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University of Illinois – Urbana-Champaign
1.
Sarton Du Jonchay, Tristan.
Modeling and simulation of permanent on-orbit servicing infrastructures dedicated to modularized earth-orbiting platforms.
Degree: MS, Aerospace Engineering, 2017, University of Illinois – Urbana-Champaign
URL: http://hdl.handle.net/2142/97510 
► This research aims to quantify the responsiveness and cost-effectiveness of permanent on-orbit servicing (OOS) infrastructures providing services to multiple serviceable platforms in coplanar medium Earth…
(more)
▼ This research aims to quantify the responsiveness and cost-effectiveness of permanent on-
orbit servicing (OOS) infrastructures providing services to multiple serviceable platforms in coplanar medium Earth
orbit (MEO) and/or geostationary
orbit (GEO). The customer satellites are assumed to be made of elementary units (EUs). EUs are small standardized structural units capable of aggregating with each other and gathering the key functions of a typical satellite within the size of a 6U cubesat. Two OOS infrastructures are modeled in this research. The first one, called “Without depot” (WoD), includes a launch vehicle and a robotic servicer. The second infrastructure, called “With Depot” (WD), includes a launch vehicle, a robotic servicer and an orbital depot of EUs. This research is divided in two parts. The first part quickly developed a Simulink-based event-driven simulation framework to compare the responsiveness of WoD and WD, and provide some insight into their respective cost-effectiveness. The metrics used to quantify responsiveness for this first study are the service completion rate and the average waiting time before an EU is replaced over a 10-year period of operation. It is shown that WD is more responsive thanWoD but is also likely to be more expensive to run. Based on this observation, the second part of this research developed a Python-based event-driven simulation framework capable of capturing a much larger trade space of the WD infrastructure than the Simulink framework does. The Python framework considers more accurate models and includes much more OOS design features, such as the number of servicers, more efficient service dispatch strategies and new space trajectories. For this second study, responsiveness is measured via the average working state of the population of customer satellites, which captures how well the satellites work based on three different failure severities and the number of failures. Cost-effectiveness is measured thanks to the average mass sent to
orbit per year required to efficiently run the OOS infrastructures. It is first shown that there exist designs based on propellant optimal trajectories yielding similar levels of responsiveness as designs using Lambert-trajectory-based propellant-time-traded trajectories but at much lower costs. The second conclusion is that finding responsive and cost-effective OOS designs is not intuitive. This has to be done through an exhaustive exploration of the trade space of OOS, given the high number of design variables. This research si believed to be a critical milestone in the design of a responsive integrated space infrastructure dedicated to the development and prosperity of a new GEO/MEO economy.
Advisors/Committee Members: Ho, Koki (advisor).
Subjects/Keywords: On-orbit servicing; Satellite modularization
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APA (6th Edition):
Sarton Du Jonchay, T. (2017). Modeling and simulation of permanent on-orbit servicing infrastructures dedicated to modularized earth-orbiting platforms. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/97510
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):
Sarton Du Jonchay, Tristan. “Modeling and simulation of permanent on-orbit servicing infrastructures dedicated to modularized earth-orbiting platforms.” 2017. Thesis, University of Illinois – Urbana-Champaign. Accessed March 07, 2021.
http://hdl.handle.net/2142/97510.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Sarton Du Jonchay, Tristan. “Modeling and simulation of permanent on-orbit servicing infrastructures dedicated to modularized earth-orbiting platforms.” 2017. Web. 07 Mar 2021.
Vancouver:
Sarton Du Jonchay T. Modeling and simulation of permanent on-orbit servicing infrastructures dedicated to modularized earth-orbiting platforms. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2017. [cited 2021 Mar 07].
Available from: http://hdl.handle.net/2142/97510.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Sarton Du Jonchay T. Modeling and simulation of permanent on-orbit servicing infrastructures dedicated to modularized earth-orbiting platforms. [Thesis]. University of Illinois – Urbana-Champaign; 2017. Available from: http://hdl.handle.net/2142/97510
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
2.
Sciortino, Douglas.
Satellite Constellation Architecture and Design to take Advantage of On-Orbit Servicing and Repair.
Degree: MS, Systems Engineering, 2018, Loyola Marymount University
URL: https://digitalcommons.lmu.edu/etd/940
► Access to space is becoming less expensive, which is allowing smaller companies with big ideas, such as on-orbit servicing and repair, to enter into…
(more)
▼ Access to space is becoming less expensive, which is allowing smaller companies with big ideas, such as on-
orbit servicing and repair, to enter into the space industry. On-
orbit servicing and repair provides capabilities, such as towing, refueling, inspections, and physical repair, to add additional life to on-
orbit satellites by resolving life-limiting issues. On-
orbit servicing and repair is technically possible, but there is still one major issue that continues to stifle the on-
orbit servicing and repair market – “satellites are not built with
servicing in mind” (Parker, 2015). The on-
orbit servicing and repair industry is stagnate due to a challenging conundrum. Potential satellite customers are unwilling to pay for on-
orbit servicing or repair until the capability is successfully demonstrated on-
orbit. Unfortunately, it is difficult for the industry to prove the capability without customers willing to take a little risk. This “chicken and egg” scenario leaves several satellite manufacturers unwilling to change their satellite architectures and designs to accommodate on-
orbit servicing and repair. This paper attempts to show the “how” and the “why” the space industry should change their architectures and designs to enable on-
orbit servicing and repair. There are many satellite bus components/consumables, including software, that could fail and shorten a satellite’s life. However, the bus components/consumables that fail the most, batteries, solar arrays, propellant, reaction wheels, and power distribution components, are best suited for on-
orbit servicing and repair. These five bus components/consumables, in addition to the satellite as a whole, will require several design changes specific to each bus component, which will drive new or updated requirements for each. Additionally, to increase the effectiveness and efficiency of on-
orbit servicing and repair, satellite architectures will require changes, such as an on-
orbit depot, on-
orbit warehouse, and on-
orbit gas tank. The consequence of changing satellite design will affect satellite ground testing. The on-
orbit servicing and repair processes, such as rendezvous, docking, and EMI/EMC will require testing between the on-
orbit servicer and its customer satellite. The on-
orbit servicing and repair capability provides the satellite manufacturer the ability to reduce qualification testing, run-time testing, and burn-in testing. This capability increases the probability that redundancy for these five bus components/consumables is no longer required, which reduces the hardware cost and testing schedule for each satellite. On-
orbit servicing and repair creates seven new risks – do no harm, debris and contamination, on-
orbit servicer reliability, politics, cyber security, liability, and unintended consequences – that must be mitigated. Two simple business cases demonstrate the possible value of this new capability. The business case for Low Earth
Orbit (LEO) does not provide a return on investment, because on-
orbit…
Advisors/Committee Members: Claire Leon.
