that R2tol < R1tol, which can correspond to the tolerable risk of accidental explosion during mission operations in Orbit (typically, 0.1%). Implementation of the proposed design paradigm required 1) weight-efficient shielding systems to be designed against highly probable impacts of small-size orbital debris; and 2) a procedure capable of predicting the behavior of a shielded COPV subjected to perforating orbital debris impacts to be developed. Correspondingly, this study focused on these two aspects. First, five different external shielding systems were analysed for their weight efficiency when designed against small-size (1 mm) orbital debris impacts, including a novel orbital debris shield with ceramo-metallic bumper. Conducted evaluation made it possible to identify and recommend weight-efficient shielding designs in such categories as “Single purpose orbital debris shields” and “Multipurpose structural panels”. In this part, the results are mainly applicable to the spacecraft in low Earth Orbit. Second, a two-step modeling procedure was proposed to simulate behavior of shielded composite overwrapped pressure vessels when subjected to perforating impacts by large-size hypervelocity projectiles. The procedure can be used to evaluate vulnerability of a shielded vessel to catastrophic failure. Advisors/Committee Members: Telichev, Igor (Mechanical Engineering) (supervisor), Bassim, Nabil (Mechanical Engineering) Jayaraman, Raghavan (Mechanical Engineering) Svecova, Dagmar (Civil Engineering) Jablonski, Alexander (David Florida Laboratory, Canadian Space Agency) (examiningcommittee).

Subjects/Keywords: Orbital debris; Composite pressure vessel; Hypervelocity impact; Impact shielding; Impact modeling

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APA (6^th Edition):

Cherniaev, A. (2016). Design and analysis of orbital debris protection for spacecraft composite pressure vessels. (Thesis). University of Manitoba. Retrieved from http://hdl.handle.net/1993/31949

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

Chicago Manual of Style (16^th Edition):

Cherniaev, Aleksandr. “Design and analysis of orbital debris protection for spacecraft composite pressure vessels.” 2016. Thesis, University of Manitoba. Accessed March 08, 2021. http://hdl.handle.net/1993/31949.

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

MLA Handbook (7^th Edition):

Cherniaev, Aleksandr. “Design and analysis of orbital debris protection for spacecraft composite pressure vessels.” 2016. Web. 08 Mar 2021.

Vancouver:

Cherniaev A. Design and analysis of orbital debris protection for spacecraft composite pressure vessels. [Internet] [Thesis]. University of Manitoba; 2016. [cited 2021 Mar 08]. Available from: http://hdl.handle.net/1993/31949.

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

Council of Science Editors:

Cherniaev A. Design and analysis of orbital debris protection for spacecraft composite pressure vessels. [Thesis]. University of Manitoba; 2016. Available from: http://hdl.handle.net/1993/31949

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

University of Toronto

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

Degree: PhD, 2020, University of Toronto

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

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

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

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

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

APA (6^th Edition):

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

Chicago Manual of Style (16^th Edition):

Hakima, Houman. “A New Approach to Active Removal of Space Debris.” 2020. Doctoral Dissertation, University of Toronto. Accessed March 08, 2021. http://hdl.handle.net/1807/101359.

MLA Handbook (7^th Edition):

Hakima, Houman. “A New Approach to Active Removal of Space Debris.” 2020. Web. 08 Mar 2021.

Vancouver:

Hakima H. A New Approach to Active Removal of Space Debris. [Internet] [Doctoral dissertation]. University of Toronto; 2020. [cited 2021 Mar 08]. Available from: http://hdl.handle.net/1807/101359.

Council of Science Editors:

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

University of the Western Cape

9. 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)

Subjects/Keywords: Space Debris; Orbital Debris; Developing states; BRICS (Brazil, Russia, India, China and South Africa); Space junk

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

APA (6^th 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 (16^th Edition):

Logday, Ayesha. “Space Debris and the BRICS countries: The role of international Environmental Law. ” 2019. Thesis, University of the Western Cape. Accessed March 08, 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 (7^th Edition):

Logday, Ayesha. “Space Debris and the BRICS countries: The role of international Environmental Law. ” 2019. Web. 08 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 08]. 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

10. O'Gorman, John. The Cost of Clean Space- A Study of the Additional Fuel Costs of Launching Above Low Earth Orbit.

Degree: MS, Public Policy (CLA), 2018, Rochester Institute of Technology

URL: https://scholarworks.rit.edu/theses/9796

► Ever since the launch of Sputnik in 1957, humans have put over 40,000 pieces of debris into orbit around the Earth. In particular, most… (more)

Subjects/Keywords: Debris; LEO; Orbital; Space; Sustainability

…infrastructure, an increasing number of launches and competing interests makes 7 orbital debris a… …region because it is the most economical to reach. Therefore, most orbital debris is… …42,000 km which is also of interest to debris studies because of its unique orbital period of… …to mitigate the creation and effects of orbital debris [to the FCC]" (… …control of the hazards of orbital debris is reassuring, but not enough to solve the problem of…

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APA (6^th Edition):

O'Gorman, J. (2018). The Cost of Clean Space- A Study of the Additional Fuel Costs of Launching Above Low Earth Orbit. (Masters Thesis). Rochester Institute of Technology. Retrieved from https://scholarworks.rit.edu/theses/9796

Chicago Manual of Style (16^th Edition):

O'Gorman, John. “The Cost of Clean Space- A Study of the Additional Fuel Costs of Launching Above Low Earth Orbit.” 2018. Masters Thesis, Rochester Institute of Technology. Accessed March 08, 2021. https://scholarworks.rit.edu/theses/9796.

MLA Handbook (7^th Edition):

O'Gorman, John. “The Cost of Clean Space- A Study of the Additional Fuel Costs of Launching Above Low Earth Orbit.” 2018. Web. 08 Mar 2021.

Vancouver:

O'Gorman J. The Cost of Clean Space- A Study of the Additional Fuel Costs of Launching Above Low Earth Orbit. [Internet] [Masters thesis]. Rochester Institute of Technology; 2018. [cited 2021 Mar 08]. Available from: https://scholarworks.rit.edu/theses/9796.

Council of Science Editors:

O'Gorman J. The Cost of Clean Space- A Study of the Additional Fuel Costs of Launching Above Low Earth Orbit. [Masters Thesis]. Rochester Institute of Technology; 2018. Available from: https://scholarworks.rit.edu/theses/9796

Penn State University

11. McTernan, Jesse Kane. DEVELOPMENT OF A MODELING CAPABILITY FOR ENERGY HARVESTING MODULES IN ELECTRODYNAMIC TETHER SYSTEMS .

Degree: 2011, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/12063

► Electrodynamic tethers can be used to harvest energy onboard a spacecraft orbiting the Earth or any planetary body with a magnetic ﬁeld and surrounding plasma.… (more)

▼ Electrodynamic tethers can be used to harvest energy onboard a spacecraft orbiting the Earth or any planetary body with a magnetic ﬁeld and surrounding plasma. The motion of the conductive tether in the Earth’s magnetic ﬁeld generates an electromotive force along the length of the tether. The ionospheric plasma completes the circuit to allow current to ﬂow through the tether and, ultimately, through the energy-handling components on the spacecraft. This energy can be used immediately or stored in batteries, capacitors, ﬂywheels, or other storage devices. As current ﬂows through the tether, the spacecraft loses altitude due to the electrodynamic force created by the ﬂow of electrons in the magnetic ﬁeld. One can think of the electrodynamic tether system as transforming orbital potential energy into electrical energy. The system can regain the lost altitude by forcing current to ﬂow against the generated electromotive force, creating a thrust in the direction of motion. Electrodynamic tether systems can augment a spacecraft’s performance or enable capabilities that were previously unobtainable, such as energy harvesting while in the Earth’s shadow. The objectives of this research were to evaluate the feasibility, performance, trade-oﬀs, and net beneﬁt of electrodynamic-tether power generation for space missions. Speciﬁc objectives included creating system concepts for various classes and sizes of spacecraft, characterizing eﬃciencies, and comparing alternative storage technologies. Our research has found that large satellites have the potential to harvest as much as kilowatts of power at some load. Small electrodynamic tether systems the size of CubeSats have the potential to harvest 50% more energy than solar panel systems alone and can produce over 40-watts-average power useful during, for example, a 10-minute ground station overpass. An energy storage module was added to our simulation software that models physical storage devices, such as supercapacitors and lithium–ion batteries, and a generic device. It also investigates orbital energy concepts such as in-plane energy changes, energy needed to torque an orbit, and the conservation of energy as orbital energy is transferred into electrical energy. In spite of the enhanced capabilities provided to orbiting spacecraft by electrodynamic tether systems, signiﬁcant research remains to realize the promise of electrodynamic tether systems as a unique solution to the energy needs of satellites. Advisors/Committee Members: Sven G Bilen, Thesis Advisor/Co-Advisor, Sven G Bilen, Thesis Advisor/Co-Advisor.

