subject:(Orbital Mechanics)

Penn State University

1. Kuppa, Koundinya. Long-term Orbit Propagation Using Symplectic Integration Algorithms.

Degree: 2016, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/29463

► Understanding the evolution of satellite orbits in the long-term is of great importance in astrodynamics. In order to achieve this, accurate propagation of the orbital… (more)

Subjects/Keywords: astrodynamics; orbital mechanics; symplectic integration; numerical integration; orbit propagation; spaceflight mechanics

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APA (6^th Edition):

Kuppa, K. (2016). Long-term Orbit Propagation Using Symplectic Integration Algorithms. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/29463

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

Chicago Manual of Style (16^th Edition):

Kuppa, Koundinya. “Long-term Orbit Propagation Using Symplectic Integration Algorithms.” 2016. Thesis, Penn State University. Accessed January 21, 2021. https://submit-etda.libraries.psu.edu/catalog/29463.

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

MLA Handbook (7^th Edition):

Kuppa, Koundinya. “Long-term Orbit Propagation Using Symplectic Integration Algorithms.” 2016. Web. 21 Jan 2021.

Vancouver:

Kuppa K. Long-term Orbit Propagation Using Symplectic Integration Algorithms. [Internet] [Thesis]. Penn State University; 2016. [cited 2021 Jan 21]. Available from: https://submit-etda.libraries.psu.edu/catalog/29463.

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

Council of Science Editors:

Kuppa K. Long-term Orbit Propagation Using Symplectic Integration Algorithms. [Thesis]. Penn State University; 2016. Available from: https://submit-etda.libraries.psu.edu/catalog/29463

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

University of Arizona

2. Burnett, Ethan Ryan. Relative Orbital Motion Dynamical Models for Orbits about Nonspherical Bodies .

Degree: 2018, University of Arizona

URL: http://hdl.handle.net/10150/628098

► Relative orbital motion dynamical models are presented and discussed. Two types of models are primarily discussed in this work: a linear relative motion model accounting… (more)

Subjects/Keywords: aerospace; asteroids; astrodynamics; celestial mechanics; orbital mechanics; spacecraft

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APA (6^th Edition):

Burnett, E. R. (2018). Relative Orbital Motion Dynamical Models for Orbits about Nonspherical Bodies . (Masters Thesis). University of Arizona. Retrieved from http://hdl.handle.net/10150/628098

Chicago Manual of Style (16^th Edition):

Burnett, Ethan Ryan. “Relative Orbital Motion Dynamical Models for Orbits about Nonspherical Bodies .” 2018. Masters Thesis, University of Arizona. Accessed January 21, 2021. http://hdl.handle.net/10150/628098.

MLA Handbook (7^th Edition):

Burnett, Ethan Ryan. “Relative Orbital Motion Dynamical Models for Orbits about Nonspherical Bodies .” 2018. Web. 21 Jan 2021.

Vancouver:

Burnett ER. Relative Orbital Motion Dynamical Models for Orbits about Nonspherical Bodies . [Internet] [Masters thesis]. University of Arizona; 2018. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/10150/628098.

Council of Science Editors:

Burnett ER. Relative Orbital Motion Dynamical Models for Orbits about Nonspherical Bodies . [Masters Thesis]. University of Arizona; 2018. Available from: http://hdl.handle.net/10150/628098

Rochester Institute of Technology

3. Dubill, Amber. Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails.

Degree: MS, Mechanical Engineering, 2020, Rochester Institute of Technology

URL: https://scholarworks.rit.edu/theses/10388

► A solar sail making use of the physics of diffracted light enables the transfer of optical to mechanical momentum for in-space propulsion. In this… (more)

Subjects/Keywords: Attitude control; Diffractice; Heliophysics; Orbital mechanics; Solar sailing; Spacecraft

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APA (6^th Edition):

Dubill, A. (2020). Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails. (Masters Thesis). Rochester Institute of Technology. Retrieved from https://scholarworks.rit.edu/theses/10388

Chicago Manual of Style (16^th Edition):

Dubill, Amber. “Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails.” 2020. Masters Thesis, Rochester Institute of Technology. Accessed January 21, 2021. https://scholarworks.rit.edu/theses/10388.

MLA Handbook (7^th Edition):

Dubill, Amber. “Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails.” 2020. Web. 21 Jan 2021.

Vancouver:

Dubill A. Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails. [Internet] [Masters thesis]. Rochester Institute of Technology; 2020. [cited 2021 Jan 21]. Available from: https://scholarworks.rit.edu/theses/10388.

Council of Science Editors:

Dubill A. Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails. [Masters Thesis]. Rochester Institute of Technology; 2020. Available from: https://scholarworks.rit.edu/theses/10388

Delft University of Technology

4. Gondelach, D. (author). A Hodographic-Shaping Method for Low-Thrust Trajectory Design.

Degree: 2012, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:6a4f1673-88b1-4823-b2ef-9d864c84ab11

► The goal of this research was to develop an analytic low-thrust trajectory design method. The term low thrust stems form the fact that current electric… (more)