Subjects/Keywords: on-orbit repair servicing space satellites; Systems Engineering
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APA (6th Edition):
Sciortino, D. (2018). Satellite Constellation Architecture and Design to take Advantage of On-Orbit Servicing and Repair. (Masters Thesis). Loyola Marymount University. Retrieved from https://digitalcommons.lmu.edu/etd/940
Chicago Manual of Style (16th Edition):
Sciortino, Douglas. “Satellite Constellation Architecture and Design to take Advantage of On-Orbit Servicing and Repair.” 2018. Masters Thesis, Loyola Marymount University. Accessed March 07, 2021.
https://digitalcommons.lmu.edu/etd/940.
MLA Handbook (7th Edition):
Sciortino, Douglas. “Satellite Constellation Architecture and Design to take Advantage of On-Orbit Servicing and Repair.” 2018. Web. 07 Mar 2021.
Vancouver:
Sciortino D. Satellite Constellation Architecture and Design to take Advantage of On-Orbit Servicing and Repair. [Internet] [Masters thesis]. Loyola Marymount University; 2018. [cited 2021 Mar 07].
Available from: https://digitalcommons.lmu.edu/etd/940.
Council of Science Editors:
Sciortino D. Satellite Constellation Architecture and Design to take Advantage of On-Orbit Servicing and Repair. [Masters Thesis]. Loyola Marymount University; 2018. Available from: https://digitalcommons.lmu.edu/etd/940
University of Illinois – Urbana-Champaign
3.
Sears, Patrick.
Impact evaluation of in-space additive manufacturing and recycling technologies for on-orbit servicing.
Degree: MS, Aerospace Engineering, 2018, University of Illinois – Urbana-Champaign
URL: http://hdl.handle.net/2142/101237
► This thesis proposes an integrated simulation tool to evaluate the impact of future in-space additive manufacturing (ISAM) and recycling technologies on the responsiveness of an…
(more)
▼ This thesis proposes an integrated simulation tool to evaluate the impact of future in-space additive manufacturing (ISAM) and recycling technologies on the responsiveness of an on-
orbit servicing (OOS) infrastructure to random failures of satellites distributed over an
orbit. The considered OOS infrastructure is composed of a mothership and a servicer (i.e., daughtership); the mothership serves as a depot for spares, whereas the servicer travels with the spares to randomly failed satellites and provides a service. All satellites are assumed to be modularized, and thus the service type considered within the infrastructure is the replacement of a failed module with a new spare one. Additionally, an ISAM facility can be added to the mothership, which can scavenge material that makes up the failed module. This obtained feedstock from failed modules, along with raw material supplied from Earth, could be used to manufacture a new spare. The key parameters in this analysis include the technology level of ISAM, in terms of the types of material it can manufacture, and the scavenge rate, defined as the percent of material mass able to be recycled from the failed module to the new module. The two metrics for evaluation are the required resupply launch mass to the mothership and the average waiting time of the satellites before it is serviced. Simulations results showed that the ISAM and recycling technology provides a large impact in terms of both reduction in resupply launch mass and responsiveness of its service to the randomly failed satellites.
Advisors/Committee Members: Ho, Koki (advisor).
Subjects/Keywords: On-Orbit Servicing; Additive Manufacturing; Space Systems; Modularized Satellite; 3D Printing; Simulation; Geostationary orbit
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APA (6th Edition):
Sears, P. (2018). Impact evaluation of in-space additive manufacturing and recycling technologies for on-orbit servicing. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/101237
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):
Sears, Patrick. “Impact evaluation of in-space additive manufacturing and recycling technologies for on-orbit servicing.” 2018. Thesis, University of Illinois – Urbana-Champaign. Accessed March 07, 2021.
http://hdl.handle.net/2142/101237.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Sears, Patrick. “Impact evaluation of in-space additive manufacturing and recycling technologies for on-orbit servicing.” 2018. Web. 07 Mar 2021.
Vancouver:
Sears P. Impact evaluation of in-space additive manufacturing and recycling technologies for on-orbit servicing. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2018. [cited 2021 Mar 07].
Available from: http://hdl.handle.net/2142/101237.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Sears P. Impact evaluation of in-space additive manufacturing and recycling technologies for on-orbit servicing. [Thesis]. University of Illinois – Urbana-Champaign; 2018. Available from: http://hdl.handle.net/2142/101237
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Illinois – Urbana-Champaign
4.
Perez, Jeff.
Stochastic design optimization of modular, reconfigurable, persistent support platforms in Earth orbit.
