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York University
1.
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
York University
2.
Agarwal, Anirudh.
Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages.
Degree: MSc -MS, Earth & Space Science, 2019, York University
URL: http://hdl.handle.net/10315/35911
► This study designs and analyzes a new type of controller that helps improve the performance of single axis attitude control of flexible appendages attached to…
(more)
▼ This study designs and analyzes a new type of controller that helps improve the performance of single axis attitude control of flexible appendages attached to a rigid spacecraft. Conventionally, PID with position feedback was used to control single axis attitude manoeuvre of flexible appendages on a spacecraft but designing a PID to control a higher order system is a limited strategy. Also, PID controllers are inherently unstable for third order systems and higher as will be demonstrated later. Thus, acceleration feedback is included in the design to demonstrate a more stable way of designing controllers for these systems and it is called PDA (Proportional Derivative Acceleration) controller. The controller is first designed using a root locus method and then applied to a simulated third order system om MATLAB. Then a higher order system model (rigid body with flexible appendage) is created on SIMULINK and the controller is applied to it. Finally, an experiment is performed and demonstrated to show the practical implementation of the control design.
Advisors/Committee Members: Zhu, George (advisor).
Subjects/Keywords: Aerospace engineering; Spacecraft dynamics; Control systems; Acceleration feedback; PIDA; PID; Attitude control; Classical control; Spacecraft attitude control; Single axis attitude control
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APA (6th Edition):
Agarwal, A. (2019). Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages. (Masters Thesis). York University. Retrieved from http://hdl.handle.net/10315/35911
Chicago Manual of Style (16th Edition):
Agarwal, Anirudh. “Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages.” 2019. Masters Thesis, York University. Accessed March 01, 2021.
http://hdl.handle.net/10315/35911.
MLA Handbook (7th Edition):
Agarwal, Anirudh. “Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages.” 2019. Web. 01 Mar 2021.
Vancouver:
Agarwal A. Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages. [Internet] [Masters thesis]. York University; 2019. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/10315/35911.
Council of Science Editors:
Agarwal A. Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages. [Masters Thesis]. York University; 2019. Available from: http://hdl.handle.net/10315/35911
York University
3.
Li, Peng.
Dynamics and Control of Spacecraft Rendezvous By Nonlinear Model Predictive Control.
Degree: PhD, Earth & Space Science, 2019, York University
URL: http://hdl.handle.net/10315/35890
► This doctoral research investigates the fundamental problems in the dynamics and control of spacecraft rendezvous with a non-cooperative tumbling target. New control schemes based on…
(more)
▼ This doctoral research investigates the fundamental problems in the dynamics and control of spacecraft rendezvous with a non-cooperative tumbling target. New control schemes based on nonlinear model predictive control method have been developed and validated experimentally by ground-based air-bearing satellite simulators. It is focused on the autonomous rendezvous for a chaser spacecraft to approach the target in the final rendezvous stage. Two challenges have been identified and investigated in this stage: the mathematical modeling of the targets tumbling motion and the constrained control scheme that is solvable in an on-line manner. First, the mathematical description of the tumbling motion of the target spacecraft is proposed for the chaser spacecraft to rendezvous with the target. In the meantime, the practical constraints are formulated to ensure the safety and avoid collision during the final approaching stage. This set of constraints are integrated into the trajectory planning problem as a constrained optimization problem. Second, the nonlinear model predictive control is proposed to generate the feedback control commands by iteratively solving an open-loop discrete-time nonlinear optimal control problem at each sampling instant. The proposed control scheme is validated both theoretically and experimentally by a custom-built spacecraft simulator floating on a high-accuracy granite table. Computer software for electronic hardware for the spacecraft simulator and for the controller is designed and developed in house. The experimental results demonstrate the effectiveness and advantages of the proposed nonlinear model predictive control scheme in a hardware-in-the-loop environment. Furthermore, a preliminary outlook is given for future extension of the spacecraft simulator with consideration of the robotic arms.
Advisors/Committee Members: Zhu, George (advisor).
Subjects/Keywords: Aerospace engineering; Spacecraft Rendezvous; Proximity Operation; Autonomous Rendezvous; Nonlinear Model Predictive Control
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APA (6th Edition):
Li, P. (2019). Dynamics and Control of Spacecraft Rendezvous By Nonlinear Model Predictive Control. (Doctoral Dissertation). York University. Retrieved from http://hdl.handle.net/10315/35890
Chicago Manual of Style (16th Edition):
Li, Peng. “Dynamics and Control of Spacecraft Rendezvous By Nonlinear Model Predictive Control.” 2019. Doctoral Dissertation, York University. Accessed March 01, 2021.
http://hdl.handle.net/10315/35890.