Subjects/Keywords: debris mitigation; orbital energy; enrgy harvesting; energy; space tether; electrodynamic tether; propulsion

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APA (6^th Edition):

McTernan, J. K. (2011). DEVELOPMENT OF A MODELING CAPABILITY FOR ENERGY HARVESTING MODULES IN ELECTRODYNAMIC TETHER SYSTEMS . (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/12063

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

Chicago Manual of Style (16^th Edition):

McTernan, Jesse Kane. “DEVELOPMENT OF A MODELING CAPABILITY FOR ENERGY HARVESTING MODULES IN ELECTRODYNAMIC TETHER SYSTEMS .” 2011. Thesis, Penn State University. Accessed March 08, 2021. https://submit-etda.libraries.psu.edu/catalog/12063.

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

MLA Handbook (7^th Edition):

McTernan, Jesse Kane. “DEVELOPMENT OF A MODELING CAPABILITY FOR ENERGY HARVESTING MODULES IN ELECTRODYNAMIC TETHER SYSTEMS .” 2011. Web. 08 Mar 2021.

Vancouver:

McTernan JK. DEVELOPMENT OF A MODELING CAPABILITY FOR ENERGY HARVESTING MODULES IN ELECTRODYNAMIC TETHER SYSTEMS . [Internet] [Thesis]. Penn State University; 2011. [cited 2021 Mar 08]. Available from: https://submit-etda.libraries.psu.edu/catalog/12063.

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

Council of Science Editors:

McTernan JK. DEVELOPMENT OF A MODELING CAPABILITY FOR ENERGY HARVESTING MODULES IN ELECTRODYNAMIC TETHER SYSTEMS . [Thesis]. Penn State University; 2011. Available from: https://submit-etda.libraries.psu.edu/catalog/12063

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

University of Toronto

12. Cotten, Scott Bradley. Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission.

Degree: 2014, University of Toronto

URL: http://hdl.handle.net/1807/68553

►

In the context of space debris mitigation, a major challenge currently facing the space community is the removal of nano and microsatellites from orbit following… (more)

Subjects/Keywords: Magnetic Attitude Control; Microsatellite Technology; Orbital Debris; Spacecraft Deorbiting; Thermal Control of Space Systems; 0538

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APA (6^th Edition):

Cotten, S. B. (2014). Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/68553

Chicago Manual of Style (16^th Edition):

Cotten, Scott Bradley. “Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission.” 2014. Masters Thesis, University of Toronto. Accessed March 08, 2021. http://hdl.handle.net/1807/68553.

MLA Handbook (7^th Edition):

Cotten, Scott Bradley. “Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission.” 2014. Web. 08 Mar 2021.

Vancouver:

Cotten SB. Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission. [Internet] [Masters thesis]. University of Toronto; 2014. [cited 2021 Mar 08]. Available from: http://hdl.handle.net/1807/68553.

Council of Science Editors:

Cotten SB. Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission. [Masters Thesis]. University of Toronto; 2014. Available from: http://hdl.handle.net/1807/68553

University of Colorado

13. Bennett, Trevor John. On-Orbit 3-Dimensional Electrostatic Detumble for Generic Spacecraft Geometries.

Degree: PhD, 2017, University of Colorado

URL: https://scholar.colorado.edu/asen_gradetds/226

► In recent years, there is a growing interest in active debris removal and on-orbit servicing of Earth orbiting assets. The growing need for such… (more)

▼ In recent years, there is a growing interest in active debris removal and on-orbit servicing of Earth orbiting assets. The growing need for such approaches is often exemplified by the Iridium-Kosmos collision in 2009 that generated thousands of debris fragments. There exists a variety of active debris removal and on-orbit servicing technologies in development. Conventional docking mechanisms and mechanical capture by actuated manipulators, exemplified by NASA's Restore-L mission, require slow target tumble rates or more aggressive circumnavigation rate matching. The tumble rate limitations can be overcome with flexible capture systems such nets, harpoons, or tethers yet these systems require complex deployment, towing, and/or interfacing strategies to avoid servicer and target damage. Alternatively, touchless methods overcome the tumble rate limitations by provide detumble control prior to a mechanical interface. This thesis explores electrostatic detumble technology to touchlessly reduce large target rotation rates of Geostationary satellites and debris. The technical challenges preceding flight implementation largely reside in the long-duration formation flying guidance, navigation, and control of a servicer spacecraft equipped with electrostatic charge transfer capability. Leveraging prior research into the electrostatic charging of spacecraft, electrostatic detumble control formulations are developed for both axisymmetric and generic target geometries. A novel relative position vector and associated relative orbit control approach is created to manage the long-duration proximity operations. Through detailed numerical simulations, the proposed detumble and relative motion control formulations demonstrate detumble of several thousand kilogram spacecraft tumbling at several degrees per second in only several days. The availability, either through modeling or sensing, of the relative attitude, relative position, and electrostatic potential are among key concerns with implementation of electrostatic detumble control on-orbit. Leveraging an extended Kalman filter scheme, the relative position information is readily obtained. In order to touchlessly acquire the target electrostatic potential, a nested two-time scale Kalman filter is employed to provide real-time estimates of both relative position and electrostatic potential while on-orbit. The culmination of the presented control formulations for generic spacecraft geometries, the proximity and formation flying control capability, and the availability of necessary state information provide significant contributions towards the viability of electrostatic detumble mission concepts. Advisors/Committee Members: Hanspeter Schaub, Jay McMahon, Jeffrey Parker, Elizabeth Bradley, Zoltan Sternovsky.

Subjects/Keywords: contactless/touchless; electrostatic actuation; formation flying; orbital debris; relative navigation; Aerospace Engineering; Physics

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APA (6^th Edition):

Bennett, T. J. (2017). On-Orbit 3-Dimensional Electrostatic Detumble for Generic Spacecraft Geometries. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/226

Chicago Manual of Style (16^th Edition):

Bennett, Trevor John. “On-Orbit 3-Dimensional Electrostatic Detumble for Generic Spacecraft Geometries.” 2017. Doctoral Dissertation, University of Colorado. Accessed March 08, 2021. https://scholar.colorado.edu/asen_gradetds/226.

MLA Handbook (7^th Edition):

Bennett, Trevor John. “On-Orbit 3-Dimensional Electrostatic Detumble for Generic Spacecraft Geometries.” 2017. Web. 08 Mar 2021.

Vancouver:

Bennett TJ. On-Orbit 3-Dimensional Electrostatic Detumble for Generic Spacecraft Geometries. [Internet] [Doctoral dissertation]. University of Colorado; 2017. [cited 2021 Mar 08]. Available from: https://scholar.colorado.edu/asen_gradetds/226.

Council of Science Editors:

Bennett TJ. On-Orbit 3-Dimensional Electrostatic Detumble for Generic Spacecraft Geometries. [Doctoral Dissertation]. University of Colorado; 2017. Available from: https://scholar.colorado.edu/asen_gradetds/226

University of Manitoba

14. Jones, Alexander James Bryan. Modelling of hypervelocity impact on foam-core sandwich panel with enhanced capability for orbital debris protection.

Degree: Mechanical Engineering, 2018, University of Manitoba

URL: http://hdl.handle.net/1993/32882

► Many commonly-used orbits are increasingly cluttered with orbital debris, posing a significant threat to space assets, which require enhanced protection. Recent studies demonstrate that foam-core… (more)

Subjects/Keywords: Orbital debris; Numerical modelling; Metal foam core; Hypervelocity impact; Autodyn; MMOD; HVI

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APA (6^th Edition):

Jones, A. J. B. (2018). Modelling of hypervelocity impact on foam-core sandwich panel with enhanced capability for orbital debris protection. (Masters Thesis). University of Manitoba. Retrieved from http://hdl.handle.net/1993/32882

Chicago Manual of Style (16^th Edition):

Jones, Alexander James Bryan. “Modelling of hypervelocity impact on foam-core sandwich panel with enhanced capability for orbital debris protection.” 2018. Masters Thesis, University of Manitoba. Accessed March 08, 2021. http://hdl.handle.net/1993/32882.

MLA Handbook (7^th Edition):

Jones, Alexander James Bryan. “Modelling of hypervelocity impact on foam-core sandwich panel with enhanced capability for orbital debris protection.” 2018. Web. 08 Mar 2021.

Vancouver:

Jones AJB. Modelling of hypervelocity impact on foam-core sandwich panel with enhanced capability for orbital debris protection. [Internet] [Masters thesis]. University of Manitoba; 2018. [cited 2021 Mar 08]. Available from: http://hdl.handle.net/1993/32882.