Degree: MS, Aerospace Engineering, 2019, University of Illinois – Urbana-Champaign
URL: http://hdl.handle.net/2142/104870
► This thesis focuses on the design and optimization of modular, reconfigurable, hosted payload platforms operating in Earth orbit. Recent advancements in on-orbit servicing technologies and…
(more)
▼ This thesis focuses on the design and optimization of modular, reconfigurable, hosted payload platforms operating in Earth
orbit. Recent advancements in on-
orbit servicing technologies and robotics are creating a market for hosted-payload platforms which can support multiple payloads with varying requirements. Such platforms can employ on-
orbit servicing and robotic manipulation to repair or replace modules, enhance the platform’s capabilities over time, and reconfigure modules to optimize performance. Traditional spacecraft design is often driven largely by payload requirements. For the case of persistent platforms, however, not all payloads will be known in the initial design phase. This presents a unique challenge to designers, who must account for the uncertainty of future payloads by trading off between the costs of adding more capability to the platform initially, which assumes the risk of wasted costs due to over-designing the platform, and the costs of utilizing an on-
orbit servicer to add capability as needed. The hosted payload platforms considered in this thesis consist of platform modules and payload modules and uses a standardized interface for intermodular and customer payload connection. Each platform module contains a critical satellite subsystem that is necessary for on-
orbit functionality. As payloads are added to the platform over time, their demands may exceed the current capability of the platform, at which point additional platform modules can be added to increase the platforms capabilities. This thesis proposes an approach using a multi-stage stochastic programming method to create an initial platform design that is robust and flexible enough to support a wide range of payloads and minimizes the expected costs of future platform additions. Probability distributions for future payload selections are created based on a survey of active satellites. These distributions are then used to create samples of payload selection scenarios. Using a simple cost model, the expected costs associated with the addition of new payloads and the required platform modules are computed for each scenario in the sample. A genetic algorithm is used to find an optimal initial platform size that minimizes the combined total of the initial cost of the platform and the expected on-
orbit servicing costs associated with adding future payloads and platform modules for each scenario. Platform designs are compared for a range of on-
orbit servicing costs to determine the cost at which the optimizer begins to utilize
servicing over adding more capability initially. Finally, a sensitivity analysis is performed to assess the variations in platform design due to the randomly selected payload scenario samples. The results of this work are a first step towards a solving a unique challenge presented by an emerging and increasingly relevant mission concept.
Advisors/Committee Members: Ho, Koki (advisor).
Subjects/Keywords: Stochastic design optimization; hosted payload platform; persistent support platform; modular satellite; spacecraft design optimization; multistage stochastic programming; reconfigurable; on-orbit satellite servicing; servicing spacecraft; robotic servicer; reconfigurable satellite
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APA (6th Edition):
Perez, J. (2019). Stochastic design optimization of modular, reconfigurable, persistent support platforms in Earth orbit. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/104870
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):
Perez, Jeff. “Stochastic design optimization of modular, reconfigurable, persistent support platforms in Earth orbit.” 2019. Thesis, University of Illinois – Urbana-Champaign. Accessed March 07, 2021.
http://hdl.handle.net/2142/104870.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Perez, Jeff. “Stochastic design optimization of modular, reconfigurable, persistent support platforms in Earth orbit.” 2019. Web. 07 Mar 2021.
Vancouver:
Perez J. Stochastic design optimization of modular, reconfigurable, persistent support platforms in Earth orbit. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2019. [cited 2021 Mar 07].
Available from: http://hdl.handle.net/2142/104870.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Perez J. Stochastic design optimization of modular, reconfigurable, persistent support platforms in Earth orbit. [Thesis]. University of Illinois – Urbana-Champaign; 2019. Available from: http://hdl.handle.net/2142/104870
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Luleå University of Technology
5.
Bondoky, Karim.
On-Orbit Servicing Satellite Docking Mechanism Modeling and Simulation.
Degree: 2015, Luleå University of Technology
URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-56392
► Docking mechanism of two spacecraft is considered as one of the main challenging aspects of an on-orbit servicing mission. This thesis presents the modeling,…
(more)
▼ Docking mechanism of two spacecraft is considered as one of the main challenging aspects of an on-orbit servicing mission. This thesis presents the modeling, analysis and software simulation of one of the docking mechanisms called "probe and drogue". The aim of this thesis is to model the docking mechanism, simulate the docking process and use the results as a reference for the Hardware-In-the-Loop simulation (HIL) of the docking mechanism, in order to verify and validate it. Modeling of the two spacecraft, docking mechanism and the contact dynamics are the most challenging parts of this thesis. The spacecraft motion's modeling is done using Newton-Euler equations, with consideration of the homogeneous transformations of the different coordinate frames. Contact dynamics modeling included the Hertz dynamics, different types of damping models and a modified Coulomb's friction model. Simulink/ Matlab 2013b are used to build two models, one for numerical analysis of the model and another one for the HIL simulation. Results are analyzed in Matlab and visualized using the 3D visualization program that is built within the scope of this thesis. The results are then used as a guide for the requirements of the robotic hardware that will carry out the HIL simulation. Also, two different robotics hardware are proposed in this thesis to carry out the HIL simulation. The work has a lot of aspects in common with the satellite of the German Space Agency (DLR) called, "DEutsche Orbitale Servicing Mission" (DEOS). This work took place in Friedrichshafen/Germany at the facilities of Airbus Defence and Space (the prime contractor of DEOS) in collaboration with Würzburg university in Germany and Luleå university of technology in Sweden.
Validerat; 20141221 (global_studentproject_submitter)
Subjects/Keywords: Technology; Docking; On-Orbit Servicing; Contact Dynamics; Multi-body Modeling; Multi-body Dynamics; Newton-Euler; Homogenous Transformations; Teknik
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APA (6th Edition):
Bondoky, K. (2015). On-Orbit Servicing Satellite Docking Mechanism Modeling and Simulation. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-56392
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):
Bondoky, Karim. “On-Orbit Servicing Satellite Docking Mechanism Modeling and Simulation.” 2015. Thesis, Luleå University of Technology. Accessed March 07, 2021.
http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-56392.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Bondoky, Karim. “On-Orbit Servicing Satellite Docking Mechanism Modeling and Simulation.” 2015. Web. 07 Mar 2021.
Vancouver:
Bondoky K. On-Orbit Servicing Satellite Docking Mechanism Modeling and Simulation. [Internet] [Thesis]. Luleå University of Technology; 2015. [cited 2021 Mar 07].
Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-56392.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Bondoky K. On-Orbit Servicing Satellite Docking Mechanism Modeling and Simulation. [Thesis]. Luleå University of Technology; 2015. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-56392
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Delft University of Technology
6.
Crepy-Marglais, Jean-Daniel (author).
Development of a Robust and Combined Controller for On-Orbit Servicing Missions.