MLA Handbook (7th Edition):
Li, Peng. “Dynamics and Control of Spacecraft Rendezvous By Nonlinear Model Predictive Control.” 2019. Web. 01 Mar 2021.
Vancouver:
Li P. Dynamics and Control of Spacecraft Rendezvous By Nonlinear Model Predictive Control. [Internet] [Doctoral dissertation]. York University; 2019. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/10315/35890.
Council of Science Editors:
Li P. Dynamics and Control of Spacecraft Rendezvous By Nonlinear Model Predictive Control. [Doctoral Dissertation]. York University; 2019. Available from: http://hdl.handle.net/10315/35890
York University
4.
Sidhu, Gurtej Singh.
Fabrication and Characterization of Self-Sensing Nanocomposite - "Smart Skin".
Degree: MASc - Master of Applied Science, Mechanical Engineering, 2019, York University
URL: http://hdl.handle.net/10315/35896
► This study characterizes the behaviour and properties of self-sensing polymer nanocomposite. Specifically, we studied the Electrical, Mechanical and Piezoresistive properties. Electrically the material is conductive…
(more)
▼ This study characterizes the behaviour and properties of self-sensing polymer nanocomposite. Specifically, we studied the Electrical, Mechanical and Piezoresistive properties. Electrically the material is conductive with a linear response to change in applied strain. Mechanically the material behaves like a polymer, whose Youngs Modulus increases with added MWCNT. From a piezoelectricalperspective this material is stable and can maintain its electrical and mechanical behaviour for 50 cycles of repeated loading at 2mm/min. When producing thin sheets of nanocomposite, the effects of material thickness on piezoresistivity are negligible.
The nanocomposite is fabricated by mechanically mixing multiwalled carbon nanotubes (MWCNT) with 2-part polydimethylsiloxane (PDMS). The randomly aligned MWCNT-PDMS is fabricated for two configurations, Type I and Type II. In these configurations, Type I is read longitudinal to force using 4-Probe method and Type II is read perpendicularly with 2-Probe method. The strain is applied to Type I in tension and Type II in compression. The Type I characterizes the bulk conductivity for varying wt% of MWCNT. The Type II looks at the sheet conductivity for varying thickness.
Advisors/Committee Members: Zhu, George (advisor).
Subjects/Keywords: Nanotechnology; self sensing; smart material; nanocomposite; strain sensor; smart sensor; multifunctional; piezoresistive sensor; carbon nanotubes; Polydimethylsiloxane; PDMS; MWCNT
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APA (6th Edition):
Sidhu, G. S. (2019). Fabrication and Characterization of Self-Sensing Nanocomposite - "Smart Skin". (Masters Thesis). York University. Retrieved from http://hdl.handle.net/10315/35896
Chicago Manual of Style (16th Edition):
Sidhu, Gurtej Singh. “Fabrication and Characterization of Self-Sensing Nanocomposite - "Smart Skin".” 2019. Masters Thesis, York University. Accessed March 01, 2021.
http://hdl.handle.net/10315/35896.
MLA Handbook (7th Edition):
Sidhu, Gurtej Singh. “Fabrication and Characterization of Self-Sensing Nanocomposite - "Smart Skin".” 2019. Web. 01 Mar 2021.
Vancouver:
Sidhu GS. Fabrication and Characterization of Self-Sensing Nanocomposite - "Smart Skin". [Internet] [Masters thesis]. York University; 2019. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/10315/35896.
Council of Science Editors:
Sidhu GS. Fabrication and Characterization of Self-Sensing Nanocomposite - "Smart Skin". [Masters Thesis]. York University; 2019. Available from: http://hdl.handle.net/10315/35896
York University
5.
Li, Gangqiang.
Multibody Dynamics and Control of Tethered Spacecraft Systems.