Council of Science Editors:

Jones AJB. Modelling of hypervelocity impact on foam-core sandwich panel with enhanced capability for orbital debris protection. [Masters Thesis]. University of Manitoba; 2018. Available from: http://hdl.handle.net/1993/32882

University of Toronto

15. Bazzocchi, Michael Christopher Francesco. Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization.

Degree: PhD, 2018, University of Toronto

URL: http://hdl.handle.net/1807/89883

► In this thesis, an overall framework is established for the redirection of near-Earth asteroids using spacecraft formation strategies in order to access and utilize asteroid… (more)

▼ In this thesis, an overall framework is established for the redirection of near-Earth asteroids using spacecraft formation strategies in order to access and utilize asteroid resources. The framework is parsed into three critical areas of research, namely, redirection methods, trajectory transfer, and formation design and control. Additionally, research into the application of asteroid redirection methods to the related area of space debris removal is discussed. In the area of redirection methods, in-depth analyses and systematic comparisons are conducted. The performance of each method is evaluated through several multicriteria assessment techniques and Monte Carlo analysis is used to quantify the uncertainty intrinsic to the asteroid population. The redirection methods are evaluated with respect to their suitability for spacecraft formation. The trajectory transfer research focuses on the study of Arjuna-type asteroids, which are considered excellent targets for redirection missions. The research can be divided into two main studies using low-thrust methods: i) an assessment of the Arjuna domain, and ii) an approach to optimal three-dimensional transfer trajectory design. The first study investigates the feasibility of transferring an Arjuna-type asteroid using a minimized form of Gauss’s variational equations, spacecraft sizing metrics, and mission cost analysis formulae. The second study outlines the design of a stochastic optimization approach to three-dimensional asteroid transfer from its initial orbit to an orbit in the Earth-Moon system. The research employs pseudo-equinoctial exponential shaping to design the transfer trajectory and quantifies the uncertainty in asteroid parameters through Monte Carlo analysis. In the area of formation design and control, the thesis develops an optimal approach to asteroid redirection using landed thruster formations. First, the mission design for a landed formation of spacecraft is analysed and optimized from the perspective of resource utilization. Secondly, a method for determining the landing locations and thruster orientations for time-optimal detumbling of an asteroid using a landed formation of spacecraft is formulated. The method models the asteroid as a high resolution convex polyhedra, determines feasible landing locations and thrust directions, and optimizes a spacecraft formation to minimize detumbling time while ensuring full control. Through systematically presenting work in these three areas, this research helps set the groundwork for future researchers, corporations, and government agencies to seize the opportunities provided by asteroid resources. Advisors/Committee Members: Emami, M. Reza, Aerospace Science and Engineering.

Subjects/Keywords: Asteroid Redirection; Formation Control; Orbital Dynamics; Spacecraft Formation; Space Debris; Transfer Trajectory Design; 0538

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APA (6^th Edition):

Bazzocchi, M. C. F. (2018). Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization. (Doctoral Dissertation). University of Toronto. Retrieved from http://hdl.handle.net/1807/89883

Chicago Manual of Style (16^th Edition):

Bazzocchi, Michael Christopher Francesco. “Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization.” 2018. Doctoral Dissertation, University of Toronto. Accessed March 08, 2021. http://hdl.handle.net/1807/89883.

MLA Handbook (7^th Edition):

Bazzocchi, Michael Christopher Francesco. “Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization.” 2018. Web. 08 Mar 2021.

Vancouver:

Bazzocchi MCF. Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization. [Internet] [Doctoral dissertation]. University of Toronto; 2018. [cited 2021 Mar 08]. Available from: http://hdl.handle.net/1807/89883.

Council of Science Editors:

Bazzocchi MCF. Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization. [Doctoral Dissertation]. University of Toronto; 2018. Available from: http://hdl.handle.net/1807/89883

Cal Poly

16. Hawkins, Robert A, Jr. Analysis of an Inflatable Gossamer Device to Efficiently De-Orbit CubeSats.

Degree: MS, Aerospace Engineering, 2013, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/1139 ; 10.15368/theses.2013.219

► There is an increased need for spacecraft to quickly and efficiently de-orbit themselves as the amount of debris in orbit around Earth grows. Defunct… (more)

Subjects/Keywords: CubeSat; de-orbit; orbital debris; drag; orbit; Gossamer; Astrodynamics; Propulsion and Power; Space Vehicles

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APA (6^th Edition):

Hawkins, Robert A, J. (2013). Analysis of an Inflatable Gossamer Device to Efficiently De-Orbit CubeSats. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1139 ; 10.15368/theses.2013.219

Chicago Manual of Style (16^th Edition):

Hawkins, Robert A, Jr. “Analysis of an Inflatable Gossamer Device to Efficiently De-Orbit CubeSats.” 2013. Masters Thesis, Cal Poly. Accessed March 08, 2021. https://digitalcommons.calpoly.edu/theses/1139 ; 10.15368/theses.2013.219.

MLA Handbook (7^th Edition):

Hawkins, Robert A, Jr. “Analysis of an Inflatable Gossamer Device to Efficiently De-Orbit CubeSats.” 2013. Web. 08 Mar 2021.

Vancouver:

Hawkins, Robert A J. Analysis of an Inflatable Gossamer Device to Efficiently De-Orbit CubeSats. [Internet] [Masters thesis]. Cal Poly; 2013. [cited 2021 Mar 08]. Available from: https://digitalcommons.calpoly.edu/theses/1139 ; 10.15368/theses.2013.219.

Council of Science Editors:

Hawkins, Robert A J. Analysis of an Inflatable Gossamer Device to Efficiently De-Orbit CubeSats. [Masters Thesis]. Cal Poly; 2013. Available from: https://digitalcommons.calpoly.edu/theses/1139 ; 10.15368/theses.2013.219

17. Horn, Adam Charles. A Low Cost Inflatable CubeSat Drag Brake Utilizing Sublimation.

Degree: MS, Mechanical & Aerospace Engineering, 2017, Old Dominion University

URL: 9780355409376 ; https://digitalcommons.odu.edu/mae_etds/28

► The United Nations Inter-Agency Debris Coordination Committee has adopted a 25-year post-mission lifetime requirement for any satellite orbiting below 2000 km in order to… (more)

Subjects/Keywords: CubeSat; Drag brake; Inflatable; Orbital debris; Space; Sublimation; Aerospace Engineering; Mechanical Engineering

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APA (6^th Edition):

Horn, A. C. (2017). A Low Cost Inflatable CubeSat Drag Brake Utilizing Sublimation. (Thesis). Old Dominion University. Retrieved from 9780355409376 ; https://digitalcommons.odu.edu/mae_etds/28

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

Chicago Manual of Style (16^th Edition):

Horn, Adam Charles. “A Low Cost Inflatable CubeSat Drag Brake Utilizing Sublimation.” 2017. Thesis, Old Dominion University. Accessed March 08, 2021. 9780355409376 ; https://digitalcommons.odu.edu/mae_etds/28.

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

MLA Handbook (7^th Edition):

Horn, Adam Charles. “A Low Cost Inflatable CubeSat Drag Brake Utilizing Sublimation.” 2017. Web. 08 Mar 2021.

Vancouver:

Horn AC. A Low Cost Inflatable CubeSat Drag Brake Utilizing Sublimation. [Internet] [Thesis]. Old Dominion University; 2017. [cited 2021 Mar 08]. Available from: 9780355409376 ; https://digitalcommons.odu.edu/mae_etds/28.

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

Council of Science Editors:

Horn AC. A Low Cost Inflatable CubeSat Drag Brake Utilizing Sublimation. [Thesis]. Old Dominion University; 2017. Available from: 9780355409376 ; https://digitalcommons.odu.edu/mae_etds/28

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

18. Hofsteenge, R. (author). Computational Methods for the Long-Term Propagation of Space Debris Orbits.

Degree: 2013, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:eee70164-4c99-470d-b8ee-5314ffcf63f8

►

Space debris poses a significant problem for the space sector. This problem relates to potential collisions of debris objects with active satellites, which in many… (more)

▼

Space debris poses a significant problem for the space sector. This problem relates to potential collisions of debris objects with active satellites, which in many cases will lead to catastrophic damage. Due to the absence of natural decay mechanisms in the higher regions of space, debris objects in these regions have very long orbital lifetimes. In order to assess the hazards posed to active satellites, it is relevant to be able to predict how the orbits of these debris objects behave on long timescales. A simulation code in C++ has been created for this thesis project, capable of efficient propagation of space debris trajectories over long periods of time (typically a century or more), while taking into account various relevant perturbing forces. The simulation code can be applied to simulate the orbits of debris objects with a wide range of area-to-mass ratios, from intact satellites to tiny flecks of paint. The results produced with the simulation code have been verified to be consistent with results presented in recent research papers on space debris. An extensive performance comparison has been made regarding the efficiency of different computational methods for carrying out accurate, long-term integrations of space debris orbits. Both traditional integration methods and symplectic integration methods were tested, the latter of which are interesting because of their energy conservation properties. All methods were also combined with different formulations of the equations of motion. Of the methods tested, the Dormand-Prince 8(7) integration method combined with Gauss' form of Lagrange's planetary equations in modified equinoctial elements was found to be the most efficient. The performance of the symplectic integration methods was markedly less for this application than for the integration of completely Hamiltonian systems, though it was certainly acceptable. The simulation code was also applied to predict the long-term orbital evolution for debris objects in GEO and GNSS graveyard orbits. While proposed GEO graveyard orbits were found to be safe, graveyard orbits in the GNSS region were found to be susceptible to resonances induced by the luni-solar perturbations, and hence, require a careful selection of the initial orbital parameters. In all cases, debris objects with high area-to-mass ratios were determined to be dangerous to active satellites, regardless of the initial conditions of the graveyard orbit.