Degree: 2018, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:f163745c-e9d9-4b22-9e5b-1f4d3790ebf6
► Nowadays, a satellite is considered as out of range forever once it is launched. This may soon no longer hold thanks to on-orbit servicing. However,…
(more)
▼ Nowadays, a satellite is considered as out of range forever once it is launched. This may soon no longer hold thanks to on-orbit servicing. However, the complexity of that topic makes it highly challenging on many aspects. On-orbit servicing using a robotic arm is nonetheless the most investigated technology in order to achieve the berthing of two satellites in orbit. This research project aims at developing a robust controller for the deployment of a robotic arm, which is mounted on a servicer satellite, and for the reaching of a defined handle on the target satellite under mission constraints. While operating the space manipulator, the combined control of both the manipulator and the spacecraft base has a great potential in terms of achievable performance and may bring robotic on-orbit servicing one step closer to reality. In order to reveal the potential of this innovative control strategy, a model of the system dynamics was developed, before being used to design a robust controller. The latter was then successfully implemented in different simulators to test its performance and robustness to a variety of constraints including hardware, environment and mission constraints. The simulations proved that combined control can be used for the entire maneuver. Finally, this controller was successfully implemented in the on-board computer of the on-orbit servicing simulator at the German Aerospace Center. From now on, the maneuver can be completed from the ground control room. The implementation of the robust and combined controller has increased the technology readiness level of the reach phase during an on-orbit servicing mission.
RICADOS
Aerospace Engineering
Advisors/Committee Members: Fónod, Róbert (mentor), Krenn, Rainer (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: space robotics; on-orbit servicing; Control; H-infinity control; Attitude control; Robotics; loop shaping; combined control; robust control
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APA (6th Edition):
Crepy-Marglais, J. (. (2018). Development of a Robust and Combined Controller for On-Orbit Servicing Missions. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:f163745c-e9d9-4b22-9e5b-1f4d3790ebf6
Chicago Manual of Style (16th Edition):
Crepy-Marglais, Jean-Daniel (author). “Development of a Robust and Combined Controller for On-Orbit Servicing Missions.” 2018. Masters Thesis, Delft University of Technology. Accessed March 07, 2021.
http://resolver.tudelft.nl/uuid:f163745c-e9d9-4b22-9e5b-1f4d3790ebf6.
MLA Handbook (7th Edition):
Crepy-Marglais, Jean-Daniel (author). “Development of a Robust and Combined Controller for On-Orbit Servicing Missions.” 2018. Web. 07 Mar 2021.
Vancouver:
Crepy-Marglais J(. Development of a Robust and Combined Controller for On-Orbit Servicing Missions. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Mar 07].
Available from: http://resolver.tudelft.nl/uuid:f163745c-e9d9-4b22-9e5b-1f4d3790ebf6.
Council of Science Editors:
Crepy-Marglais J(. Development of a Robust and Combined Controller for On-Orbit Servicing Missions. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:f163745c-e9d9-4b22-9e5b-1f4d3790ebf6
York University
7.
Santaguida, Lucas Francesco.
Study of Autonomous Capture and Detumble of Non-Cooperative Target by a Free-Flying Space Manipulator Using an Air-Bearing Platform.
Degree: MASc - Master of Applied Science, Mechanical Engineering, 2020, York University
URL: http://hdl.handle.net/10315/37778
► This thesis developed a 3-DOF satellite simulator with an attached 3-DOF manipulator to capture and detumble a target satellite simulator. Existing systems are heavily dependent…
(more)
▼ This thesis developed a 3-DOF satellite simulator with an attached 3-DOF manipulator to capture and detumble a target satellite simulator. Existing systems are heavily dependent on external systems to compute the position and orientation of the chaser and target satellite simulators. Using external sensors and high-power computers allows their systems to have high accuracy and high sampling frequencies. This approach is not reflective of the challenges faced by an on-
orbit servicing spacecraft as all positioning of the space vehicle is computed on-board. In addition, their systems use the same external sensors to determine the position and orientation of the target simulator and transmit it to the chaser. A true on-
orbit servicing vehicle would need to sense and compute the target simulators position and orientation relative to itself. The simulator developed in this thesis addresses these issues by computing its own position using a star-tracking system and computes the relative position and orientation of the target simulator using a monocular camera. The simulator was developed to act as a testbed for on-
orbit servicing technologies. Different sensors, path planning and control algorithms can be implemented to test their effectiveness before implementation on a
servicing vehicle. To demonstrate this, a PD controller as well as an adaptive controller were implemented. Fuzzy logic was used to perform gain scheduling on the PD controller to improve its performance.
Advisors/Committee Members: Zhu, George Z. H. (advisor).
Subjects/Keywords: Robotics; On-Orbit Servicing; Air-bearing testbed; Planning; Space Vehicles; Autonomous; Free-Flying Space Robotic; Orbital Robotics
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APA (6th Edition):
Santaguida, L. F. (2020). Study of Autonomous Capture and Detumble of Non-Cooperative Target by a Free-Flying Space Manipulator Using an Air-Bearing Platform. (Masters Thesis). York University. Retrieved from http://hdl.handle.net/10315/37778
Chicago Manual of Style (16th Edition):
Santaguida, Lucas Francesco. “Study of Autonomous Capture and Detumble of Non-Cooperative Target by a Free-Flying Space Manipulator Using an Air-Bearing Platform.” 2020. Masters Thesis, York University. Accessed March 07, 2021.
http://hdl.handle.net/10315/37778.
MLA Handbook (7th Edition):
Santaguida, Lucas Francesco. “Study of Autonomous Capture and Detumble of Non-Cooperative Target by a Free-Flying Space Manipulator Using an Air-Bearing Platform.” 2020. Web. 07 Mar 2021.
Vancouver:
Santaguida LF. Study of Autonomous Capture and Detumble of Non-Cooperative Target by a Free-Flying Space Manipulator Using an Air-Bearing Platform. [Internet] [Masters thesis]. York University; 2020. [cited 2021 Mar 07].
Available from: http://hdl.handle.net/10315/37778.
Council of Science Editors:
Santaguida LF. Study of Autonomous Capture and Detumble of Non-Cooperative Target by a Free-Flying Space Manipulator Using an Air-Bearing Platform. [Masters Thesis]. York University; 2020. Available from: http://hdl.handle.net/10315/37778
8.