▼ The goal of this research was to develop an analytic low-thrust trajectory design method. The term low thrust stems form the fact that current electric propulsion systems can only produce low amounts of thrust. Nevertheless, these systems can deliver very high amounts of ?V using little propellant, which makes them very suitable for interplanetary flight. The orbital mechanics regarding low-thrust interplanetary flight were considered and it was found that for first-order design it is acceptable to neglect all perturbing forces with respect to the Sun's gravitational attraction and the (low) thrust force. In addition to that, a look was taken at the characteristics of electric propulsion and feasible thrust (acceleration) levels were obtained. Since only low thrust levels can be achieved by electric propulsion, long periods of thrusting are required to obtain sufficient change in velocity. This continuous thrusting feature of electrically-propelled spacecraft highly complicates the dynamics of such spacecraft. As a consequence, the design and optimization of low-thrust trajectories is very difficult, and therefore preliminary design of such trajectories is very important. Such first-order designs can give a fast overview of all feasible trajectories and can, moreover, be used as an initial guess for more refined trajectory optimization. For generating and optimizing first-order low-thrust trajectories, analytical methods are very suited, since they are very fast and exact. Several analytical low-thrust methods have been developed recently and most of them are shape-based; the trajectory is assumed to have a specific shape which satisfies the boundary conditions and subsequently the thrust profile can be obtained from the dynamics. These shape-based methods are popular for preliminary design, because of their simplicity and ability to obtain feasible trajectories. The currently known shape-based methods were investigated to obtain know-how about their functioning and to find their strengths and weaknesses. It was noticed that regarding the solving of boundary conditions improvements could be made and that most shaping methods lack flexibility. Inspired by the use of velocity hodographs for the computation of non-perturbed transfer orbits, a novel low-thrust trajectory design method was developed based on shaping the velocity of spacecraft during the transfer. For the shaping of the velocity components, velocity functions were used which consist of a sum of simple base functions. These base functions can be integrated analytically, such that the change in position can be obtained analytically. Since the velocity is shaped, the conditions on initial and final velocity can be solved very easily and exactly. In addition, the boundary conditions on position can be solved exactly without the need of iterative computations. Next to the parameters required to satisfy the boundary conditions, extra parameters can be added to make the design and optimization of trajectories more flexible. Two different methods have been… Advisors/Committee Members: Noomen, R. (mentor).

Subjects/Keywords: shape-based method; low-thrust transfer; orbital mechanics

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APA (6^th Edition):

Gondelach, D. (. (2012). A Hodographic-Shaping Method for Low-Thrust Trajectory Design. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:6a4f1673-88b1-4823-b2ef-9d864c84ab11

Chicago Manual of Style (16^th Edition):

Gondelach, D (author). “A Hodographic-Shaping Method for Low-Thrust Trajectory Design.” 2012. Masters Thesis, Delft University of Technology. Accessed January 21, 2021. http://resolver.tudelft.nl/uuid:6a4f1673-88b1-4823-b2ef-9d864c84ab11.

MLA Handbook (7^th Edition):

Gondelach, D (author). “A Hodographic-Shaping Method for Low-Thrust Trajectory Design.” 2012. Web. 21 Jan 2021.

Vancouver:

Gondelach D(. A Hodographic-Shaping Method for Low-Thrust Trajectory Design. [Internet] [Masters thesis]. Delft University of Technology; 2012. [cited 2021 Jan 21]. Available from: http://resolver.tudelft.nl/uuid:6a4f1673-88b1-4823-b2ef-9d864c84ab11.

Council of Science Editors:

Gondelach D(. A Hodographic-Shaping Method for Low-Thrust Trajectory Design. [Masters Thesis]. Delft University of Technology; 2012. Available from: http://resolver.tudelft.nl/uuid:6a4f1673-88b1-4823-b2ef-9d864c84ab11

University of Minnesota

5. Chandramouli, Harini. Effects of a Rogue Star on Earth's Climate.

Degree: PhD, Mathematics, 2020, University of Minnesota

URL: http://hdl.handle.net/11299/216900

► The details of the way in which the Earth orbits the Sun can have profound effects on Earth’s climate. Elements such as the Earth’s tilt… (more)

Subjects/Keywords: Celestial mechanics; Dynamical systems; Geological record; Milankovitch cycles; Orbital elements

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APA (6^th Edition):

Chandramouli, H. (2020). Effects of a Rogue Star on Earth's Climate. (Doctoral Dissertation). University of Minnesota. Retrieved from http://hdl.handle.net/11299/216900

Chicago Manual of Style (16^th Edition):

Chandramouli, Harini. “Effects of a Rogue Star on Earth's Climate.” 2020. Doctoral Dissertation, University of Minnesota. Accessed January 21, 2021. http://hdl.handle.net/11299/216900.

MLA Handbook (7^th Edition):

Chandramouli, Harini. “Effects of a Rogue Star on Earth's Climate.” 2020. Web. 21 Jan 2021.

Vancouver:

Chandramouli H. Effects of a Rogue Star on Earth's Climate. [Internet] [Doctoral dissertation]. University of Minnesota; 2020. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/11299/216900.

Council of Science Editors:

Chandramouli H. Effects of a Rogue Star on Earth's Climate. [Doctoral Dissertation]. University of Minnesota; 2020. Available from: http://hdl.handle.net/11299/216900

Virginia Tech

6. Ojeda Romero, Juan Andre. Dual Satellite Coverage using Particle Swarm Optimization.

Degree: MS, Aerospace Engineering, 2014, Virginia Tech

URL: http://hdl.handle.net/10919/50627

► A dual satellite system in a Low Earth Orbit, LEO, would be beneficial to study the electromagnetic occurrences in the magnetosphere and their contributions to… (more)

Subjects/Keywords: particle swarm optimization; space weather; aurora borealis; orbital mechanics; satellite coverage

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APA (6^th Edition):

Ojeda Romero, J. A. (2014). Dual Satellite Coverage using Particle Swarm Optimization. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/50627

Chicago Manual of Style (16^th Edition):

Ojeda Romero, Juan Andre. “Dual Satellite Coverage using Particle Swarm Optimization.” 2014. Masters Thesis, Virginia Tech. Accessed January 21, 2021. http://hdl.handle.net/10919/50627.