Astrodynamics and Space Missions

Aerospace Engineering

Advisors/Committee Members: Noomen, R. (mentor).

Subjects/Keywords: space debris; astrodynamics; numerical integration; orbital perturbations

…regions generally have very long orbital lifetimes. Simulating the orbits of debris objects over… …long-term orbital developments of debris objects in graveyard orbits will be considered in… …or orbital debris has been defined by the Inter-Agency Space Debris Coordination Committee… …for the future of spaceflight. 2.3 The Space Debris Environment The higher the orbital… …Figure 2.2. As can be seen in the figure, most orbital debris resides within 2,000 km of the…

10 more images…

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APA (6^th Edition):

Hofsteenge, R. (. (2013). Computational Methods for the Long-Term Propagation of Space Debris Orbits. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:eee70164-4c99-470d-b8ee-5314ffcf63f8

Chicago Manual of Style (16^th Edition):

Hofsteenge, R (author). “Computational Methods for the Long-Term Propagation of Space Debris Orbits.” 2013. Masters Thesis, Delft University of Technology. Accessed March 08, 2021. http://resolver.tudelft.nl/uuid:eee70164-4c99-470d-b8ee-5314ffcf63f8.

MLA Handbook (7^th Edition):

Hofsteenge, R (author). “Computational Methods for the Long-Term Propagation of Space Debris Orbits.” 2013. Web. 08 Mar 2021.

Vancouver:

Hofsteenge R(. Computational Methods for the Long-Term Propagation of Space Debris Orbits. [Internet] [Masters thesis]. Delft University of Technology; 2013. [cited 2021 Mar 08]. Available from: http://resolver.tudelft.nl/uuid:eee70164-4c99-470d-b8ee-5314ffcf63f8.

Council of Science Editors:

Hofsteenge R(. Computational Methods for the Long-Term Propagation of Space Debris Orbits. [Masters Thesis]. Delft University of Technology; 2013. Available from: http://resolver.tudelft.nl/uuid:eee70164-4c99-470d-b8ee-5314ffcf63f8

Cal Poly

19. Biehl, James Patrick. FORMULATION OF A SEARCH STRATEGY FOR SPACE DEBRIS AT GEO.

Degree: MS, Aerospace Engineering, 2010, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/355 ; 10.15368/theses.2010.124

► The main purpose of this thesis is to develop a search strategy for space debris that are in the geosynchronous orbit (GEO) region. The… (more)

Subjects/Keywords: Space Debris; Search Strategies; Orbits; Orbital Dynamics

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APA (6^th Edition):

Biehl, J. P. (2010). FORMULATION OF A SEARCH STRATEGY FOR SPACE DEBRIS AT GEO. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/355 ; 10.15368/theses.2010.124

Chicago Manual of Style (16^th Edition):

Biehl, James Patrick. “FORMULATION OF A SEARCH STRATEGY FOR SPACE DEBRIS AT GEO.” 2010. Masters Thesis, Cal Poly. Accessed March 08, 2021. https://digitalcommons.calpoly.edu/theses/355 ; 10.15368/theses.2010.124.

MLA Handbook (7^th Edition):

Biehl, James Patrick. “FORMULATION OF A SEARCH STRATEGY FOR SPACE DEBRIS AT GEO.” 2010. Web. 08 Mar 2021.

Vancouver:

Biehl JP. FORMULATION OF A SEARCH STRATEGY FOR SPACE DEBRIS AT GEO. [Internet] [Masters thesis]. Cal Poly; 2010. [cited 2021 Mar 08]. Available from: https://digitalcommons.calpoly.edu/theses/355 ; 10.15368/theses.2010.124.

Council of Science Editors:

Biehl JP. FORMULATION OF A SEARCH STRATEGY FOR SPACE DEBRIS AT GEO. [Masters Thesis]. Cal Poly; 2010. Available from: https://digitalcommons.calpoly.edu/theses/355 ; 10.15368/theses.2010.124

Aristotle University Of Thessaloniki (AUTH); Αριστοτέλειο Πανεπιστήμιο Θεσσαλονίκης (ΑΠΘ)

20. Skoulidou, Despoina. Dynamical evolution of artificial satellites and space debris in near earth region.

Degree: 2019, Aristotle University Of Thessaloniki (AUTH); Αριστοτέλειο Πανεπιστήμιο Θεσσαλονίκης (ΑΠΘ)

URL: http://hdl.handle.net/10442/hedi/46490

►

In this study, we perform a complete, dynamical cartography of the dynamics of satellites and space debris in the near Earth space, by using detailed… (more)

▼

In this study, we perform a complete, dynamical cartography of the dynamics of satellites and space debris in the near Earth space, by using detailed numerical simulations. The aim of this study is the investigation of natural reentry highways in the Earth's atmosphere that could be used for passive space debris mitigation, and the deeper understanding of the dynamics of the region. For the detailed cartography of the circumterrestrial phase space the numerical propagation and analysis of millions of fictitious orbits is necessary, using a suitable dynamical model that considers the main physics that affect satellites (Earth oblateness, lunisolar perturbations, solar radiation pressure, and atmospheric drag). We present the most complete to date dynamical atlas of the entire usable circumterrestrial space in orbital elements (a, e, i), characterizing the long-term dynamical behavior of Earth satellites from LEO to GEO and beyond. We find that the circumterrestrial space is smooth for low and high inclinations, but the most interesting and complex dynamical behavior appears for moderate-to-high inclinations, due to the overlapping of the lunisolar resonances. When augmented area-to-mass ratio values are assumed, useful dynamical hatches appear close to the upper limit of LEO protected region, which could be considered in designing disposal strategies. A more detailed study in the GTO regime shows that there is strong dependence on initial perigee altitude, as also on the area-to-mass value and drag, especially in low inclinations. The more detailed study around the MEO/GNSS regime, shows that the number of reentry solutions seems to maximize around three particular inclination zones (around i=46, 56, and 68deg), and the mean dynamical lifetime (i.e., the time span needed to reach at Earth's surface) of reentry orbits minimizes. Additionally, a dedicated study for the graveyard regions around the four GNSS constellations reveals that around 13-20% of the initial population is stable for at least 200yr. Finally, we used the dynamical atlas to find optimal reentry and graveyard solutions that could be reached with suitable engine-driven maneuvers, starting from a typical GNSS orbit. According to our study, reentry solutions that can be approached with velocity change (ΔV) lower than 300m/s have lifetimes longer that 70yr, while graveyard solutions can be easily targeted with ΔV of 5-40m/s.

Σε αυτή την διδακτορική διατριβή, γίνεται πλήρης χαρτογράφηση της δυναμικής εξέλιξης δορυφόρων στο εγγύς διαστημικό περιβάλλον για χρονική κλίμακα εκατοντάδων ετών, με τη χρήση λεπτομερών αριθμητικών προσομοιώσεων. Σκοπός της εργασίας είναι ο εντοπισμός φυσικών διόδων (τροχιών) επανόδου δορυφόρων στην ατμόσφαιρα της Γης, που θα μπορούσαμε να εκμεταλλευτούμε ώστε να μετριαστεί το πρόβλημα των διαστημικών καταλοίπων, και βέβαια η κατανόηση των δυναμικών μηχανισμών που οδηγούν στην ύπαρξή τους. Η λεπτομερής χαρτογράφηση ολόκληρης της τροχιακής περιοχής γύρω από τη Γη απαιτεί την αριθμητική ολοκλήρωση και ανάλυση δεκάδων εκατομμυρίων…

Subjects/Keywords: Τροχιακή μηχανική; Τεχνητοί δορυφόροι; Διαστημικά κατάλοιπα; Εγγύς διαστημικό περιβάλλον; Orbital mechanics; Artificial satellites; Space debris; Near earth space environment

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APA (6^th Edition):

Skoulidou, D. (2019). Dynamical evolution of artificial satellites and space debris in near earth region. (Thesis). Aristotle University Of Thessaloniki (AUTH); Αριστοτέλειο Πανεπιστήμιο Θεσσαλονίκης (ΑΠΘ). Retrieved from http://hdl.handle.net/10442/hedi/46490

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

Chicago Manual of Style (16^th Edition):

Skoulidou, Despoina. “Dynamical evolution of artificial satellites and space debris in near earth region.” 2019. Thesis, Aristotle University Of Thessaloniki (AUTH); Αριστοτέλειο Πανεπιστήμιο Θεσσαλονίκης (ΑΠΘ). Accessed March 08, 2021. http://hdl.handle.net/10442/hedi/46490.

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

MLA Handbook (7^th Edition):

Skoulidou, Despoina. “Dynamical evolution of artificial satellites and space debris in near earth region.” 2019. Web. 08 Mar 2021.