Paraskevas, Iosif.
Capturing of orbital space systems by robots.
Degree: 2015, National Technical University of Athens (NTUA); Εθνικό Μετσόβιο Πολυτεχνείο (ΕΜΠ)
URL: http://hdl.handle.net/10442/hedi/41279
► Space exploration and exploitation require enhancing of the human and robotic infrastructure on orbitand beyond. To this end, tasks like satellite servicing, space debris removal…
(more)
▼ Space exploration and exploitation require enhancing of the human and robotic infrastructure on orbitand beyond. To this end, tasks like satellite servicing, space debris removal and construction of largeassemblies on Earth’s or other planetary orbits will be of critical importance in the near future. Thus,many space agencies such as NASA, ESA and JAXA have already incorporated OOS activities in theirroadmaps. Tο achieve these goals, prior extensive analysis of any OOS mission is required. Animportant part of such missions is reaching and capturing/ docking a Target (satellite or debris).Capturing and docking to the Target by a space robotic system (Chaser), consisting of a non-fixedsatellite base and of one or more manipulators mounted on it, is an especially demanding task, due tothe dynamic coupling between them. Additionally, these procedures are inevitably associated withimpact forces as these bodies come into contact. The challenges are higher when the robotic systemand the Target have comparable masses. In the case of passive docking, known as impact docking,these impact forces are also part of the procedure. Unsuccessful impacts may separate the servicerfrom the target, or damage critical subsystems, therefore the study of the behaviour of the participatingsystems under impact is vital. For all the above reasons, some of the aspects which need thoroughexamination during impacts in free-fall environment include: (a) adequate modelling of the procedure,(b) effects of mass and compliance parameters, (c) design and control of an effective approach of theChaser to the Target.In this work, an analysis of the modelling of impacts of two bodies in space is presented. Limitations ofcurrent viscoelastic models are described, and a novel viscoplastic model is developed which showsvery good correlation with experimental results found in the literature. Interestingly the generalization ofthis model to impacts that occur in terrestrial applications shows that this model has high potential ineveryday robotic applications. Simulations and examples are presented which support this statement.Next, the usual approaches during modeling of impact docking is presented and examined. Theseapproaches lack on accounting the effects of inertia and stiffness of the systems of masses that comeinto contact. A more generalized approach in modeling this free-floating impact by usingcomputationally fast methods stemming from rigid- body theory is shown. The effect of the mass ratioof the systems under impact is quantified. Insights to on-going research on the stiffness effects are alsopresented. Finally a method is proposed in order to reduce reaction forces during impacts. The exertedreactions can be minimized using the Center of Percussion (CoP) concept. After the two- and threedimensionalcases are presented, the performance of a robot under impact is assessed exploiting theCoP. The effects of parametric sensitivity on the joint reactions at a manipulator are examined. Αcontrol method to compensate the reaction forces is proposed.…
Subjects/Keywords: Ρομποτική; Τροχιακές υπηρεσίες; Μοντέλο Κρούσης; Κρουστικό Κέντρο; Δυναμική και Έλεγχος; Robotics; On - orbit servicing; Impact Model; Center of percussion; Dynamics and control
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APA (6th Edition):
Paraskevas, I. (2015). Capturing of orbital space systems by robots. (Thesis). National Technical University of Athens (NTUA); Εθνικό Μετσόβιο Πολυτεχνείο (ΕΜΠ). Retrieved from http://hdl.handle.net/10442/hedi/41279
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):
Paraskevas, Iosif. “Capturing of orbital space systems by robots.” 2015. Thesis, National Technical University of Athens (NTUA); Εθνικό Μετσόβιο Πολυτεχνείο (ΕΜΠ). Accessed March 07, 2021.
http://hdl.handle.net/10442/hedi/41279.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Paraskevas, Iosif. “Capturing of orbital space systems by robots.” 2015. Web. 07 Mar 2021.
Vancouver:
Paraskevas I. Capturing of orbital space systems by robots. [Internet] [Thesis]. National Technical University of Athens (NTUA); Εθνικό Μετσόβιο Πολυτεχνείο (ΕΜΠ); 2015. [cited 2021 Mar 07].
Available from: http://hdl.handle.net/10442/hedi/41279.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Paraskevas I. Capturing of orbital space systems by robots. [Thesis]. National Technical University of Athens (NTUA); Εθνικό Μετσόβιο Πολυτεχνείο (ΕΜΠ); 2015. Available from: http://hdl.handle.net/10442/hedi/41279
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Maryland
9.
Koelln, Nathan Thomas.
Task-Based Mass Optimization of Reconfigurable Robotic Manipulator Systems.
Degree: Aerospace Engineering, 2006, University of Maryland
URL: http://hdl.handle.net/1903/3943
► This work develops a method for implementing task-based mass optimization of modular, reconfigurable manipulators. Link and joint modules are selected from a library of potential…
(more)
▼ This work develops a method for implementing task-based mass optimization of modular, reconfigurable manipulators. Link and joint modules are selected from a library of potential parts and assembled into serial manipulator configurations. A genetic algorithm is used to search over the potential set of combinations to find mass-minimized solutions. To facilitate the automatic evaluation required by the genetic algorithm, Denavit-Hartenberg parameters are automatically generated from module combinations. Reconfigurable manipulators are shown to be lighter than fixed-topology manipulators, demonstrating the potential utility of reconfigurable robotics technology for mass reduction in space robots.
Advisors/Committee Members: Akin, David L (advisor).
Subjects/Keywords: Engineering, Aerospace; Reconfigular Robotics; Modular Robotics; Genetic Algorithm; On-Orbit Servicing
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APA (6th Edition):
Koelln, N. T. (2006). Task-Based Mass Optimization of Reconfigurable Robotic Manipulator Systems. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/3943
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):
Koelln, Nathan Thomas. “Task-Based Mass Optimization of Reconfigurable Robotic Manipulator Systems.” 2006. Thesis, University of Maryland. Accessed March 07, 2021.
http://hdl.handle.net/1903/3943.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Koelln, Nathan Thomas. “Task-Based Mass Optimization of Reconfigurable Robotic Manipulator Systems.” 2006. Web. 07 Mar 2021.
