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University of Colorado
1.
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)
▼ 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 presentday
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 theGEOdebris 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.
Subjects/Keywords: active debris removal; geostationary orbit; geosynchronous orbit; orbital debris; Aerospace Engineering
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APA (6th 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 (16th Edition):
Anderson, Paul V. “Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime.” 2010. Doctoral Dissertation, University of Colorado. Accessed March 01, 2021.
https://scholar.colorado.edu/asen_gradetds/14.
MLA Handbook (7th Edition):
Anderson, Paul V. “Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime.” 2010. Web. 01 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 01].
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
2.
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 (6th 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 (16th Edition):
Anderson, Paul Vincent. “Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime.” 2015. Doctoral Dissertation, University of Colorado. Accessed March 01, 2021.
https://scholar.colorado.edu/asen_gradetds/91.
MLA Handbook (7th Edition):
Anderson, Paul Vincent. “Characterizing Longitude-Dependent Orbital Debris Congestion in the Geosynchronous Orbit Regime.” 2015. Web. 01 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 01].
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
3.
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
…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… …Active Debris Removal
Analytical Hierarchy Process
Airbus Defence and Space
Beginning of Life… …cope with the threat of space debris, Active Debris Removal (ADR) is required to… …students, a heavy space debris removal system. Next, I continued working on the subject
during my…
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APA (6th 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 (16th 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 01, 2021.
http://resolver.tudelft.nl/uuid:7f445d54-c758-45a8-b87e-a9c0eec61617.
MLA Handbook (7th Edition):
Deloo, J A F (author). “Analysis of the Rendezvous Phase of e.deorbit: Guidance, Communication and Illumination.” 2015. Web. 01 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 01].
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
York University
4.
Dong, Gangqi.
Autonomous Visual Servo Robotic Capture of Non-cooperative Target.
Degree: PhD, Earth & Space Science, 2017, York University
URL: http://hdl.handle.net/10315/33406
► This doctoral research develops and validates experimentally a vision-based control scheme for the autonomous capture of a non-cooperative target by robotic manipulators for active space…
(more)
▼ This doctoral research develops and validates experimentally a vision-based control scheme for the autonomous capture of a non-cooperative target by robotic manipulators for
active space
debris removal and on-orbit servicing. It is focused on the final capture stage by robotic manipulators after the orbital rendezvous and proximity maneuver being completed. Two challenges have been identified and investigated in this stage: the dynamic estimation of the non-cooperative target and the autonomous visual servo robotic control. First, an integrated algorithm of photogrammetry and extended Kalman filter is proposed for the dynamic estimation of the non-cooperative target because it is unknown in advance. To improve the stability and precision of the algorithm, the extended Kalman filter is enhanced by dynamically correcting the distribution of the process noise of the filter. Second, the concept of incremental kinematic control is proposed to avoid the multiple solutions in solving the inverse kinematics of robotic manipulators. The proposed target motion estimation and visual servo control algorithms are validated experimentally by a custom built visual servo manipulator-target system. Electronic hardware for the robotic manipulator and computer software for the visual servo are custom designed and developed. The experimental results demonstrate the effectiveness and advantages of the proposed vision-based robotic control for the autonomous capture of a non-cooperative target. Furthermore, a preliminary study is conducted for future extension of the robotic control with consideration of flexible joints.
Advisors/Committee Members: Zhu, George (advisor).
Subjects/Keywords: Engineering; Robotic manipulator; Visual servo; Non-cooperative target; Target estimation; Autonomous capture; Kinematics-based robotic control; Joint flexibility; On orbit servicing; Active debris removal
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APA (6th Edition):
Dong, G. (2017). Autonomous Visual Servo Robotic Capture of Non-cooperative Target. (Doctoral Dissertation). York University. Retrieved from http://hdl.handle.net/10315/33406
Chicago Manual of Style (16th Edition):
Dong, Gangqi. “Autonomous Visual Servo Robotic Capture of Non-cooperative Target.” 2017. Doctoral Dissertation, York University. Accessed March 01, 2021.
http://hdl.handle.net/10315/33406.
MLA Handbook (7th Edition):
Dong, Gangqi. “Autonomous Visual Servo Robotic Capture of Non-cooperative Target.” 2017. Web. 01 Mar 2021.
Vancouver:
Dong G. Autonomous Visual Servo Robotic Capture of Non-cooperative Target. [Internet] [Doctoral dissertation]. York University; 2017. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/10315/33406.