Vancouver:

Skoulidou D. Dynamical evolution of artificial satellites and space debris in near earth region. [Internet] [Thesis]. Aristotle University Of Thessaloniki (AUTH); Αριστοτέλειο Πανεπιστήμιο Θεσσαλονίκης (ΑΠΘ); 2019. [cited 2021 Mar 08]. Available from: http://hdl.handle.net/10442/hedi/46490.

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

Council of Science Editors:

Skoulidou D. Dynamical evolution of artificial satellites and space debris in near earth region. [Thesis]. Aristotle University Of Thessaloniki (AUTH); Αριστοτέλειο Πανεπιστήμιο Θεσσαλονίκης (ΑΠΘ); 2019. Available from: http://hdl.handle.net/10442/hedi/46490

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

21. Diaz, Christina R. A STUDY OF THE COLLISIONAL EVOLUTION OF ORBITAL DEBRIS IN GEOPOTENTIAL WELLS AND GEO DISPOSAL ORBITS.

Degree: MS, Aerospace Engineering, 2013, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/1063 ; 10.15368/theses.2013.157

► This thesis will present the effects of the orbital debris evolution in two key areas: the geosynchronous disposal orbit regime known as “graveyard” and… (more)

Subjects/Keywords: orbital debris; debris; collisions; ODPO; orbital mechanics; fortran; Astrodynamics; Other Aerospace Engineering

…debris is a present and future hazard to all Earth space operations. Orbital debris consists of… …collisions also contribute to the present population. Orbital debris’ time in orbit is dependent on… …the orbital altitude. Debris in lower orbits often reenter within several years to decades… …GEO Region Understanding debris evolution requires a thorough understanding of the orbital… …to orbital debris, geopotential wells are of interest due to their interesting behavior and…

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APA (6^th Edition):

Diaz, C. R. (2013). A STUDY OF THE COLLISIONAL EVOLUTION OF ORBITAL DEBRIS IN GEOPOTENTIAL WELLS AND GEO DISPOSAL ORBITS. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1063 ; 10.15368/theses.2013.157

Chicago Manual of Style (16^th Edition):

Diaz, Christina R. “A STUDY OF THE COLLISIONAL EVOLUTION OF ORBITAL DEBRIS IN GEOPOTENTIAL WELLS AND GEO DISPOSAL ORBITS.” 2013. Masters Thesis, Cal Poly. Accessed March 08, 2021. https://digitalcommons.calpoly.edu/theses/1063 ; 10.15368/theses.2013.157.

MLA Handbook (7^th Edition):

Diaz, Christina R. “A STUDY OF THE COLLISIONAL EVOLUTION OF ORBITAL DEBRIS IN GEOPOTENTIAL WELLS AND GEO DISPOSAL ORBITS.” 2013. Web. 08 Mar 2021.

Vancouver:

Diaz CR. A STUDY OF THE COLLISIONAL EVOLUTION OF ORBITAL DEBRIS IN GEOPOTENTIAL WELLS AND GEO DISPOSAL ORBITS. [Internet] [Masters thesis]. Cal Poly; 2013. [cited 2021 Mar 08]. Available from: https://digitalcommons.calpoly.edu/theses/1063 ; 10.15368/theses.2013.157.

Council of Science Editors:

Diaz CR. A STUDY OF THE COLLISIONAL EVOLUTION OF ORBITAL DEBRIS IN GEOPOTENTIAL WELLS AND GEO DISPOSAL ORBITS. [Masters Thesis]. Cal Poly; 2013. Available from: https://digitalcommons.calpoly.edu/theses/1063 ; 10.15368/theses.2013.157

University of Florida

22. Cojuangco, Ai-Ai Lumnay C. Orbital Lifetime Analyses of Pico- and Nano-Satellites.

Degree: MS, Mechanical Engineering - Mechanical and Aerospace Engineering, 2007, University of Florida

URL: https://ufdc.ufl.edu/UFE0020154

► In recent years, orbital debris has been a growing concern for the space industry due to its potential risk of causing collisions. Several agencies and… (more)

▼ In recent years, orbital debris has been a growing concern for the space industry due to its potential risk of causing collisions. Several agencies and organizations, such as the National Aeronautics and Space Administration (NASA), and the United Nations Committee on the Peaceful Uses of Outer Space (UNCOPUOS), have been involved in studying orbital debris and developing mitigation guidelines. In 2004, the Federal Communications Commission (FCC) began requiring a debris mitigation plan for all non-government United States radio communication satellites to be launched into orbit. Orbital lifetime analysis of a satellite is important in its development and in complying with debris mitigation guidelines. Factors that must be taken into consideration include environmental perturbations, such as solar radiation pressure, the Earth?s oblateness, and atmospheric drag. Other factors that affect orbital lifetime prediction are the satellite's physical properties. In this research, these perturbations and their effects on orbital lifetime, for Earth-orbiting satellites, were investigated. In this study, orbital lifetimes were determined using the Lifetime analysis tool in Analytical Graphics? Satellite Tool Kit (STK) software, focusing on pico- and nano-satellites. The focus on these two classes of satellites is due to their perceived rapid growth and the potential difficulty of adhering to FCC requirements for debris mitigation. The effect of solar cycle and different atmospheric density models were also explored during the analyses. The results indicate that orbital lifetimes of pico-satellites can be significantly reduced by increasing their drag area. For instance, changing the drag area of a 1-kg satellite from 0.01 to 0.1 meters squared decreased its orbital lifetime from 22 to 3 years, an 86% reduction. At 600 km above the Earth?s surface, pico-satellites with drag areas of 0.1 meters squared had minimum orbital lifetimes during years of highest solar activity. Our analysis implies that passive de-orbiting devices such as drag chutes can be effective devices on pico-satellites for addressing orbital debris mitigation. Meanwhile, the nano-satellites used in our study were between 11 to 28 kg, with drag areas from 0.08 and 0.2 meters squared, which led to orbital lifetimes in centuries when launched at 750 km altitude. Values indicate that additions to the nano-satellites are needed to fulfill a 25 year orbital lifetime requirement set by the FCC. ( en ) Advisors/Committee Members: Fitz-Coy, Norman G. (committee chair), Crane, Carl D. (committee member), Schueller, John K. (committee member).

Subjects/Keywords: Altitude; Artificial satellites; Atmospheric density; Drag coefficient; Orbital elements; Orbital lifetime; Orbitals; Orbits; Simulations; Space debris; lifetime, nano, orbital, pico, satellite

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APA (6^th Edition):

Cojuangco, A. L. C. (2007). Orbital Lifetime Analyses of Pico- and Nano-Satellites. (Masters Thesis). University of Florida. Retrieved from https://ufdc.ufl.edu/UFE0020154

Chicago Manual of Style (16^th Edition):

Cojuangco, Ai-Ai Lumnay C. “Orbital Lifetime Analyses of Pico- and Nano-Satellites.” 2007. Masters Thesis, University of Florida. Accessed March 08, 2021. https://ufdc.ufl.edu/UFE0020154.

MLA Handbook (7^th Edition):

Cojuangco, Ai-Ai Lumnay C. “Orbital Lifetime Analyses of Pico- and Nano-Satellites.” 2007. Web. 08 Mar 2021.

Vancouver:

Cojuangco ALC. Orbital Lifetime Analyses of Pico- and Nano-Satellites. [Internet] [Masters thesis]. University of Florida; 2007. [cited 2021 Mar 08]. Available from: https://ufdc.ufl.edu/UFE0020154.

Council of Science Editors:

Cojuangco ALC. Orbital Lifetime Analyses of Pico- and Nano-Satellites. [Masters Thesis]. University of Florida; 2007. Available from: https://ufdc.ufl.edu/UFE0020154

23. Deloo, J.A.F. (author). Analysis of the Rendezvous Phase of e.deorbit: Guidance, Communication and Illumination.

Degree: 2015, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:7f445d54-c758-45a8-b87e-a9c0eec61617

►

The aim of this thesis is to investigate a debris-remediation technique where a chaser performs a rendezvous with the debris, establishes a rigid-link connection, and… (more)

▼

The aim of this thesis is to investigate a debris-remediation technique where a chaser performs a rendezvous with the debris, establishes a rigid-link connection, and actively de-orbits the debris. Remediation of the space environment becomes an increasing urgency, since the continuously growing space debris population in low-Earth orbit currently poses a serious threat for active satellites. Furthermore, on Earth a threat exists due to uncontrolled re-entry of the debris sooner or later. The thesis addresses various aspects of the rendezvous phase for the debris-remediation technique under consideration. Among others, the aim is to assess passive safety of the required manoeuvres in the rendezvous phase. Also, the thesis explores the possibility of continuous ground communication of the chaser during its final approach with the target. Finally, the thesis studies the illumination conditions. This includes sensor blinding, target face illumination and chaser solar array illumination. ESA's satellite ENVISAT was used as design case. The safety aspects of the rendezvous manoeuvres were assessed by analysing the resulting trajectories after various thruster failures. For the analysis related to communication, the chain of core ESTRACK ground stations (located mainly in Europe) was considered. Furthermore, obstruction of the communication signal by the target was studied. Last, for the illumination conditions, obscuration of the Sun by target was taken into account. In the topic of passive safety, the results indicate that fly-around manoeuvres are preferred in the direction opposite to the natural orbital motion, as these are passively safe. On the other hand, manoeuvres on H-bar and fly-around manoeuvres along the natural orbital motion are found to be passively unsafe. It can be concluded from the communication analysis that the maximum duration of the uninterrupted window amounts up to more than half an hour, using the chain of core ESTRACK ground stations. However, the study on communication blockage shows that frequent communication gaps can occur, with the longest gaps being in the order of one minute in duration. In the field of illumination, it can be concluded that correct target illumination and sensor visibility cannot be guaranteed. Furthermore, the results show that the average solar array area available during final approach varies between 35% and 75%, due to both incorrect pointing by the chaser and obscuration by the target.