Vancouver:
Koelln NT. Task-Based Mass Optimization of Reconfigurable Robotic Manipulator Systems. [Internet] [Thesis]. University of Maryland; 2006. [cited 2021 Mar 07].
Available from: http://hdl.handle.net/1903/3943.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Koelln NT. Task-Based Mass Optimization of Reconfigurable Robotic Manipulator Systems. [Thesis]. University of Maryland; 2006. Available from: http://hdl.handle.net/1903/3943
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
10.
Rekleitis, Georgios.
Motion planning and control of cooperating robotic systems in orbit.
Degree: 2015, National Technical University of Athens (NTUA); Εθνικό Μετσόβιο Πολυτεχνείο (ΕΜΠ)
URL: http://hdl.handle.net/10442/hedi/39463
► Both interplanetary traveling crafts and stationary systems will be in need of servicing, such as assembly, maintenance, replacement of broken/expendable modules, refueling, inspection and repair.…
(more)
▼ Both interplanetary traveling crafts and stationary systems will be in need of servicing, such as assembly, maintenance, replacement of broken/expendable modules, refueling, inspection and repair. To relieve astronauts from dangerous extra-vehicular activities, enhance performance and extend the feasible tasks range, the international research community has been focusing on the realization of autonomous robotic servicing. While important tasks, such as orbital assembly and debris handling, require passive object handling capabilities, the actual handling of a secured passive object by a number of free-flying robotic servicers, has not been studied adequately, with several issues still open.On-orbit object handling has similarities to cooperative manipulation of passive objects on earth, with the additional complexities that in space no fixed ground to support the manipulators exists, thus letting momentum changes to play a key role in body motion, and that orbital system thrusters are of on-off control nature. In order to protect the thruster valves from the extreme space conditions, proportional or pulse-width-modulation (PWM) thrusters are not used in space, thus reducing system positioning capabilities, when only thrusters are used.The introduction of a number of manipulator-equipped free-flying servicers, where both on-off thruster propulsion and manipulator continuous forces/ torques are used for passive object handling, both for the case of firm grasp and in the more general case of point contact, between the servicer manipulator end-effectors and the passive object, is presented in this thesis.The design of a controller for the free-flying servicer manipulators that enables the stable handling of the passive object by the servicers, in trajectory tracking scenarios, as well as the design of a controller for the free-flying servicer bases that enables them to move within the workspace of their manipulators, under the influence of the reaction generalized forces from their manipulator bases, is also presented. An initial comparison between the choice of three small free-flying robotic servicers and a single, larger one is also conducted.A spatial system of robotic servicers handling a passive object is highly non-linear. Unfortunately, there is not much generally applied theory on the field of non-linear system robustness. One method is to use linearization, under certain assumptions, in order to be able to use linear systems robustness tools. The sensitivity of the controller for the 3D motion of the handled passive object in space in terms of parameter estimation is also studied in this work.Finally, the design of a two-layer optimization process that allows for i) optimal selection of contact points between the manipulator end-effectors and the passive object, for both contact cases and ii) force distribution so that the required control generalized force for the passive object motion, is applied by the manipulator end-effectors, is also presented.
Τόσο τα διαπλανητικά σκάφη, όσο και τα στατικά διαστημικά…
Subjects/Keywords: Τροχιακές διεργασίες εξυπηρέτησης;
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APA (6th Edition):
Rekleitis, G. (2015). Motion planning and control of cooperating robotic systems in orbit. (Thesis). National Technical University of Athens (NTUA); Εθνικό Μετσόβιο Πολυτεχνείο (ΕΜΠ). Retrieved from http://hdl.handle.net/10442/hedi/39463
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):
Rekleitis, Georgios. “Motion planning and control of cooperating robotic systems in orbit.” 2015. Thesis, National Technical University of Athens (NTUA); Εθνικό Μετσόβιο Πολυτεχνείο (ΕΜΠ). Accessed March 07, 2021.
http://hdl.handle.net/10442/hedi/39463.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Rekleitis, Georgios. “Motion planning and control of cooperating robotic systems in orbit.” 2015. Web. 07 Mar 2021.
Vancouver:
Rekleitis G. Motion planning and control of cooperating robotic systems in orbit. [Internet] [Thesis]. National Technical University of Athens (NTUA); Εθνικό Μετσόβιο Πολυτεχνείο (ΕΜΠ); 2015. [cited 2021 Mar 07].
Available from: http://hdl.handle.net/10442/hedi/39463.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Rekleitis G. Motion planning and control of cooperating robotic systems in orbit. [Thesis]. National Technical University of Athens (NTUA); Εθνικό Μετσόβιο Πολυτεχνείο (ΕΜΠ); 2015. Available from: http://hdl.handle.net/10442/hedi/39463
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Delft University of Technology
11.
Barad, K.R. (author).
Robust Navigation Framework for Proximity Operations around Uncooperative Spacecraft: A monocular vision-based navigation approach using deep learning.