MLA Handbook (7^th Edition):

Ojeda Romero, Juan Andre. “Dual Satellite Coverage using Particle Swarm Optimization.” 2014. Web. 21 Jan 2021.

Vancouver:

Ojeda Romero JA. Dual Satellite Coverage using Particle Swarm Optimization. [Internet] [Masters thesis]. Virginia Tech; 2014. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/10919/50627.

Council of Science Editors:

Ojeda Romero JA. Dual Satellite Coverage using Particle Swarm Optimization. [Masters Thesis]. Virginia Tech; 2014. Available from: http://hdl.handle.net/10919/50627

University of Illinois – Urbana-Champaign

7. De La Mata, Jorge. Optimal strategies for selecting from multiple asteroid interception targets.

Degree: MS, 4048, 2014, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/50647

► The goal of this thesis is to demonstrate the applicability of the discrimination time optimization problem to space systems. The concept is applied to an… (more)

▼ The goal of this thesis is to demonstrate the applicability of the discrimination time optimization problem to space systems. The concept is applied to an asteroid interception problem using low-thrust propulsion and solved through a combination of particle swarm optimization (PSO) and a commercial non-linear programming (NLP) solver SNOPT (Sparse Nonlinear OPTimizer). The problem considers an intercepting vehicle and three bodies of interest, only one of which can be intercepted. The resulting optimal trajectory must maximize the amount of time the vehicle can travel before committing to intercepting one of the three bodies of interest, assuring that all three bodies are available for intercept within a maximum flight time. This time before commitment is called the discrimination time. Practically, an increase in discrimination time provides the decision makers with an opportunity for further deliberation and organization of mission priorities. This can represent additional time to determine which body holds the most scientific value, or which body presents the largest threat to human life or financial assets. The solution method is a two-step process. An approximate solution is found using a metaheursitic method, PSO. The control is modeled as a combination of polynomials to give the best opportunity for convergence to a feasible solution. The solution found by the PSO algorithm is then used to initialize a much more accurate solution method using NLP. The two optimization techniques are applied in series because of the problem complexity. The PSO algorithm is a stochastic process and can therefore not guarantee optimality and struggles to perform with a large set of optimal parameters. NLP solvers can guarantee first or second order optimality, but require initialization and convergence is contingent on the quality of the initial guess. Creating a four phase trajectory solution ad hoc that could reliably serve as an initial guess for the NLP solver is impractical, and allowing the PSO algorithm to solve a fully discrete control time history problem would be impractical. Using the two together takes advantage of the simplicity and speed provided by the PSO algorithm and the ability of the NLP solver to yield high fidelity, optimal solutions. Advisors/Committee Members: Conway, Bruce A. (advisor).

Subjects/Keywords: Astrodynamics; Orbital Mechanics; Optimization; Nonlinear Programming; Space; Aerospace; Optimal trajectories; Controls

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APA (6^th Edition):

De La Mata, J. (2014). Optimal strategies for selecting from multiple asteroid interception targets. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/50647

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

Chicago Manual of Style (16^th Edition):

De La Mata, Jorge. “Optimal strategies for selecting from multiple asteroid interception targets.” 2014. Thesis, University of Illinois – Urbana-Champaign. Accessed January 21, 2021. http://hdl.handle.net/2142/50647.

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

MLA Handbook (7^th Edition):

De La Mata, Jorge. “Optimal strategies for selecting from multiple asteroid interception targets.” 2014. Web. 21 Jan 2021.

Vancouver:

De La Mata J. Optimal strategies for selecting from multiple asteroid interception targets. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2014. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/2142/50647.

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

Council of Science Editors:

De La Mata J. Optimal strategies for selecting from multiple asteroid interception targets. [Thesis]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/50647

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

Virginia Tech

8. Karlgaard, Christopher David. Second-Order Relative Motion Equations.

Degree: MS, Aerospace and Ocean Engineering, 2001, Virginia Tech

URL: http://hdl.handle.net/10919/34025

► This thesis presents an approximate solution of second order relative motion equations. The equations of motion for a Keplerian orbit in spherical coordinates are expanded… (more)

Subjects/Keywords: Orbital Mechanics; Perturbation Methods

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APA (6^th Edition):

Karlgaard, C. D. (2001). Second-Order Relative Motion Equations. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/34025

Chicago Manual of Style (16^th Edition):

Karlgaard, Christopher David. “Second-Order Relative Motion Equations.” 2001. Masters Thesis, Virginia Tech. Accessed January 21, 2021. http://hdl.handle.net/10919/34025.

MLA Handbook (7^th Edition):

Karlgaard, Christopher David. “Second-Order Relative Motion Equations.” 2001. Web. 21 Jan 2021.

Vancouver:

Karlgaard CD. Second-Order Relative Motion Equations. [Internet] [Masters thesis]. Virginia Tech; 2001. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/10919/34025.

Council of Science Editors:

Karlgaard CD. Second-Order Relative Motion Equations. [Masters Thesis]. Virginia Tech; 2001. Available from: http://hdl.handle.net/10919/34025

University of Texas – Austin

9. Pasupathy, Muthukumar. A comparison of range and range-rate based GRACE gravity field solutions.

Degree: MSin Engineering, Aerospace Engineering, 2011, University of Texas – Austin

URL: http://hdl.handle.net/2152/ETD-UT-2011-05-2818

► In the generation of the standard GRACE gravity fields, the K-Band Ranging (KBR) system data is used in its range-rate mode. Because time derivatives attenuate… (more)

Subjects/Keywords: GRACE mission; Range-Rate; Gravitational fields; Orbital mechanics; Earth gravity

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APA (6^th Edition):

Pasupathy, M. (2011). A comparison of range and range-rate based GRACE gravity field solutions. (Masters Thesis). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/ETD-UT-2011-05-2818

Chicago Manual of Style (16^th Edition):

Pasupathy, Muthukumar. “A comparison of range and range-rate based GRACE gravity field solutions.” 2011. Masters Thesis, University of Texas – Austin. Accessed January 21, 2021. http://hdl.handle.net/2152/ETD-UT-2011-05-2818.