Council of Science Editors:
Dong G. Autonomous Visual Servo Robotic Capture of Non-cooperative Target. [Doctoral Dissertation]. York University; 2017. Available from: http://hdl.handle.net/10315/33406
University of Toronto
5.
Hakima, Houman.
A New Approach to Active Removal of Space Debris.
Degree: PhD, 2020, University of Toronto
URL: http://hdl.handle.net/1807/101359
► As a result of human space activities for over sixty years, there exist numerous man-made debris objects in the Earth orbits. Such objects not only…
(more)
▼ As a result of human space activities for over sixty years, there exist numerous man-made
debris objects in the Earth orbits. Such objects not only jeopardize current operations of important space assets, but can also seriously hinder future space missions through a potential chain reaction of colliding space
debris. This research addresses mitigation and remediation of the space
debris environment. The thesis entails research in four critical
subject areas: i) characterization of the
debris environment, ii) assessment of the
active debris removal methods proposed in the literature, iii) detailed engineering of a novel
removal concept using a CubeSat spacecraft, called Deorbiter CubeSat, for sizable
debris objects in low-Earth orbit, and iv) design of attitude and orbit controllers for the proposed spacecraft.
The research first develops a probabilistic method for the prioritization of
debris objects to be consid- ered in near-future
removal missions. Then, a comparative study and in-depth analysis is conducted on the
removal methods proposed in the literature to investigate their viability, through a number of multi- criteria assessment techniques. A Monte Carlo analysis is used in the study to quantify the intrinsic uncertainty associated with the space
debris population. Next, a new
debris removal mission utilizing Deorbiter CubeSats is conceptualized, and the design of CubeSat subsystems is detailed. A mothership spacecraft carries and deploys a number of Deorbiter CubeSats into designated orbits near their target
debris. Each CubeSat uses an eight-unit form factor, and consists of commercially-available components with substantial space heritage. The actual performance specifications of the components are used to examine the proposed space
debris removal approach. Finally, control schemes are synthesized for the critical maneuvers in the mission, using a unilateral low-thrust propulsion and a three-axis reaction wheel systems onboard the CubeSat, namely, i) concurrent rendezvous and attitude synchronization maneuver for approaching and attaching to the
debris, ii) detumbling maneuver for stabilizing the
debris attitude motion, and iii) deorbiting maneuver for transferring the
debris from its original orbit to a deorbit altitude along a time-optimal trajectory. Several numerical simulations verify and validate the proposed approach as well as the control schemes.
Advisors/Committee Members: Emami, M. Reza, Aerospace Science and Engineering.
Subjects/Keywords: Active Debris Removal; Attitude and Orbit Control; Attitude Dynamics; Deorbiter CubeSat; Orbital Dynamics; Space Debris; 0538
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APA (6th 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 (16th Edition):
Hakima, Houman. “A New Approach to Active Removal of Space Debris.” 2020. Doctoral Dissertation, University of Toronto. Accessed March 01, 2021.
http://hdl.handle.net/1807/101359.
MLA Handbook (7th Edition):
Hakima, Houman. “A New Approach to Active Removal of Space Debris.” 2020. Web. 01 Mar 2021.
Vancouver:
Hakima H. A New Approach to Active Removal of Space Debris. [Internet] [Doctoral dissertation]. University of Toronto; 2020. [cited 2021 Mar 01].
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
6.
Hardy, Brian Patrick.
Long-term effects of satellite megaconstellations on the debris environment in low earth orbit.
Degree: MS, Aerospace Engineering, 2020, University of Illinois – Urbana-Champaign
URL: http://hdl.handle.net/2142/108004
► This thesis examines the potential long-term impacts of satellite megaconstellations in Low Earth Orbit, with a focus on how post-mission disposal rates for megaconstellations will…
(more)
▼ This thesis examines the potential long-term impacts of satellite megaconstellations in Low Earth Orbit, with a focus on how post-mission disposal rates for megaconstellations will affect their contributions to orbital
debris over the next 150 years. A new, medium-fidelity simulation for modeling orbital
debris is developed and described, and several test cases are run with SpaceX’s Starlink megaconstellation and varying success rates for post-mission disposal. In cases where Starlink’s post-mission disposal rate is insufficient to prevent
debris growth, varying amounts of
active debris removal are explored as a potential mitigation measure. It is shown that LEO
debris levels will grow at almost double their baseline rate if Starlink meets only the minimum regulatory requirements for post-mission disposal, and even relatively high rates of
active debris removal cannot always return the LEO environment to its non-megaconstellation baseline. Still, the potential exists to minimize the
debris-generating effects of large megaconstellations like Starlink if post-mission disposal rates of 95% or better can be achieved.