Degree: PhD, Earth & Space Science, 2019, York University
URL: https://yorkspace.library.yorku.ca/xmlui/handle/10315/36739
► This doctoral research conducts high-fidelity multiphysics modeling for tethered spacecraft systems, such as electrodynamic tether systems, electric solar wind sail systems, and tether transportation systems…
(more)
▼ This doctoral research conducts high-fidelity multiphysics modeling for tethered spacecraft systems, such as electrodynamic tether systems, electric solar wind sail systems, and tether transportation systems with climbers. Two models are developed based on nodal position finite element method. The first model deals with the tethered spacecraft system with fixed length tether, while the second model deals with the tethered spacecraft system with variable tether length using an arbitrary Lagrangian-Eulerian description.
First, the nodal position finite element method is applied to model the orbital motion of tethered spacecraft systems with fixed tether length over a prolonged period. A Symplectic integration scheme is employed to attenuate the accumulation of error in the numerical analysis due to the long-term integration for tethered spacecraft systems, such as the space debris deorbit by electrodynamic tethers. A high fidelity multiphysics model is developed for electrodynamic tether systems by considering elastic, thermal, and electrical coupling effects of the tether. Most importantly, the calculation of electron collection by the electrodynamic tether is coupled with the tether libration and flexible deformation, where the orbital motion limited theory for electron collection is discretized simultaneously by the same finite element mesh used for the elastodynamic analysis of tether. The model is then used to investigate dynamics and libration stability of bare electrodynamic tethers in deorbiting end-of-mission spacecraft.
Second, the model of tethered spacecraft system with fixed tether length is extended for the modeling of electric solar wind sail systems. The coupling effect of orbital and self-spinning motions of electric solar wind sail systems is investigated together with the interaction between the axial/transverse elastic motion of tether and Coulomb force. A modified throttling control algorithm is implemented in the finite element scheme to control the attitude motion of electric solar wind sail systems through the electric voltage modulation of main tethers.
Third, the model of tethered spacecraft with variable tether length is applied to handle the tether length variation in tether transportation systems. The tether length variation results from the climber moving along tether and deployment and retrieval of tether at end spacecraft. The dynamic behavior of tether transportation systems with single or multiple climbers in characterized and the effectiveness of libration suppression scheme is tested by the high-fidelity model.
Advisors/Committee Members: Zhu, George Z. H. (advisor).
Subjects/Keywords: Computer engineering; Finite element method; Tethered spacecraft systems; Control; Dynamics; Electric solar wind sail; Tether transportation system; Partial space elevator; Space elevator; Electrodynamic tether systems
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APA ·
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Manager
APA (6th Edition):
Li, G. (2019). Multibody Dynamics and Control of Tethered Spacecraft Systems. (Doctoral Dissertation). York University. Retrieved from https://yorkspace.library.yorku.ca/xmlui/handle/10315/36739
Chicago Manual of Style (16th Edition):
Li, Gangqiang. “Multibody Dynamics and Control of Tethered Spacecraft Systems.” 2019. Doctoral Dissertation, York University. Accessed March 01, 2021.
https://yorkspace.library.yorku.ca/xmlui/handle/10315/36739.
MLA Handbook (7th Edition):
Li, Gangqiang. “Multibody Dynamics and Control of Tethered Spacecraft Systems.” 2019. Web. 01 Mar 2021.
Vancouver:
Li G. Multibody Dynamics and Control of Tethered Spacecraft Systems. [Internet] [Doctoral dissertation]. York University; 2019. [cited 2021 Mar 01].
Available from: https://yorkspace.library.yorku.ca/xmlui/handle/10315/36739.
Council of Science Editors:
Li G. Multibody Dynamics and Control of Tethered Spacecraft Systems. [Doctoral Dissertation]. York University; 2019. Available from: https://yorkspace.library.yorku.ca/xmlui/handle/10315/36739
York University
6.
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 01, 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. 01 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 01].
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
York University
7.
Cookson, Joshua Jonathan.
Experimental Investigation of Spacecraft Rendezvous and Docking by Development of a 3 Degree of Freedom Satellite Simulator Testbed.
Degree: MSc -MS, Earth & Space Science, 2020, York University
URL: https://yorkspace.library.yorku.ca/xmlui/handle/10315/37388
► This thesis developed a 3 degree of freedom air bearing satellite simulator testbed. The major components of this testbed are a 2-meter by 4-meter granite…
(more)
▼ This thesis developed a 3 degree of freedom air bearing satellite simulator testbed. The major components of this testbed are a 2-meter by 4-meter granite table, a pair of satellite simulators, and a passive infrared marker array. The goal of this implementation was to achieve soft docking between 2 satellite simulators while relying only on hardware and systems onboard the satellite simulator. The satellite simulators make use of compressed air stored onboard in tanks to supply the air bearing and gas thrusters. The air bearing system provides a thin cushion of air for the satellite simulator to float on, removing surface contact and friction between the satellite simulator and the granite table. This produces a 3 degree of freedom system which is effectively free of the effects of gravity. The infrared marker array is used to provide reference points similar to stars to enable an onboard positioning system using a single observer. The experimental results obtained here demonstrate the successful implementation of this testbed.