MLA Handbook (7^th Edition):

Pasupathy, Muthukumar. “A comparison of range and range-rate based GRACE gravity field solutions.” 2011. Web. 21 Jan 2021.

Vancouver:

Pasupathy M. A comparison of range and range-rate based GRACE gravity field solutions. [Internet] [Masters thesis]. University of Texas – Austin; 2011. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/2152/ETD-UT-2011-05-2818.

Council of Science Editors:

Pasupathy M. A comparison of range and range-rate based GRACE gravity field solutions. [Masters Thesis]. University of Texas – Austin; 2011. Available from: http://hdl.handle.net/2152/ETD-UT-2011-05-2818

Ryerson University

10. Frias, Alexander. Modeling And Control Of Spacecraft Systems With Coupled Orbital And Attitude Dynamics.

Degree: 2012, Ryerson University

URL: https://digital.library.ryerson.ca/islandora/object/RULA%3A1610

► Spacecraft formation flying with coupled orbital-attitude dynamics is one of the most intriguing topics in the field of astronautics. Orbital-attitude coupling is induced when a… (more)

▼ Spacecraft formation flying with coupled orbital-attitude dynamics is one of the most intriguing topics in the field of astronautics. Orbital-attitude coupling is induced when a non-symmetrical spacecraft in orbit is disturbed by means of active maneuvering or by external disturbances. Direct contributing factors to the coupled dynamics include the orbital radius, the gravitational parameter and the orbital angular velocity. Disturbance due to coupling is inherently weak in nature (in the order of magnitudes of 10-13 Newtons) for Earth orbit, which majority of spacecraft attitude-orbital control system (AOCS) can easily overcome or can be eliminated by means of system dynamics linearization. For very large spacecraft that have very high moment of inertia, coupled dynamics can impose strong nonlinear disturbance and can affect orbital trajectory. Numerical simulations of the coupled dynamics for a rigid-body single spacecraft system, a dumbbell spacecraft system and a multiple spacecraft formation flying system are conducted for Earth and asteroid 4 Vesta orbits. Simulation results suggest that dumbbell spacecraft systems are the most severely affected by the orbital-attitude coupling due to the connecting tether. Nonlinear coupled orbital-attitude equations of motion are fully developed and are used to formulate a nonlinear controller using feedback linearization. Feedback linearization control method is perfect for this system because the spacecraft’s nonlinear coupled dynamics is preserved and not approximated. The controller is validated by numerical simulations as well as implemented in a hardware-in-the-loop experiment using the Ryerson University’s Satellite Airbed Formation Experiment. For asteroid-related missions, orbital-attitude coupling can be several magnitudes times larger than the coupling experienced for Earth orbit depending on the properties of the asteroid and thus in turn, can severely affect the performance of the spacecraft control system. Advisors/Committee Members: Ryerson University (Degree grantor).

Subjects/Keywords: Space vehicles – Design and construction; Astronautics – Systems engineering; Orbital mechanics; Space vehicles – Control systems

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APA (6^th Edition):

Frias, A. (2012). Modeling And Control Of Spacecraft Systems With Coupled Orbital And Attitude Dynamics. (Thesis). Ryerson University. Retrieved from https://digital.library.ryerson.ca/islandora/object/RULA%3A1610

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

Chicago Manual of Style (16^th Edition):

Frias, Alexander. “Modeling And Control Of Spacecraft Systems With Coupled Orbital And Attitude Dynamics.” 2012. Thesis, Ryerson University. Accessed January 21, 2021. https://digital.library.ryerson.ca/islandora/object/RULA%3A1610.

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

MLA Handbook (7^th Edition):

Frias, Alexander. “Modeling And Control Of Spacecraft Systems With Coupled Orbital And Attitude Dynamics.” 2012. Web. 21 Jan 2021.

Vancouver:

Frias A. Modeling And Control Of Spacecraft Systems With Coupled Orbital And Attitude Dynamics. [Internet] [Thesis]. Ryerson University; 2012. [cited 2021 Jan 21]. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A1610.

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

Council of Science Editors:

Frias A. Modeling And Control Of Spacecraft Systems With Coupled Orbital And Attitude Dynamics. [Thesis]. Ryerson University; 2012. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A1610

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

University of Colorado

11. McMahon, Jay Warren. An Analytical Theory for the Perturbative Effect of Solar Radiation Pressure on Natural and Artificial Satellites.