Advisors/Committee Members: Ho, Koki (advisor).
Subjects/Keywords: space debris; megaconstellations; active debris removal
…failure rate over time.
1.4
Active Debris Removal
As megaconstellations insert potentially… …x5D;. One proposed solution is active debris removal, whereby specialpurpose spacecraft… …and legal difficulties, active
debris removal could prove vital to preserving the future LEO… …study
of orbital debris, megaconstellations, and active debris removal. Notable publications… …methods discussed previously.
16
2.5
Effects of Active Debris Removal
Lastly, a significant…
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APA ·
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APA (6th Edition):
Hardy, B. P. (2020). Long-term effects of satellite megaconstellations on the debris environment in low earth orbit. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/108004
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Hardy, Brian Patrick. “Long-term effects of satellite megaconstellations on the debris environment in low earth orbit.” 2020. Thesis, University of Illinois – Urbana-Champaign. Accessed March 01, 2021.
http://hdl.handle.net/2142/108004.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Hardy, Brian Patrick. “Long-term effects of satellite megaconstellations on the debris environment in low earth orbit.” 2020. Web. 01 Mar 2021.
Vancouver:
Hardy BP. Long-term effects of satellite megaconstellations on the debris environment in low earth orbit. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2020. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/2142/108004.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Hardy BP. Long-term effects of satellite megaconstellations on the debris environment in low earth orbit. [Thesis]. University of Illinois – Urbana-Champaign; 2020. Available from: http://hdl.handle.net/2142/108004
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Colorado
7.
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 ·
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APA (6th Edition):
Jasper, L. E. Z. (2014). Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/82
Chicago Manual of Style (16th Edition):
Jasper, Lee E Z. “Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects.” 2014. Doctoral Dissertation, University of Colorado. Accessed March 01, 2021.
https://scholar.colorado.edu/asen_gradetds/82.
MLA Handbook (7th Edition):
Jasper, Lee E Z. “Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects.” 2014. Web. 01 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 01].
Available from: https://scholar.colorado.edu/asen_gradetds/82.
Council of Science Editors:
Jasper LEZ. Open-Loop Thrust Profile Development for Tethered Towing of Large Space Objects. [Doctoral Dissertation]. University of Colorado; 2014. Available from: https://scholar.colorado.edu/asen_gradetds/82
Delft University of Technology
8.
Linskens, H.T.K. (author).
Tether Dynamics Analysis and Guidance & Control Design for Active Space Debris Removal.
Degree: 2015, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:ea17ecb8-a9c1-4ac0-a209-75526ad54f14
► Recent years have seen a steep increase in research being performed towards active space debris removal: space debris has proven to be a very real…
(more)
▼ Recent years have seen a steep increase in research being performed towards
active space
debris removal: space
debris has proven to be a very real threat to operational spacecraft, and studies indicate that the frequency of collisions will only increase if nothing is done to remove large pieces of
debris. In particular, ESA has done studies towards removing Envisat from orbit, after communications were lost and were unable to be reestablished. To this end, a scenario was proposed in which a robotic chaser satellite would use a tether to interface with Envisat, either using a net or a harpoon, and proceed to deorbit the resulting tethered system. This research tackles two main challenges relating to this scenario. First, a suitable model for the tether was developed by discretizing the tether into a number of point masses and massless Kelvin-Voigt elements. The influence of the number of nodes was investigated, showing that increasing the number of nodes used does not significantly increase the fidelity of the solution. Therefore, it was chosen to model the tether with two nodes and three elements. Additionally, multiple combinations of tether length, stiffness, and damping were investigated. Second, a preliminary design for a guidance and control system was developed. This system uses multiple fixed-duration burns as the main deorbit strategy. The guidance system controls the relative state of the chaser with respect to the target during and after these main engine burns: during burns, a hold point is established at the equilibrium length of the tether, and during coasting phases the tether is kept slightly in tension to reduce target and tether motion. At the transition between thrusting and coasting phases, the thrust is gradually throttled down to further decrease these motions. The control system is designed to keep the chaser level with the local horizon at all times. During the design process, the performance of guidance and control systems based on linear quadratic regulators was used as a baseline for the same systems based on sliding-mode control. Furthermore, three different thrust levels for the deorbit burn were examined. It was found that the system based on sliding-mode control offered considerable performance improvements over the LQR-based system: total propellant consumption was reduced by an average of 48%, while adhering to the same tolerances. Furthermore, it was determined that high thrust levels are desirable for both reducing propellant consumption as well as reducing target rotation. In terms of safety, collision can best be avoided by using lower thrust levels or longer tethers. While this seems to conflict with minimizing required propellant, minimal target rotation and minimal propellant consumption can still be achieved by using long tethers with high stiffness. Finally, it was found that while sensitive to small changes in the initial conditions, the precision of the terminal point is still high enough to allow the target to be deorbited in the South Pacific Ocean. This result was…
Advisors/Committee Members: Mooij, E. (mentor).