Degree: 2020, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:6dbf6f1d-b41b-42c1-ad78-619a6c6cf071
► Autonomous vision-based navigation is a crucial element for space applications involving a potentially uncooperative target, such as proximity operations for on-orbit servicing or active debris…
(more)
▼ Autonomous vision-based navigation is a crucial element for space applications involving a potentially uncooperative target, such as proximity operations for on-
orbit servicing or active debris removal. Due to low mass and power characteristics, monocular vision sensors are an attractive choice for onboard vision-based navigation systems. This work focuses on the problem of utilizing images from a monocular vision sensor for estimation of the target's state relative to the servicer spacecraft. Of special interest is the underlying problem of estimating position and attitude (pose) from a single monocular image, given the knowledge of its 3D model. Motivated by the recent advancements in computer vision and machine learning, this work investigates a learning-based approach that has the potential to enable a new paradigm of robust and accurate onboard navigation systems. A novel framework is proposed for pose initialization and tracking of an uncooperative spacecraft in close-proximity using monocular images and deep learning. An approach based on the use of Convolutional Neural Networks (CNN) is investigated for its scope in enabling reliable on-
orbit operations. With a monocular camera as the sole navigation sensor, the underlying problem of relative pose estimation is tackled with deep learning in CNNs to provide robustness to illumination conditions, as opposed to conventional image processing approaches. The CNNs are trained on synthetic images generated from photorealistic renderings of the target spacecraft and integrated into a navigation loop. The emphasis is put on the robustness of such a CNN-based navigation loop, as CNN models are susceptible to learning implicit data distributions that generalize poorly to reality when trained on synthetic data. The central analysis in this work focuses on the European Space Agency’s decommissioned Envisat spacecraft as the target, due to its potential debris generation risk. To that extent, a navigation framework is designed that uses two CNNs- a single-shot object detection network and a high-resolution keypoint detection network, to detect predefined surface keypoints on the target spacecraft. A heatmap representation is used for keypoint detection that provides contextual information per detection and allows indirect quantification of the observation uncertainty. The detected keypoint coordinates and the associated covariances are then used to solve the Perspective-n-Points (PnP) problem using a Maximum Likelihood PnP (MLPnP) solver. The MLPnP solver provides a pose estimate and the associated uncertainty, which is used by a loosely-coupled Multiplicative Extended Kalman Filter to track the state of the target spacecraft. The pose estimation pipeline in the first two stages is benchmarked and validated on the Spacecraft Pose Estimation Dataset (it{SPEED}) from the Stanford Rendezvous Laboratory, containing images of the Tango spacecraft from the PRISMA mission. Subsequently, the framework is evaluated for the Envisat target case, using…
Advisors/Committee Members: Menicucci, A. (mentor), Pasqualetto Cassinis, L. (graduation committee), Delft University of Technology (degree granting institution).
Subjects/Keywords: Convolutional Neural Networks (CNNs); Machine Learning; Proximity Operations; Navigation; Robust Navigation; Estimation; Space Debris; on-orbit servicing; Monocular Vision; Computer Vision; Pose estimation; Filtering
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APA ·
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APA (6th Edition):
Barad, K. R. (. (2020). Robust Navigation Framework for Proximity Operations around Uncooperative Spacecraft: A monocular vision-based navigation approach using deep learning. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:6dbf6f1d-b41b-42c1-ad78-619a6c6cf071
Chicago Manual of Style (16th Edition):
Barad, K R (author). “Robust Navigation Framework for Proximity Operations around Uncooperative Spacecraft: A monocular vision-based navigation approach using deep learning.” 2020. Masters Thesis, Delft University of Technology. Accessed March 07, 2021.
http://resolver.tudelft.nl/uuid:6dbf6f1d-b41b-42c1-ad78-619a6c6cf071.
MLA Handbook (7th Edition):
Barad, K R (author). “Robust Navigation Framework for Proximity Operations around Uncooperative Spacecraft: A monocular vision-based navigation approach using deep learning.” 2020. Web. 07 Mar 2021.
Vancouver:
Barad KR(. Robust Navigation Framework for Proximity Operations around Uncooperative Spacecraft: A monocular vision-based navigation approach using deep learning. [Internet] [Masters thesis]. Delft University of Technology; 2020. [cited 2021 Mar 07].
Available from: http://resolver.tudelft.nl/uuid:6dbf6f1d-b41b-42c1-ad78-619a6c6cf071.
Council of Science Editors:
Barad KR(. Robust Navigation Framework for Proximity Operations around Uncooperative Spacecraft: A monocular vision-based navigation approach using deep learning. [Masters Thesis]. Delft University of Technology; 2020. Available from: http://resolver.tudelft.nl/uuid:6dbf6f1d-b41b-42c1-ad78-619a6c6cf071
York University
12.
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 07, 2021.
http://hdl.handle.net/10315/33406.
MLA Handbook (7th Edition):
Dong, Gangqi. “Autonomous Visual Servo Robotic Capture of Non-cooperative Target.” 2017. Web. 07 Mar 2021.
Vancouver:
Dong G. Autonomous Visual Servo Robotic Capture of Non-cooperative Target. [Internet] [Doctoral dissertation]. York University; 2017. [cited 2021 Mar 07].
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
13.
Dutta, Atri.
Optimal cooperative and non-cooperative peer-to-peer maneuvers for refueling satellites in circular constellations.
Degree: PhD, Aerospace Engineering, 2009, Georgia Tech
URL: http://hdl.handle.net/1853/28082
► On-orbit servicing (OOS) of space systems provides immense benefits by extending their lifetime, by reducing overall cost of space operations, and by adding flexibility to…
(more)
▼ On-
orbit servicing (OOS) of space systems provides immense benefits by extending their lifetime, by reducing overall cost of space operations, and by adding flexibility to space missions. Refueling is an important aspect of OOS operations. The problem of determining the optimal strategy of refueling multiple satellites in a constellation, by expending minimum fuel during the orbital transfers, is challenging, and requires the solution of a large-scale optimization problem. The conventional notion about a refueling mission is to have a service vehicle visit all fuel-deficient satellites one by one and deliver fuel to them. A recently emerged concept, known as the peer-to-peer (P2P) strategy, is a distributed method of replenishing satellites with fuel. P2P strategy is an integral part of a mixed refueling strategy, in which a service vehicle delivers fuel to part (perhaps half) of the satellites in the constellation, and these satellites, in turn, engage in P2P maneuvers with the remaining satellites. During a P2P maneuver between a fuel-sufficient and a fuel-deficient satellite, one of them performs an orbital transfer to rendezvous with the other, exchanges fuel, and then returns back to its original orbital position. In terms of fuel expended during the refueling process, the mixed strategy outperforms the single service vehicle strategy, particularly with increasing number of satellites in the constellation. This dissertation looks at the problem of P2P refueling problem and proposes new extensions like the Cooperative P2P and Egalitarian P2P strategies. It presents an overview of the methodologies developed to determine the optimal set of orbital transfers required for cooperative and non-cooperative P2P refueling strategies. Results demonstrate that the proposed strategies help in reducing fuel expenditure during the refueling process.