Degree: PhD, Aerospace Engineering Sciences, 2011, University of Colorado

URL: https://scholar.colorado.edu/asen_gradetds/26

► Solar radiation pressure is the largest non-gravitational perturbation for most satellites in the solar system, and can therefore have a significant influence on their… (more)

▼ Solar radiation pressure is the largest non-gravitational perturbation for most satellites in the solar system, and can therefore have a significant influence on their orbital dynamics. This work presents a new method for representing the solar radiation pressure force acting on a satellite, and applies this theory to natural and artificial satellites. The solar radiation pressure acceleration is modeled as a Fourier series which depends on the Sun's location in a body-fixed frame; a new set of Fourier coefficients are derived for every latitude of the Sun in this frame, and the series is expanded in terms of the longitude of the Sun. The secular effects due to the solar radiation pressure perturbations are given analytically through the application of averaging theory when the satellite is in a synchronous orbit. This theory is then applied to binary asteroid systems to explain the Binary YORP effect. Long term predictions of the evolution of the near-Earth asteroid 1999 KW4 are discussed under the influence of solar radiation pressure, J2, and 3rd body gravitational effects from the Sun. Secular effects are shown to remain when the secondary asteroid becomes non-synchronous due to a librational motion. The theory is also applied to Earth orbiting spacecraft, and is shown to be a valuable tool for improved orbit determination. The Fourier series solar radiation pressure model derived here is shown to give comparable results for orbit determination of the GPS IIR-M satellites as JPL's solar radiation pressure model. The theory is also extended to incorporate the effects of the Earth's shadow analytically. This theory is briefly applied to the evolution of orbital debris to explain the assumptions that are necessary in order to use the cannonball model for debris orbit evolution, as is common in the literature. Finally, the averaging theory methodology is applied to a class of Earth orbiting solar sail spacecraft to show the orbital effects when the sails are made to cone at orbit rates in the local horizontal frame. Advisors/Committee Members: Daniel J. Scheeres, Hanspeter Schaub, George Born.

Subjects/Keywords: astrodynamics; BYORP; celestial mechanics; orbital dynamics; orbit determination; solar radiation pressure; Aerospace Engineering; Astrodynamics

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APA (6^th Edition):

McMahon, J. W. (2011). An Analytical Theory for the Perturbative Effect of Solar Radiation Pressure on Natural and Artificial Satellites. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/26

Chicago Manual of Style (16^th Edition):

McMahon, Jay Warren. “An Analytical Theory for the Perturbative Effect of Solar Radiation Pressure on Natural and Artificial Satellites.” 2011. Doctoral Dissertation, University of Colorado. Accessed January 21, 2021. https://scholar.colorado.edu/asen_gradetds/26.

MLA Handbook (7^th Edition):

McMahon, Jay Warren. “An Analytical Theory for the Perturbative Effect of Solar Radiation Pressure on Natural and Artificial Satellites.” 2011. Web. 21 Jan 2021.

Vancouver:

McMahon JW. An Analytical Theory for the Perturbative Effect of Solar Radiation Pressure on Natural and Artificial Satellites. [Internet] [Doctoral dissertation]. University of Colorado; 2011. [cited 2021 Jan 21]. Available from: https://scholar.colorado.edu/asen_gradetds/26.

Council of Science Editors:

McMahon JW. An Analytical Theory for the Perturbative Effect of Solar Radiation Pressure on Natural and Artificial Satellites. [Doctoral Dissertation]. University of Colorado; 2011. Available from: https://scholar.colorado.edu/asen_gradetds/26

12. Azari, Pouyan. An Orbit Control System for UWE-4 Using the High Fidelity Simulation Tool Orekit.

Degree: Electrical and Space Engineering, 2017, Luleå University of Technology

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-61409

►

Cubesats are picosatellites that have a mass of less than 1.3kg and have a shape of acube. As a result of their low cost… (more)

Subjects/Keywords: Orbital mechanics; astrodynamics; small satellites; orbit control; Aerospace Engineering; Rymd- och flygteknik

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APA (6^th Edition):

Azari, P. (2017). An Orbit Control System for UWE-4 Using the High Fidelity Simulation Tool Orekit. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-61409

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

Chicago Manual of Style (16^th Edition):

Azari, Pouyan. “An Orbit Control System for UWE-4 Using the High Fidelity Simulation Tool Orekit.” 2017. Thesis, Luleå University of Technology. Accessed January 21, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-61409.

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

MLA Handbook (7^th Edition):

Azari, Pouyan. “An Orbit Control System for UWE-4 Using the High Fidelity Simulation Tool Orekit.” 2017. Web. 21 Jan 2021.

Vancouver:

Azari P. An Orbit Control System for UWE-4 Using the High Fidelity Simulation Tool Orekit. [Internet] [Thesis]. Luleå University of Technology; 2017. [cited 2021 Jan 21]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-61409.

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

Council of Science Editors:

Azari P. An Orbit Control System for UWE-4 Using the High Fidelity Simulation Tool Orekit. [Thesis]. Luleå University of Technology; 2017. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-61409

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

Iowa State University

13. Wagner, Samuel Arthur. Automated trajectory design for impulsive and low thrust interplanetary mission analysis.

Degree: 2014, Iowa State University

URL: https://lib.dr.iastate.edu/etd/14238

► This dissertation describes a hybrid optimization algorithm that is able to determine optimal trajectories for many complex mission analysis and design orbital mechanics problems. This… (more)

Subjects/Keywords: Aerospace Engineering; Astrodynamics; Genetic Algorithm; low-thrust; MGA; Optimization; Orbital Mechanics; Aerospace Engineering; Applied Mathematics

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APA (6^th Edition):

Wagner, S. A. (2014). Automated trajectory design for impulsive and low thrust interplanetary mission analysis. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/14238

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

Chicago Manual of Style (16^th Edition):

Wagner, Samuel Arthur. “Automated trajectory design for impulsive and low thrust interplanetary mission analysis.” 2014. Thesis, Iowa State University. Accessed January 21, 2021. https://lib.dr.iastate.edu/etd/14238.

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

MLA Handbook (7^th Edition):

Wagner, Samuel Arthur. “Automated trajectory design for impulsive and low thrust interplanetary mission analysis.” 2014. Web. 21 Jan 2021.

Vancouver:

Wagner SA. Automated trajectory design for impulsive and low thrust interplanetary mission analysis. [Internet] [Thesis]. Iowa State University; 2014. [cited 2021 Jan 21]. Available from: https://lib.dr.iastate.edu/etd/14238.