Subjects/Keywords: space debris; active debris removal; tether dynamics; guidance; control; sliding mode control; Envisat; lumped-mass model; Kelvin-Voigt material
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APA (6th Edition):
Linskens, H. T. K. (. (2015). Tether Dynamics Analysis and Guidance & Control Design for Active Space Debris Removal. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:ea17ecb8-a9c1-4ac0-a209-75526ad54f14
Chicago Manual of Style (16th Edition):
Linskens, H T K (author). “Tether Dynamics Analysis and Guidance & Control Design for Active Space Debris Removal.” 2015. Masters Thesis, Delft University of Technology. Accessed March 01, 2021.
http://resolver.tudelft.nl/uuid:ea17ecb8-a9c1-4ac0-a209-75526ad54f14.
MLA Handbook (7th Edition):
Linskens, H T K (author). “Tether Dynamics Analysis and Guidance & Control Design for Active Space Debris Removal.” 2015. Web. 01 Mar 2021.
Vancouver:
Linskens HTK(. Tether Dynamics Analysis and Guidance & Control Design for Active Space Debris Removal. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Mar 01].
Available from: http://resolver.tudelft.nl/uuid:ea17ecb8-a9c1-4ac0-a209-75526ad54f14.
Council of Science Editors:
Linskens HTK(. Tether Dynamics Analysis and Guidance & Control Design for Active Space Debris Removal. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:ea17ecb8-a9c1-4ac0-a209-75526ad54f14
9.
Missel, Jonathan William.
Active Space Debris Removal using Capture and Ejection.
Degree: PhD, Aerospace Engineering, 2013, Texas A&M University
URL: http://hdl.handle.net/1969.1/149391
► Low Earth Orbit is over-cluttered with rogue objects that threaten existing technological assets and interfere with allocating new ones. Traditional satellite missions are not efficient…
(more)
▼ Low Earth Orbit is over-cluttered with rogue objects that threaten existing technological assets and interfere with allocating new ones. Traditional satellite missions are not efficient enough to collect an appreciable amount of
debris due to the high cost of orbit transfers. Many alternate proposals are politically controversial, costly, or dependent on undeveloped technology. This dissertation attempts to solve the problem by introducing a new mission architecture, Space Sweeper, and bespoke hardware, Sling-Sat, that sequentially captures and ejects
debris plastically. Resulting momentum exchanges are exploited to aid in subsequent orbit transfers, thus saving fuel. Sling-Sat is a spinning satellite that captures
debris at the ends of adjustable-length arms. Arm length controls the angular rate to achieve a desired tangential ejection speed. Timing the release exacts the ejection angle. This process redirects
debris to burn up in the atmosphere, or reduce its lifetime, by lowering its perigee.
This dissertation establishes feasibility of principles fundamental to the proposed concept. Hardware is conceptualized to accommodate Space Sweeper ’s specialized needs. Mathematical models are built for the purpose of analysis and simulation. A kinematic analysis investigates system demands and long-term behavior resulting from repeated
debris interaction. A successful approach to enforce
debris capture is established through optimal control techniques. A study of orbital parameters and their response to
debris interactions builds an intuition for missions of this nature. Finally, a J2-compliant technique for path optimization is demonstrated. The results strongly support feasibility of the proposed mission.
Advisors/Committee Members: Mortari, Daniele (advisor), Junkins, John (committee member), Valasek, John (committee member), Rojas, J. Maurice (committee member).