Astrodynamics and Space Missions

Space Engineering

Aerospace Engineering

Advisors/Committee Members: Mooij, E. (mentor).

Subjects/Keywords: e.deorbit; ENVISAT; Clean Space; Orbital Debris; Uncooperative Rendezvous; Debris Remediation; Safety; Communication; Illumination; Active Debris Removal

…135 Bibliography 139 Appendices 141 A Disturbance Torques and Relative Orbital… …143 A-2 Relative Orbital Perturbations… …in Noordwijk, The Netherlands), where I worked on an active debris-removal mission… …The topic of active debris removal is one that I have found intriguing since the start of my… …students, a heavy space debris removal system. Next, I continued working on the subject during my…

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APA (6^th Edition):

Deloo, J. A. F. (. (2015). Analysis of the Rendezvous Phase of e.deorbit: Guidance, Communication and Illumination. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:7f445d54-c758-45a8-b87e-a9c0eec61617

Chicago Manual of Style (16^th Edition):

Deloo, J A F (author). “Analysis of the Rendezvous Phase of e.deorbit: Guidance, Communication and Illumination.” 2015. Masters Thesis, Delft University of Technology. Accessed March 08, 2021. http://resolver.tudelft.nl/uuid:7f445d54-c758-45a8-b87e-a9c0eec61617.

MLA Handbook (7^th Edition):

Deloo, J A F (author). “Analysis of the Rendezvous Phase of e.deorbit: Guidance, Communication and Illumination.” 2015. Web. 08 Mar 2021.

Vancouver:

Deloo JAF(. Analysis of the Rendezvous Phase of e.deorbit: Guidance, Communication and Illumination. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Mar 08]. Available from: http://resolver.tudelft.nl/uuid:7f445d54-c758-45a8-b87e-a9c0eec61617.

Council of Science Editors:

Deloo JAF(. Analysis of the Rendezvous Phase of e.deorbit: Guidance, Communication and Illumination. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:7f445d54-c758-45a8-b87e-a9c0eec61617

24. Rosenkvist, Kajsa Eriksson. Laser Orbital Derbis Removal : Studies of Spacecraft Debris Removal Using Ground Based Lasers.

Degree: Space Technology, 2019, Luleå University of Technology

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-77103

► Overcrowding of the Low Earth Orbit (LEO) region is a growing problem. Decades of treating this part of space like a scrap yard has… (more)

Subjects/Keywords: Laser; Orbital; Debris; Removal; Aerospace Engineering; Rymd- och flygteknik

…an informed decision on how the orbital debris problem can be handled. 2 Chapter 2… …system and orbital debris, the media can not be changed. Instead it is vital to choose a… …turbulence divergence angle [m] Debris ~ag Cm d ηc F~g J~ md ν o p~ ρ ~v v [J… …efficiency factor gravitational force impulse debris mass true anomaly angular displacement from… …detonated after disconnection, leaving a much lager amount of debris. A number of satellites have…

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APA (6^th Edition):

Rosenkvist, K. E. (2019). Laser Orbital Derbis Removal : Studies of Spacecraft Debris Removal Using Ground Based Lasers. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-77103

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

Chicago Manual of Style (16^th Edition):

Rosenkvist, Kajsa Eriksson. “Laser Orbital Derbis Removal : Studies of Spacecraft Debris Removal Using Ground Based Lasers.” 2019. Thesis, Luleå University of Technology. Accessed March 08, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-77103.

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

MLA Handbook (7^th Edition):

Rosenkvist, Kajsa Eriksson. “Laser Orbital Derbis Removal : Studies of Spacecraft Debris Removal Using Ground Based Lasers.” 2019. Web. 08 Mar 2021.

Vancouver:

Rosenkvist KE. Laser Orbital Derbis Removal : Studies of Spacecraft Debris Removal Using Ground Based Lasers. [Internet] [Thesis]. Luleå University of Technology; 2019. [cited 2021 Mar 08]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-77103.

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

Council of Science Editors:

Rosenkvist KE. Laser Orbital Derbis Removal : Studies of Spacecraft Debris Removal Using Ground Based Lasers. [Thesis]. Luleå University of Technology; 2019. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-77103

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

University of Florida

25. Werremeyer, Mark R. Design of Subsystems for a Representative Modern LEO Satellite.

Degree: MS, Aerospace Engineering - Mechanical and Aerospace Engineering, 2013, University of Florida

URL: https://ufdc.ufl.edu/UFE0045534

► This thesis discusses the design of subsystems for a representative modern low Earth Orbit (LEO) satellite. Specifically, the subsystems presented were designed for inclusion on… (more)

Subjects/Keywords: Aluminum; Artificial satellites; Composite materials; Low earth orbits; Magnetism; Nadir; Plumbing; Propulsion; Satellite design; Thrusters; attitude – debris – debrisat – hypervelocity – impact – leo – modern – orbital – propulsion – representative – satellite – structure – subsystems – test – thermal

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APA (6^th Edition):

Werremeyer, M. R. (2013). Design of Subsystems for a Representative Modern LEO Satellite. (Masters Thesis). University of Florida. Retrieved from https://ufdc.ufl.edu/UFE0045534

Chicago Manual of Style (16^th Edition):

Werremeyer, Mark R. “Design of Subsystems for a Representative Modern LEO Satellite.” 2013. Masters Thesis, University of Florida. Accessed March 08, 2021. https://ufdc.ufl.edu/UFE0045534.

MLA Handbook (7^th Edition):

Werremeyer, Mark R. “Design of Subsystems for a Representative Modern LEO Satellite.” 2013. Web. 08 Mar 2021.

Vancouver:

Werremeyer MR. Design of Subsystems for a Representative Modern LEO Satellite. [Internet] [Masters thesis]. University of Florida; 2013. [cited 2021 Mar 08]. Available from: https://ufdc.ufl.edu/UFE0045534.

Council of Science Editors:

Werremeyer MR. Design of Subsystems for a Representative Modern LEO Satellite. [Masters Thesis]. University of Florida; 2013. Available from: https://ufdc.ufl.edu/UFE0045534

26. Maury, Thibaut. Consideration of space debris in the life cycle assessment framework : Considération des débris spatiaux dans le cadre de l’analyse de cycle de vie.

Degree: Docteur es, Génie des Procédés, 2019, Bordeaux

URL: http://www.theses.fr/2019BORD0051

► L’analyse de cycle de vie environnementale (ACV), d’après l’ISO 14040/44, a été identifiée par l’agence spatiale Européenne, ArianeGroup et plusieurs acteurs de l’industrie spatiale européenne… (more)

▼ L’analyse de cycle de vie environnementale (ACV), d’après l’ISO 14040/44, a été identifiée par l’agence spatiale Européenne, ArianeGroup et plusieurs acteurs de l’industrie spatiale européenne comme la méthodologie la mieux adaptée pour réaliser l’évaluation environnementale des missions spatiales. Cependant, le secteur spatial est un domaine d’activité dont la particularité est de s’étendre au-delà des limites de l’environnement terrestre. Ainsi, s’il est possible d’évaluer les impacts sur l’environnement classique via la méthodologie ACV, les impacts générés sur l’environnement orbital ne sont aujourd’hui pas considérés dans son cadre de référence.Par conséquent, il s’agit ici d’étendre le champ des études ACV dans le domaine du spatial afin de caractériser les étapes du cycle de vie ayant lieu en orbite, c’est-à-dire la phase d’usage pendant la mission spatiale et la phase de fin de vie (ou Post-Mission Disposal). L’anticipation de cette dernière est devenue une étape cruciale dans la conception des missions spatiales du fait des règlementations visant à limiter la prolifération des débris spatiaux. En effet, seulement 6% de la population en orbite autour de la Terre sont des satellites actifs, le reste étant considéré comme des débris, résultat des missions et activités spatiales passées. Etant donné cet enjeu de durabilité majeur pour l'industrie spatiale, les études environnementales se doivent de mettre en évidence les transferts de pollution potentiels non seulement entre les impacts environnementaux classiques tels que Changement Climatique ou la Toxicité mais aussi ceux relatifs à l’environnement orbital, au premier rang desquels figurent les débris spatiaux.Afin de caractériser cet impact sur l’environnement orbital, nous proposons de définir une nouvelle catégorie d’impact en ACV dénommée ‘Orbital Space Use’. La conformité avec le cadre de référence de l’ACV est assurée au travers de la construction de chaines de cause-à-effet (ou impact pathways) reliant les flux élémentaires du système d’étude aux mécanismes environnementaux (indicateur midpoint) et au dommage final (indicateur endpoint) au sein de l’Aire de Protection ‘Ressources Naturelles’. En effet, les orbites proches de la Terre qui supportent les activités spatiales sont considérées à ce titre comme une ressource pouvant être impactée par des ‘stresseurs’. Les débris spatiaux sont aujourd’hui identifiés comme les principaux ‘stresseurs’ vis-à-vis de l’accès et de la pleine utilisation de la ressource orbitale. Ainsi, le développement d’un modèle de caractérisation a été entrepris. Il permet d’évaluer l’impact potentiel d’une mission spatiale sur la population des débris déjà présente en orbite. Les facteurs de caractérisation obtenus sont appliqués à un cas d’étude comparant trois scénarios de fin de vie différents dans le but de prouver l’applicabilité du modèle. En outre, une première approche s’intéressant à la quantification des externalités économiques négatives engendrées par la prolifération des débris est développée. Elle constitue une… Advisors/Committee Members: Sonnemann, Guido W. (thesis director).