Advisors/Committee Members: Zhu, George Z. H. (advisor).
Subjects/Keywords: Aerospace engineering; Planar; Air bearing; Satellite; Test bed; 3DOF; Spacecraft; Dynamics; Docking; Satellite simulator
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APA ·
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APA (6th Edition):
Cookson, J. J. (2020). Experimental Investigation of Spacecraft Rendezvous and Docking by Development of a 3 Degree of Freedom Satellite Simulator Testbed. (Masters Thesis). York University. Retrieved from https://yorkspace.library.yorku.ca/xmlui/handle/10315/37388
Chicago Manual of Style (16th Edition):
Cookson, Joshua Jonathan. “Experimental Investigation of Spacecraft Rendezvous and Docking by Development of a 3 Degree of Freedom Satellite Simulator Testbed.” 2020. Masters Thesis, York University. Accessed March 01, 2021.
https://yorkspace.library.yorku.ca/xmlui/handle/10315/37388.
MLA Handbook (7th Edition):
Cookson, Joshua Jonathan. “Experimental Investigation of Spacecraft Rendezvous and Docking by Development of a 3 Degree of Freedom Satellite Simulator Testbed.” 2020. Web. 01 Mar 2021.
Vancouver:
Cookson JJ. Experimental Investigation of Spacecraft Rendezvous and Docking by Development of a 3 Degree of Freedom Satellite Simulator Testbed. [Internet] [Masters thesis]. York University; 2020. [cited 2021 Mar 01].
Available from: https://yorkspace.library.yorku.ca/xmlui/handle/10315/37388.
Council of Science Editors:
Cookson JJ. Experimental Investigation of Spacecraft Rendezvous and Docking by Development of a 3 Degree of Freedom Satellite Simulator Testbed. [Masters Thesis]. York University; 2020. Available from: https://yorkspace.library.yorku.ca/xmlui/handle/10315/37388
York University
8.
Li, Gangqiang.
Multibody Dynamics and Control of Tethered Spacecraft Systems.
Degree: PhD, Earth & Space Science, 2019, York University
URL: http://hdl.handle.net/10315/36739
► This doctoral research conducts high-fidelity multiphysics modeling for tethered spacecraft systems, such as electrodynamic tether systems, electric solar wind sail systems, and tether transportation systems…
(more)
▼ This doctoral research conducts high-fidelity multiphysics modeling for tethered spacecraft systems, such as electrodynamic tether systems, electric solar wind sail systems, and tether transportation systems with climbers. Two models are developed based on nodal position finite element method. The first model deals with the tethered spacecraft system with fixed length tether, while the second model deals with the tethered spacecraft system with variable tether length using an arbitrary Lagrangian-Eulerian description.
First, the nodal position finite element method is applied to model the orbital motion of tethered spacecraft systems with fixed tether length over a prolonged period. A Symplectic integration scheme is employed to attenuate the accumulation of error in the numerical analysis due to the long-term integration for tethered spacecraft systems, such as the space debris deorbit by electrodynamic tethers. A high fidelity multiphysics model is developed for electrodynamic tether systems by considering elastic, thermal, and electrical coupling effects of the tether. Most importantly, the calculation of electron collection by the electrodynamic tether is coupled with the tether libration and flexible deformation, where the orbital motion limited theory for electron collection is discretized simultaneously by the same finite element mesh used for the elastodynamic analysis of tether. The model is then used to investigate dynamics and libration stability of bare electrodynamic tethers in deorbiting end-of-mission spacecraft.
Second, the model of tethered spacecraft system with fixed tether length is extended for the modeling of electric solar wind sail systems. The coupling effect of orbital and self-spinning motions of electric solar wind sail systems is investigated together with the interaction between the axial/transverse elastic motion of tether and Coulomb force. A modified throttling control algorithm is implemented in the finite element scheme to control the attitude motion of electric solar wind sail systems through the electric voltage modulation of main tethers.