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

Council of Science Editors:

Wagner SA. Automated trajectory design for impulsive and low thrust interplanetary mission analysis. [Thesis]. Iowa State University; 2014. Available from: https://lib.dr.iastate.edu/etd/14238

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

University of Arizona

14. Kidd, John Nocon. Development and Optimization of Low Energy Orbits for Advancing Exploration of the Solar System .

Degree: 2015, University of Arizona

URL: http://hdl.handle.net/10150/560837

► The architecture of a system which enables the cost-effective exploration of the solar system is proposed. Such a system will make use of the benefits… (more)

▼ The architecture of a system which enables the cost-effective exploration of the solar system is proposed. Such a system will make use of the benefits of the natural dynamics represented in the Circular Restricted Three-Body Problem (CRTBP). Additionally, a case study of the first missions which apply the lessons from the CRTBP is examined. The guiding principle of the proposed system is to apply lessons learned from both the Apollo project for deep space exploration and the International Space Station for long term habitation in space as well as modular space vehicle design. From this preliminary system design, a number of missions are outlined. These missions form the basis of an evolvable roadmap to fully develop the infrastructure required for long-term sustained manned exploration of the solar system. This roadmap provides a clear and concise pathway from current exploration capabilities to the current long-term goal of sustained manned exploration of Mars. The primary method employed in designing the staging orbits is the "Single Lunar Swingby", each of the component segment trajectory design processes is explored in detail. Additionally, the method of combining each of these segments together in a larger End-to-End optimizer environment within the General Mission Analysis Tool (GMAT) is introduced, called the Multiple Shooting Method. In particular, a specific Baseline Parking Orbit, or BPO, is chosen and analyzed. This BPO serves as the parking home orbit of any assets not currently in use. A BPO of amplitude (14000, 28000, 6000) kilometers. The BPO has full coverage to both the Earth and the Moon and orbit station-keeping may be conducted at a cost of less than 1 m/s over a 14 year period. This provides a cost-effective platform from which more advanced exploration activities can be based, both robotic and manned. One of the key advanced exploration activities considered is manned exploration of Mars, one of the current long-term goals of NASA. Trajectories from the BPO to Mars and back to Earth are explored and show approximately 50% decrease in required ΔV provided by the spacecraft. Advisors/Committee Members: Furfaro, Roberto (advisor), Head, Larry (committeemember), Gaylor, David (committeemember).

Subjects/Keywords: Interplanetary; Mission Design; Optimization; Orbital Mechanics; Spaceflight Dynamics; Systems & Industrial Engineering; Exploration Architecture

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

APA (6^th Edition):

Kidd, J. N. (2015). Development and Optimization of Low Energy Orbits for Advancing Exploration of the Solar System . (Masters Thesis). University of Arizona. Retrieved from http://hdl.handle.net/10150/560837

Chicago Manual of Style (16^th Edition):

Kidd, John Nocon. “Development and Optimization of Low Energy Orbits for Advancing Exploration of the Solar System .” 2015. Masters Thesis, University of Arizona. Accessed January 21, 2021. http://hdl.handle.net/10150/560837.

MLA Handbook (7^th Edition):

Kidd, John Nocon. “Development and Optimization of Low Energy Orbits for Advancing Exploration of the Solar System .” 2015. Web. 21 Jan 2021.

Vancouver:

Kidd JN. Development and Optimization of Low Energy Orbits for Advancing Exploration of the Solar System . [Internet] [Masters thesis]. University of Arizona; 2015. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/10150/560837.

Council of Science Editors:

Kidd JN. Development and Optimization of Low Energy Orbits for Advancing Exploration of the Solar System . [Masters Thesis]. University of Arizona; 2015. Available from: http://hdl.handle.net/10150/560837

15. Gurgenburan, Goksel. A Methodology to Repair or Deorbit LEO Satellite Constellations.

Degree: MS, Mechanical & Aerospace Engineering, 2011, Old Dominion University

URL: https://digitalcommons.odu.edu/mae_etds/318

► In this thesis, mitigation of space debris is addressed by examining an approach for repair or de-orbit of a specific population of non-functional Low… (more)

Subjects/Keywords: Low Earth Orbit satellites; LEO; Clohessy-Wiltshire equations; Orbital mechanics; Aerospace Engineering

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APA (6^th Edition):

Gurgenburan, G. (2011). A Methodology to Repair or Deorbit LEO Satellite Constellations. (Thesis). Old Dominion University. Retrieved from https://digitalcommons.odu.edu/mae_etds/318

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

Chicago Manual of Style (16^th Edition):

Gurgenburan, Goksel. “A Methodology to Repair or Deorbit LEO Satellite Constellations.” 2011. Thesis, Old Dominion University. Accessed January 21, 2021. https://digitalcommons.odu.edu/mae_etds/318.

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

MLA Handbook (7^th Edition):

Gurgenburan, Goksel. “A Methodology to Repair or Deorbit LEO Satellite Constellations.” 2011. Web. 21 Jan 2021.

Vancouver:

Gurgenburan G. A Methodology to Repair or Deorbit LEO Satellite Constellations. [Internet] [Thesis]. Old Dominion University; 2011. [cited 2021 Jan 21]. Available from: https://digitalcommons.odu.edu/mae_etds/318.