Subjects/Keywords: Analyse du Cycle de Vie; Fin de vie; Débris spatiaux; Impact environnemental; Life Cycle Assessment; Environmental impact; Space debris; Orbital space use; Post-Mission Disposal

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APA (6^th Edition):

Maury, T. (2019). Consideration of space debris in the life cycle assessment framework : Considération des débris spatiaux dans le cadre de l’analyse de cycle de vie. (Doctoral Dissertation). Bordeaux. Retrieved from http://www.theses.fr/2019BORD0051

Chicago Manual of Style (16^th Edition):

Maury, Thibaut. “Consideration of space debris in the life cycle assessment framework : Considération des débris spatiaux dans le cadre de l’analyse de cycle de vie.” 2019. Doctoral Dissertation, Bordeaux. Accessed March 08, 2021. http://www.theses.fr/2019BORD0051.

MLA Handbook (7^th Edition):

Maury, Thibaut. “Consideration of space debris in the life cycle assessment framework : Considération des débris spatiaux dans le cadre de l’analyse de cycle de vie.” 2019. Web. 08 Mar 2021.

Vancouver:

Maury T. Consideration of space debris in the life cycle assessment framework : Considération des débris spatiaux dans le cadre de l’analyse de cycle de vie. [Internet] [Doctoral dissertation]. Bordeaux; 2019. [cited 2021 Mar 08]. Available from: http://www.theses.fr/2019BORD0051.

Council of Science Editors:

Maury T. Consideration of space debris in the life cycle assessment framework : Considération des débris spatiaux dans le cadre de l’analyse de cycle de vie. [Doctoral Dissertation]. Bordeaux; 2019. Available from: http://www.theses.fr/2019BORD0051

27. Van Cor, Jared D. Characterizing Resident Space Object Earthshine Signature Variability.

Degree: MS, Chester F. Carlson Center for Imaging Science (COS), 2017, Rochester Institute of Technology

URL: https://scholarworks.rit.edu/theses/9485

► There are three major sources of illumination on objects in the near Earth space environment: Sunshine, Moonshine, and Earthshine. For objects in this environment… (more)

▼ There are three major sources of illumination on objects in the near Earth space environment: Sunshine, Moonshine, and Earthshine. For objects in this environment (satellites, orbital debris, etc.) known as Resident Space Objects (RSOs), the sun and the moon have consistently small illuminating solid angles and can be treated as point sources; this makes their incident illumination easily modeled. The Earth on the other hand has a large illuminating solid angle, is heterogeneous, and is in a constant state of change. The objective of this thesis was to characterize the impact and variability of observed RSO Earthshine on apparent magnitude signatures in the visible optical spectral region. A key component of this research was creating Earth object models incorporating the reflectance properties of the Earth. Two Earth objects were created: a homogeneous diffuse Earth object and a time sensitive heterogeneous Earth object. The homogeneous diffuse Earth object has a reflectance equal to the average global albedo, a standard model used when modeling Earthshine. The time sensitive heterogeneous Earth object was created with two material maps representative of the dynamic reflectance of the surface of the earth, and a shell representative of the atmosphere. NASA’s Moderate-resolution Imaging Spectroradiometer (MODIS) Earth observing satellite product libraries, MCD43C1 global surface BRDF map and MOD06 global fractional cloud map, were utilized to create the material maps, and a hybridized version of the Empirical Line Method (ELM) was used to create the atmosphere. This dynamic Earth object was validated by comparing simulated color imagery of the Earth to that taken by: NASAs Earth Polychromatic Imaging Camera (EPIC) located on the Deep Space Climate Observatory (DSCOVR), and by MODIS located on the Terra satellite. The time sensitive heterogeneous Earth object deviated from MODIS imagery by a spectral radiance root mean square error (RMSE) of ±14.86 [watts/m^2srμm] over a sample of ROIs. Further analysis using EPIC imagery found a total albedo difference of +0.03% and a cross correlation of 0.656. Also compared to EPIC imagery it was found our heterogeneous Earth model produced a reflected Earthshine radiance RMSE of ±28 [watts/m^2srμm] incident on diffuse spherical RSOs, specular spherical RSOs, and diffuse flat plate RSOs with an altitude of 1000km; this resulted in an apparent magnitude error of ±0.28. Furthermore, it was found our heterogeneous Earthmodel produced a reflected Earthshine radiance RMSE of ±68 [watts/m^2srμm] for specular flat plate RSOs with an altitude of 1000km; this resulted in an apparent magnitude error of ±0.68. The Earth objects were used in a workflow with the Digital Imaging and Remote Sensing Image Generation (DIRSIG) tool to explore the impact of a range of characteristic RSO geometries, geographies, orientations, and materials on the signatures from an RSO due to Earthshine. An apparent magnitude was calculated and used to quantify RSO Earthshine signature… Advisors/Committee Members: Michael Gartley.

Subjects/Keywords: DIRSIG; Earthshine; Earthshine simulation; Orbital debris; Resident space object; Space debris

…Autonomous Telescope mdpt mid point MEO Mid Earth Orbit MODEST Michigan Orbital Debris Survey… …this threat, NASA’s Orbital Debris Program office has placed great emphasis on obtaining… …0.61m aperture Michigan Orbital Debris Survey Telescope (MODEST) in Chili to help… …of countries with space assets reaching 60 and growing, the amount of debris and potential… …Earth shadowing, and near Earth orbital speeds. This problem is compounded by bidirectional…

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APA (6^th Edition):

Van Cor, J. D. (2017). Characterizing Resident Space Object Earthshine Signature Variability. (Masters Thesis). Rochester Institute of Technology. Retrieved from https://scholarworks.rit.edu/theses/9485

Chicago Manual of Style (16^th Edition):

Van Cor, Jared D. “Characterizing Resident Space Object Earthshine Signature Variability.” 2017. Masters Thesis, Rochester Institute of Technology. Accessed March 08, 2021. https://scholarworks.rit.edu/theses/9485.

MLA Handbook (7^th Edition):

Van Cor, Jared D. “Characterizing Resident Space Object Earthshine Signature Variability.” 2017. Web. 08 Mar 2021.

Vancouver:

Van Cor JD. Characterizing Resident Space Object Earthshine Signature Variability. [Internet] [Masters thesis]. Rochester Institute of Technology; 2017. [cited 2021 Mar 08]. Available from: https://scholarworks.rit.edu/theses/9485.