Subjects/Keywords: Active; space; debris; removal; Sling-sat; sweeper
…15]), active debris removal
is necessary; unfortunately, this is a nontrivial… …11
2.3.5 Active Removal
Active debris removal methods involve some form of controlled… …the economic solution to active debris
removal, but it does not establish how a removal… …in favor of attitude dynamics.
Navigating the political grounds of active debris removal… …refueling station.
In terms of active debris removal, this means a team of debris-capturing…
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APA ·
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APA (6th Edition):
Missel, J. W. (2013). Active Space Debris Removal using Capture and Ejection. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/149391
Chicago Manual of Style (16th Edition):
Missel, Jonathan William. “Active Space Debris Removal using Capture and Ejection.” 2013. Doctoral Dissertation, Texas A&M University. Accessed March 01, 2021.
http://hdl.handle.net/1969.1/149391.
MLA Handbook (7th Edition):
Missel, Jonathan William. “Active Space Debris Removal using Capture and Ejection.” 2013. Web. 01 Mar 2021.
Vancouver:
Missel JW. Active Space Debris Removal using Capture and Ejection. [Internet] [Doctoral dissertation]. Texas A&M University; 2013. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/1969.1/149391.
Council of Science Editors:
Missel JW. Active Space Debris Removal using Capture and Ejection. [Doctoral Dissertation]. Texas A&M University; 2013. Available from: http://hdl.handle.net/1969.1/149391
Delft University of Technology
10.
Singh, Sunayna (author).
Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages.
Degree: 2019, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:625c408b-97ae-47a5-90c9-493dc4bc0224
► The space environment is ever-changing with space structures getting larger and the orbits getting increasingly crowded with time. This creates a need for removal of…
(more)
▼ The space environment is ever-changing with space structures getting larger and the orbits getting increasingly crowded with time. This creates a need for removal of large defunct satellites to avoid the disastrous Kessler syndrome, which poses a major threat to the future of space exploration. This research examines the dynamics and control involved in the active removal of a large space debris - Envisat. European Space Agency's e.deorbit mission aims to de-orbit Envisat using a chaser satellite, which synchronises, docks, detumbles and deorbits it. The presence of large flexible appendages makes the configuration prone to elastic perturbations leading to complex dynamics that cannot be represented using rigid body dynamics. Therefore, a unique multibody approach based on the absolute interface coordinates in the floating frame formulation is used to model the Flexible Multibody Dynamics. The novel method proves to provide a good balance between computation time and efficiency for the control application. The controllability characteristics of two phases of the e.deorbit mission are analysed using a linear PD controller and an Incremental Nonlinear Dynamic Inversion controller. For the first phase, both controllers successfully synchronise the chaser with the target debris tumbling at the rate of 3.5 deg/s about all axes. However, during the detumbling phase, the large appendage (14.2 m) in the stacked configuration introduces complex dynamics, which could not be stabilised completely by applied controllers. Nonetheless, interesting relationships could be established between the dynamics and control of the system, which will facilitate robust control design in future work.
Aerospace Engineering
Advisors/Committee Members: Mooij, Erwin (mentor), Gransden, Derek (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: Space debris; multibody dynamics; Flexible structures; Control; Active debris removal; floating frames
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APA ·
Chicago ·
MLA ·
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CSE |
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APA (6th Edition):
Singh, S. (. (2019). Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:625c408b-97ae-47a5-90c9-493dc4bc0224
Chicago Manual of Style (16th Edition):
Singh, Sunayna (author). “Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages.” 2019. Masters Thesis, Delft University of Technology. Accessed March 01, 2021.
http://resolver.tudelft.nl/uuid:625c408b-97ae-47a5-90c9-493dc4bc0224.
MLA Handbook (7th Edition):
Singh, Sunayna (author). “Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages.” 2019. Web. 01 Mar 2021.
Vancouver:
Singh S(. Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages. [Internet] [Masters thesis]. Delft University of Technology; 2019. [cited 2021 Mar 01].
Available from: http://resolver.tudelft.nl/uuid:625c408b-97ae-47a5-90c9-493dc4bc0224.
Council of Science Editors:
Singh S(. Multibody Approach to Controlled Removal of Large Space Debris with Flexible Appendages. [Masters Thesis]. Delft University of Technology; 2019. Available from: http://resolver.tudelft.nl/uuid:625c408b-97ae-47a5-90c9-493dc4bc0224
. 
Open Access Theses and Dissertations