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

Council of Science Editors:

Gurgenburan G. A Methodology to Repair or Deorbit LEO Satellite Constellations. [Thesis]. Old Dominion University; 2011. Available from: https://digitalcommons.odu.edu/mae_etds/318

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

16. Shepard, John. A Preliminary Study Of Leo To Geo Transfers For Inclination Changes Using Libration Point Orbits.

Degree: MS, Space Studies, 2020, University of North Dakota

URL: https://commons.und.edu/theses/3121

► The required change in velocity for a satellite to change inclination has prompted studies of efficient orbital transfers. Modeling the motion of a spacecraft… (more)

Subjects/Keywords: CR3BP; invariant manifold; Libration Point Orbit; low-energy transfer; Lyapunov; orbital mechanics

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APA (6^th Edition):

Shepard, J. (2020). A Preliminary Study Of Leo To Geo Transfers For Inclination Changes Using Libration Point Orbits. (Masters Thesis). University of North Dakota. Retrieved from https://commons.und.edu/theses/3121

Chicago Manual of Style (16^th Edition):

Shepard, John. “A Preliminary Study Of Leo To Geo Transfers For Inclination Changes Using Libration Point Orbits.” 2020. Masters Thesis, University of North Dakota. Accessed January 21, 2021. https://commons.und.edu/theses/3121.

MLA Handbook (7^th Edition):

Shepard, John. “A Preliminary Study Of Leo To Geo Transfers For Inclination Changes Using Libration Point Orbits.” 2020. Web. 21 Jan 2021.

Vancouver:

Shepard J. A Preliminary Study Of Leo To Geo Transfers For Inclination Changes Using Libration Point Orbits. [Internet] [Masters thesis]. University of North Dakota; 2020. [cited 2021 Jan 21]. Available from: https://commons.und.edu/theses/3121.

Council of Science Editors:

Shepard J. A Preliminary Study Of Leo To Geo Transfers For Inclination Changes Using Libration Point Orbits. [Masters Thesis]. University of North Dakota; 2020. Available from: https://commons.und.edu/theses/3121

17. Cognee, Kevin. Hybridization of open photonic resonators : Hybridation de résonateurs photoniques ouverts.

Degree: Docteur es, Lasers, Matière et Nanosciences, 2020, Bordeaux; Universiteit van Amsterdam

URL: http://www.theses.fr/2020BORD0002

►

Le contrôle de l'interaction entre la lumière et la matière est d'une importance capitale dans de nombreuses technologies modernes, avec des applications allant de la… (more)

▼

Le contrôle de l'interaction entre la lumière et la matière est d'une importance capitale dans de nombreuses technologies modernes, avec des applications allant de la détection, aux télécommunications et à l'information quantique. Les résonateurs nanophotoniques permettent d'améliorer cette interaction par le confinement et le stockage du champ lumineux.Cette thèse étudie l'hybridation des modes propres des nano et microrésonateurs, et en particulier les propriétés de résonateurs hybrides composés d'une cavité diélectrique et de nanoantennes plasmoniques. Les résonateurs photoniques présentent toujours des pertes, en particulier par rayonnement, et ainsi, ne peuvent être bien décrits que dans le cadre de la théorie des modes quasi-normaux (quasinormal modes - QNM). Nous confirmons la pertinence de telles théories en étudiant numériquement et expérimentalement la perturbation de cavités diélectriques à facteurs de qualité élevés.Ensuite, nous proposons une théorie permettant d’étudier l'hybridation de plusieurs résonateurs pour ainsi prédire les propriétés de l’ensemble. Dans le cas d’hybrides antenne-cavité, des travaux antérieurs ont démontré le grand potentiel de ce type de résonateurs pour améliorer l'interaction lumière-matière au-delà de ce qui accessible avec leurs composants pris individuellement. Nous montrons ici, par le biais de travaux théoriques et expérimentaux, que ces résonateurs offrent également des degrés de contrôle supplémentaires sur les propriétés de la lumière émise, telles que la directionnalité, ou encore l’émission d’ondes présentant un moment angulaire orbital pur. Enfin, nous étudions les performances de tels résonateurs hybrides dans le cadre de l'optomécanique moléculaire. En effet, nous montrons qu'ils constituent une excellente plateforme pour augmenter la diffusion Raman, tout en offrant des canaux d’excitation et d’émission dont les propriétés peuvent-être contrôlées, pour les signaux de pompe et Raman.

The control of the interaction between light and matter is of paramount importance in many modern technologies, with applications ranging from sensing to telecommunication and quantum information. Nanophotonic resonators allow to enhance this interaction by the storage and confinement of the light field.This thesis studies the hybridization of eigenmodes of nano- and microresonators, and in particular the properties of hybrid resonators composed of a dielectric cavity and plasmonic nanoantennas. Due to their lossy nature, in particular radiation, photonic resonators can only be well described in the framework of quasinormal modes theory (QNM). We confirm the relevance of such theories by investigating the physics of the perturbation of high-Q dielectric cavities aided by numerical and experimental works.Then we propose a theory to study the hybridization of multiple resonators and predict the properties of the ensemble. In the context of antenna-cavity hybrids, previous works have demonstrated the great potential of such resonators to enhance light-matter interaction further than…

Advisors/Committee Members: Lalanne, Philippe (thesis director), Koenderink, Femius (thesis director).

Subjects/Keywords: Modes quasi-Normaux; Hybrides metallo-Dielectriques; Moment orbital angulaire; Opto-Mécanique moléculaire; Coupled modes; Quasi-Normal modes; Orbital angular momentum; Molecular opto-Mechanics

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APA (6^th Edition):

Cognee, K. (2020). Hybridization of open photonic resonators : Hybridation de résonateurs photoniques ouverts. (Doctoral Dissertation). Bordeaux; Universiteit van Amsterdam. Retrieved from http://www.theses.fr/2020BORD0002

Chicago Manual of Style (16^th Edition):

Cognee, Kevin. “Hybridization of open photonic resonators : Hybridation de résonateurs photoniques ouverts.” 2020. Doctoral Dissertation, Bordeaux; Universiteit van Amsterdam. Accessed January 21, 2021. http://www.theses.fr/2020BORD0002.