Council of Science Editors:

Van Cor JD. Characterizing Resident Space Object Earthshine Signature Variability. [Masters Thesis]. Rochester Institute of Technology; 2017. Available from: https://scholarworks.rit.edu/theses/9485

28. Roberts, Lyle Edward. Internally Sensed Optical Phased Arrays .

Degree: 2016, Australian National University

URL: http://hdl.handle.net/1885/110523

► The performance of existing ground-based space debris laser ranging systems can be improved by directing more light onto space debris by coherently combining multiple lasers… (more)

▼ The performance of existing ground-based space debris laser ranging systems can be improved by directing more light onto space debris by coherently combining multiple lasers using an optical phased array (OPA). If the power delivered to target is sufficiently high then these systems may also provide the capability to remotely manoeuvre space debris via photon radiation pressure and/or ablation. By stabilising the relative output phase of multiple lasers, OPAs form a coherent optical wave-front in the far field. Since the phase of each laser can be controlled independently, they also have the ability to dynamically manipulate the distribution of optical power in the far field, potentially enabling them to compensate for atmospheric turbulence. This beam-forming functionality, combined with their inherent scalability and high power handling capabilities make OPAs a promising technology for future space debris laser ranging and manoeuvring systems. In this thesis, we describe the iterative development of a high-power compatible internally sensed OPA, which – in contrast to externally sensed OPAs that sense the output phase of each laser externally using free-space optics – relies on the small fraction of light that is reflected back into the fibre at the output of the OPA to stabilise its relative output phase. This allows internally sensed OPAs to be implemented entirely within fibre without any dependence on free-space optics at the output, offering potential advantages over externally sensed techniques when operating in the presence of shock and vibration. A proof-of-concept experiment demonstrated the viability of internal sensing, but also highlighted a number of weaknesses that would affect its utility, specifically in supporting high optical powers greater than 100s of mW. An improved high-power compatible internally sensed OPA was designed to overcome these restrictions by isolating sensitive optical components from high optical powers using asymmetric fibre couplers. This concept was initially demonstrated experimentally using slave lasers offset phase-locked to a single master laser, and then again using fibre amplifiers in a master oscillator power amplifier configuration. The experimental demonstration of the fibre amplifier compatible OPA stabilised the relative output phase of three commercial 15 W fibre amplifiers, demonstrating a root-mean-squared output phase stability of λ/194, and the ability to steer the beam at up to 10 kHz. The internally sensed OPA presented here requires the simultaneous measurement, and control of the phase of each emitter in the OPA. This is accomplished using digitally enhanced heterodyne interferometry and digitally implemented phasemeters, both of which rely heavily on high-speed digital signal processing resources…

Subjects/Keywords: Optical Phased Arrays; Control Systems; Lasers; Optics; Stabilisation; Stabilization; Coherent Beam Combining; Space Debris; Orbital Debris; Interferometry; Digitally Enhanced Heterodyne Interferometry; Phasemeters; Digitally Implemented Phasemeters; Field Programmable Gate Array; FPGA; OPA; CBC; Internal sensing; Internally sensed

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APA (6^th Edition):

Roberts, L. E. (2016). Internally Sensed Optical Phased Arrays . (Thesis). Australian National University. Retrieved from http://hdl.handle.net/1885/110523

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

Chicago Manual of Style (16^th Edition):

Roberts, Lyle Edward. “Internally Sensed Optical Phased Arrays .” 2016. Thesis, Australian National University. Accessed March 08, 2021. http://hdl.handle.net/1885/110523.

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

MLA Handbook (7^th Edition):

Roberts, Lyle Edward. “Internally Sensed Optical Phased Arrays .” 2016. Web. 08 Mar 2021.

Vancouver:

Roberts LE. Internally Sensed Optical Phased Arrays . [Internet] [Thesis]. Australian National University; 2016. [cited 2021 Mar 08]. Available from: http://hdl.handle.net/1885/110523.

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

Council of Science Editors:

Roberts LE. Internally Sensed Optical Phased Arrays . [Thesis]. Australian National University; 2016. Available from: http://hdl.handle.net/1885/110523

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

University of Colorado

29. Trowbridge, Michael Aaron. Autonomous 3D Model Generation of Orbital Debris using Point Cloud Sensors.

Degree: MS, Aerospace Engineering Sciences, 2014, University of Colorado

URL: https://scholar.colorado.edu/asen_gradetds/86

► A software prototype for autonomous 3D scanning of uncooperatively rotating orbital debris using a point cloud sensor is designed and tested. The software successfully… (more)

Subjects/Keywords: 3D scanning; explicit loop closure heuristic; Graph SLAM; model generation; orbital debris; point clouds; Aerospace Engineering; Artificial Intelligence and Robotics; Computer-Aided Engineering and Design; Systems Engineering and Multidisciplinary Design Optimization

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

APA (6^th Edition):

Trowbridge, M. A. (2014). Autonomous 3D Model Generation of Orbital Debris using Point Cloud Sensors. (Masters Thesis). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/86

Chicago Manual of Style (16^th Edition):

Trowbridge, Michael Aaron. “Autonomous 3D Model Generation of Orbital Debris using Point Cloud Sensors.” 2014. Masters Thesis, University of Colorado. Accessed March 08, 2021. https://scholar.colorado.edu/asen_gradetds/86.

MLA Handbook (7^th Edition):

Trowbridge, Michael Aaron. “Autonomous 3D Model Generation of Orbital Debris using Point Cloud Sensors.” 2014. Web. 08 Mar 2021.

Vancouver:

Trowbridge MA. Autonomous 3D Model Generation of Orbital Debris using Point Cloud Sensors. [Internet] [Masters thesis]. University of Colorado; 2014. [cited 2021 Mar 08]. Available from: https://scholar.colorado.edu/asen_gradetds/86.

Council of Science Editors:

Trowbridge MA. Autonomous 3D Model Generation of Orbital Debris using Point Cloud Sensors. [Masters Thesis]. University of Colorado; 2014. Available from: https://scholar.colorado.edu/asen_gradetds/86

30. Mackay, Sean Leland. Age, origin and evolution of Antarctic debris-covered glaciers: implications for landscape evolution and long-term climate change.

Degree: PhD, Earth & Environment, 2016, Boston University

URL: http://hdl.handle.net/2144/14508

► Antarctic debris-covered glaciers are potential archives of long-term climate change. However, the geomorphic response of these systems to climate forcing is not well understood. To… (more)

▼ Antarctic debris-covered glaciers are potential archives of long-term climate change. However, the geomorphic response of these systems to climate forcing is not well understood. To address this concern, I conducted a series of field-based and numerical modeling studies in the McMurdo Dry Valleys of Antarctica (MDV), with a focus on Mullins and Friedman glaciers. I used data and results from geophysical surveys, ice-core collection and analysis, geomorphic mapping, micro-meteorological stations, and numerical-process models to (1) determine the precise origin and distribution of englacial and supraglacial debris within these buried-ice systems, (2) quantify the fundamental processes and feedbacks that govern interactions among englacial and supraglacial debris, (3) establish a process-based model to quantify the inventory of cosmogenic nuclides within englacial and supraglacial debris, and (4) isolate the governing relationships between the evolution of englacial /supraglacial debris and regional climate forcing. Results from 93 field excavations, 21 ice cores, and 24 km of ground-penetrating radar data show that Mullins and Friedman glaciers contain vast areas of clean glacier ice interspersed with inclined layers of concentrated debris. The similarity in the pattern of englacial debris bands across both glaciers, along with model results that call for negligible basal entrainment, is best explained by episodic environmental change at valley headwalls. To constrain better the timing of debris-band formation, I developed a modeling framework that tracks the accumulation of cosmogenic 3He in englacial and supraglacial debris. Results imply that ice within Mullins Glacier increases in age non-linearly from 12 ka to ~220 ka in areas of active flow (up to >> 1.6 Ma in areas of slow-moving-to-stagnant ice) and that englacial debris bands originate with a periodicity of ~41 ka. Modeling studies suggest that debris bands originate in synchronicity with changes in obliquity-paced, total integrated summer insolation. The implication is that the englacial structure and surface morphology of some cold-based, debris-covered glaciers can preserve high-resolution climate archives that exceed the typical resolution of Antarctic terrestrial deposits and moraine records.

Subjects/Keywords: Geomorphology; Antarctica; Climate change; Cosmogenic nuclide dating; Debris-covered glacier; Ground-penetrating radar; Orbital forcing

…1 Chapter 2: Cold-based debris-covered glaciers: evaluating their potential as climate… …paced late Pleistocene climate change recorded in the structure of Antarctic debris-covered… …35 Figure 2.6. Measured air, supraglacial debris, and ice temperatures at selected… …Figure 2.16. Morphometric properties of supraglacial debris on Mullins Glacier ...........67… …Figure 2.17. Sedimentological variation in supraglacial debris on Mullins Glacier .........71…

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

APA (6^th Edition):

Mackay, S. L. (2016). Age, origin and evolution of Antarctic debris-covered glaciers: implications for landscape evolution and long-term climate change. (Doctoral Dissertation). Boston University. Retrieved from http://hdl.handle.net/2144/14508

Chicago Manual of Style (16^th Edition):

Mackay, Sean Leland. “Age, origin and evolution of Antarctic debris-covered glaciers: implications for landscape evolution and long-term climate change.” 2016. Doctoral Dissertation, Boston University. Accessed March 08, 2021. http://hdl.handle.net/2144/14508.

MLA Handbook (7^th Edition):

Mackay, Sean Leland. “Age, origin and evolution of Antarctic debris-covered glaciers: implications for landscape evolution and long-term climate change.” 2016. Web. 08 Mar 2021.

Vancouver:

Mackay SL. Age, origin and evolution of Antarctic debris-covered glaciers: implications for landscape evolution and long-term climate change. [Internet] [Doctoral dissertation]. Boston University; 2016. [cited 2021 Mar 08]. Available from: http://hdl.handle.net/2144/14508.

Council of Science Editors:

Mackay SL. Age, origin and evolution of Antarctic debris-covered glaciers: implications for landscape evolution and long-term climate change. [Doctoral Dissertation]. Boston University; 2016. Available from: http://hdl.handle.net/2144/14508

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Open Access Theses and Dissertations