Advisors/Committee Members: Panagiotis Tsiotras (Committee Chair), Eric Feron (Committee Member), Joseph Saleh (Committee Member), Ryan Russell (Committee Member), William Cook (Committee Member).
Subjects/Keywords: Constellation graphs; Three-index assignment problem; NP-hardness; Network flows; Cooperative rendezvous; On-orbit servicing; Satellite refueling; Peer-to-peer refueling; Lambert's problem; Hohmann transfers; Phasing maneuvers; Artificial satellites Refueling; Artificial satellites Orbits; Artificial satellites Maintenance and repair; Mathematical optimization
…for CE-P2P Lower Bound Calculation. . . . . . . . . 158
62
On-Orbit Servicing… …170
xiii
SUMMARY
On-orbit servicing (OOS) of space systems provides immense… …on-orbit servicing, and refueling in particular. Capabilities to repair, upgrade, and… …when on-orbit servicing has
proven to be beneficial. The first on-orbit servicing mission can… …servicing in space. DARPA’s
Orbital Express program demonstrated several key on-orbit servicing…
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APA ·
Chicago ·
MLA ·
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Manager
APA (6th Edition):
Dutta, A. (2009). Optimal cooperative and non-cooperative peer-to-peer maneuvers for refueling satellites in circular constellations. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/28082
Chicago Manual of Style (16th Edition):
Dutta, Atri. “Optimal cooperative and non-cooperative peer-to-peer maneuvers for refueling satellites in circular constellations.” 2009. Doctoral Dissertation, Georgia Tech. Accessed March 07, 2021.
http://hdl.handle.net/1853/28082.
MLA Handbook (7th Edition):
Dutta, Atri. “Optimal cooperative and non-cooperative peer-to-peer maneuvers for refueling satellites in circular constellations.” 2009. Web. 07 Mar 2021.
Vancouver:
Dutta A. Optimal cooperative and non-cooperative peer-to-peer maneuvers for refueling satellites in circular constellations. [Internet] [Doctoral dissertation]. Georgia Tech; 2009. [cited 2021 Mar 07].
Available from: http://hdl.handle.net/1853/28082.
Council of Science Editors:
Dutta A. Optimal cooperative and non-cooperative peer-to-peer maneuvers for refueling satellites in circular constellations. [Doctoral Dissertation]. Georgia Tech; 2009. Available from: http://hdl.handle.net/1853/28082
14.
Risi, Benjamin.
Propulsion System Development for the CanX-4 and CanX-5 Dual Nanosatellite Formation Flying Mission.
Degree: 2014, University of Toronto
URL: http://hdl.handle.net/1807/65601
► The Canadian Nanosatellite Advanced Propulsion System is a liquefied cold-gas thruster system that provides propulsive capabilities to CanX-4/-5, the Canadian Advanced Nanospace eXperiment 4 and…
(more)
▼ The Canadian Nanosatellite Advanced Propulsion System is a liquefied cold-gas thruster system that provides propulsive capabilities to CanX-4/-5, the Canadian Advanced Nanospace eXperiment 4 and 5. With a launch date of early 2014, CanX-4/-5's primary mission objective is to demonstrate precise autonomous formation flight of nanosatellites in low Earth orbit. The high-level CanX-4/-5 mission and system architecture is described. The final design and assembly of the propulsion system is presented along with the lessons learned. A high-level test plan provides a roadmap of the testing required to qualify the propulsion system for flight. The setup and execution of these tests, as well as the analyses of the results found therein, are discussed in detail.
MAST
Advisors/Committee Members: Zee, Robert, Aerospace Science and Engineering.
Subjects/Keywords: aerospace; microsatellite; nanosatellite; propulsion; formation flying; canx4; canx5; canx-4; canx-5; canx-4/-5; SFL; UTIAS; cold-gas thruster; satellite; CNAPS; NANOPS; nano; sulfur hexafluoride; SF6; vibration testing; spacecraft environmental testing; propulsion testing; low earth orbit; canx2; canx-2; station keeping; orbit maneuver; orbital station-keeping; liquefied cold-gas propulsion; micropropulsion; engineering; space; canadian; space flight laboratory; canadian advanced nanospace experiment; PSLV; micro-propulsion; thruster; interferometry; ground moving target indicator; on-orbit servicing and inspection; 0538
…not limited to: high resolution interferometry, on-orbit servicing and inspection, Ground… …Propulsion System
On-Board Computer
Projected Circular Orbit
Polyetheretherketone
Polar Satellite… …They will be the first on-orbit platform to demonstrate nanosatellite
formation flight with… …liquefied cold-gas propulsion system used for on-orbit manoeuvres (Figure 2.5). This… …expected on-orbit. Final flight configuration has one CNAPS
unit filled to 237 grams with the…
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Manager
APA (6th Edition):
Risi, B. (2014). Propulsion System Development for the CanX-4 and CanX-5 Dual Nanosatellite Formation Flying Mission. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/65601
Chicago Manual of Style (16th Edition):
Risi, Benjamin. “Propulsion System Development for the CanX-4 and CanX-5 Dual Nanosatellite Formation Flying Mission.” 2014. Masters Thesis, University of Toronto. Accessed March 07, 2021.
http://hdl.handle.net/1807/65601.
MLA Handbook (7th Edition):
Risi, Benjamin. “Propulsion System Development for the CanX-4 and CanX-5 Dual Nanosatellite Formation Flying Mission.” 2014. Web. 07 Mar 2021.
Vancouver:
Risi B. Propulsion System Development for the CanX-4 and CanX-5 Dual Nanosatellite Formation Flying Mission. [Internet] [Masters thesis]. University of Toronto; 2014. [cited 2021 Mar 07].
Available from: http://hdl.handle.net/1807/65601.
Council of Science Editors:
Risi B. Propulsion System Development for the CanX-4 and CanX-5 Dual Nanosatellite Formation Flying Mission. [Masters Thesis]. University of Toronto; 2014. Available from: http://hdl.handle.net/1807/65601
. 
Open Access Theses and Dissertations