Third, the model of tethered spacecraft with variable tether length is applied to handle the tether length variation in tether transportation systems. The tether length variation results from the climber moving along tether and deployment and retrieval of tether at end spacecraft. The dynamic behavior of tether transportation systems with single or multiple climbers in characterized and the effectiveness of libration suppression scheme is tested by the high-fidelity model.
Advisors/Committee Members: Zhu, George Z. H. (advisor).
Subjects/Keywords: Computer engineering; Finite element method; Tethered spacecraft systems; Control; Dynamics; Electric solar wind sail; Tether transportation system; Partial space elevator; Space elevator; Electrodynamic tether systems
Record Details
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Record Details
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APA ·
Chicago ·
MLA ·
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CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Li, G. (2019). Multibody Dynamics and Control of Tethered Spacecraft Systems. (Doctoral Dissertation). York University. Retrieved from http://hdl.handle.net/10315/36739
Chicago Manual of Style (16th Edition):
Li, Gangqiang. “Multibody Dynamics and Control of Tethered Spacecraft Systems.” 2019. Doctoral Dissertation, York University. Accessed March 01, 2021.
http://hdl.handle.net/10315/36739.
MLA Handbook (7th Edition):
Li, Gangqiang. “Multibody Dynamics and Control of Tethered Spacecraft Systems.” 2019. Web. 01 Mar 2021.
Vancouver:
Li G. Multibody Dynamics and Control of Tethered Spacecraft Systems. [Internet] [Doctoral dissertation]. York University; 2019. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/10315/36739.
Council of Science Editors:
Li G. Multibody Dynamics and Control of Tethered Spacecraft Systems. [Doctoral Dissertation]. York University; 2019. Available from: http://hdl.handle.net/10315/36739
York University
9.
Furtal, Jude Joseph.
Structural Design and Finite Element Analysis of DESCENT CubeSats.
Degree: MASc - Master of Applied Science, Mechanical Engineering, 2020, York University
URL: https://yorkspace.library.yorku.ca/xmlui/handle/10315/37381
► This thesis outlines the development of a two custom CubeSat structures used for the DESCENT mission. DESCENT aims to test the feasibility of Electrodynamic Tethers…
(more)
▼ This thesis outlines the development of a two custom CubeSat structures used for the DESCENT mission. DESCENT aims to test the feasibility of Electrodynamic Tethers (EDT) to deorbit spacecrafts. The payloads and bus components require DESCENT to have its own custom structures. The design is initially completed using a Computer Aided Design (CAD) software to create a solid model that fulfills the requirements stated by the launch provider. Next, a Computer Aided Engineering (CAE) tool is then used to create a Finite Element Model (FEM) of the satellites. The FEM is then used to run a Finite Element Analysis (FEA) to validate the structural integrity of the satellites in the launch and thermal environments. After the structure had been validated, technical drawings of components were completed, and the parts were manufactured. Finally, the manufactured parts were assembled together, and a fit check was completed to confirm the satellites outer dimensions.
Advisors/Committee Members: Zhu, George Z. H. (advisor).
Subjects/Keywords: Aerospace engineering; Satellites; Cubesats; Finite element analysis; Structural design; Mechanical design
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APA (6th Edition):
Furtal, J. J. (2020). Structural Design and Finite Element Analysis of DESCENT CubeSats. (Masters Thesis). York University. Retrieved from https://yorkspace.library.yorku.ca/xmlui/handle/10315/37381
Chicago Manual of Style (16th Edition):
Furtal, Jude Joseph. “Structural Design and Finite Element Analysis of DESCENT CubeSats.” 2020. Masters Thesis, York University. Accessed March 01, 2021.
https://yorkspace.library.yorku.ca/xmlui/handle/10315/37381.
MLA Handbook (7th Edition):
Furtal, Jude Joseph. “Structural Design and Finite Element Analysis of DESCENT CubeSats.” 2020. Web. 01 Mar 2021.
Vancouver:
Furtal JJ. Structural Design and Finite Element Analysis of DESCENT CubeSats. [Internet] [Masters thesis]. York University; 2020. [cited 2021 Mar 01].
Available from: https://yorkspace.library.yorku.ca/xmlui/handle/10315/37381.
Council of Science Editors:
Furtal JJ. Structural Design and Finite Element Analysis of DESCENT CubeSats. [Masters Thesis]. York University; 2020. Available from: https://yorkspace.library.yorku.ca/xmlui/handle/10315/37381
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Open Access Theses and Dissertations