MLA Handbook (7^th Edition):

Cognee, Kevin. “Hybridization of open photonic resonators : Hybridation de résonateurs photoniques ouverts.” 2020. Web. 21 Jan 2021.

Vancouver:

Cognee K. Hybridization of open photonic resonators : Hybridation de résonateurs photoniques ouverts. [Internet] [Doctoral dissertation]. Bordeaux; Universiteit van Amsterdam; 2020. [cited 2021 Jan 21]. Available from: http://www.theses.fr/2020BORD0002.

Council of Science Editors:

Cognee K. Hybridization of open photonic resonators : Hybridation de résonateurs photoniques ouverts. [Doctoral Dissertation]. Bordeaux; Universiteit van Amsterdam; 2020. Available from: http://www.theses.fr/2020BORD0002

Texas A&M University

18. Read, Julie Louise. Modified Chebyshev Picard Iteration: Integration of Perturbed Motion using Modified Equinoctial Elements.

Degree: PhD, Aerospace Engineering, 2016, Texas A&M University

URL: http://hdl.handle.net/1969.1/159095

► The topic of this dissertation is the fusion of a novel integration method, Modified Chebyshev Picard Iteration (MCPI), with Gauss' Variational Equations using a set… (more)

Subjects/Keywords: Orbital Mechanics; Parallel Processing; Numerical Integration; Modified Chebyshev Picard Iteration; MCPI; Modified Equinoctial Elements; Chebyshev Polynomials

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APA (6^th Edition):

Read, J. L. (2016). Modified Chebyshev Picard Iteration: Integration of Perturbed Motion using Modified Equinoctial Elements. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/159095

Chicago Manual of Style (16^th Edition):

Read, Julie Louise. “Modified Chebyshev Picard Iteration: Integration of Perturbed Motion using Modified Equinoctial Elements.” 2016. Doctoral Dissertation, Texas A&M University. Accessed January 21, 2021. http://hdl.handle.net/1969.1/159095.

MLA Handbook (7^th Edition):

Read, Julie Louise. “Modified Chebyshev Picard Iteration: Integration of Perturbed Motion using Modified Equinoctial Elements.” 2016. Web. 21 Jan 2021.

Vancouver:

Read JL. Modified Chebyshev Picard Iteration: Integration of Perturbed Motion using Modified Equinoctial Elements. [Internet] [Doctoral dissertation]. Texas A&M University; 2016. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/1969.1/159095.

Council of Science Editors:

Read JL. Modified Chebyshev Picard Iteration: Integration of Perturbed Motion using Modified Equinoctial Elements. [Doctoral Dissertation]. Texas A&M University; 2016. Available from: http://hdl.handle.net/1969.1/159095

Penn State University

19. Shank, Brian Steven. Development of an Optimized Lambert Problem Solver for Targeting Elliptical Orbits.

Degree: 2013, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/17560

► This thesis investigates the solution of Lambert’s Problem for targets in elliptical orbits. Preliminary efforts are made in developing a mission design software tool to… (more)

Subjects/Keywords: Lambert's Problem; Pork Chop Plot; ATSV; Visual Data Techniques; Orbital Mechanics; Astrodynamics; Mission Planning; Propulsion Optimization

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APA (6^th Edition):

Shank, B. S. (2013). Development of an Optimized Lambert Problem Solver for Targeting Elliptical Orbits. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/17560

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

Chicago Manual of Style (16^th Edition):

Shank, Brian Steven. “Development of an Optimized Lambert Problem Solver for Targeting Elliptical Orbits.” 2013. Thesis, Penn State University. Accessed January 21, 2021. https://submit-etda.libraries.psu.edu/catalog/17560.

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

MLA Handbook (7^th Edition):

Shank, Brian Steven. “Development of an Optimized Lambert Problem Solver for Targeting Elliptical Orbits.” 2013. Web. 21 Jan 2021.

Vancouver:

Shank BS. Development of an Optimized Lambert Problem Solver for Targeting Elliptical Orbits. [Internet] [Thesis]. Penn State University; 2013. [cited 2021 Jan 21]. Available from: https://submit-etda.libraries.psu.edu/catalog/17560.

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

Council of Science Editors:

Shank BS. Development of an Optimized Lambert Problem Solver for Targeting Elliptical Orbits. [Thesis]. Penn State University; 2013. Available from: https://submit-etda.libraries.psu.edu/catalog/17560

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

University of Adelaide

20. Shimmin, Rogan. Trajectory design for a very-low-thrust lunar mission.

Degree: 2013, University of Adelaide

URL: http://hdl.handle.net/2440/80842

► The University of Stuttgart is conducting a research program to build a succession of small satellites. The ultimate goal of this program is to build… (more)

▼ The University of Stuttgart is conducting a research program to build a succession of small satellites. The ultimate goal of this program is to build and launch a craft named Lunar Mission BW-1 (after the federal state that Stuttgart is situated in, Baden-Wurttemberg) into lunar orbit, for eventual impact with the Moon. As with the majority of space missions, launch cost is a severely limiting factor so it is necessary to carefully plan the trajectory before launch, to ensure lunar capture and minimise the amount of fuel needed by the spacecraft. This thesis outlines work conducted to find a robust fuel-optimal trajectory for Lunar Mission BW-1 to reach the Moon. Several unique aspects of this craft require a novel approach to that optimisation. Firstly, the spacecraft uses a new low-cost propulsion system, severely limiting manoeuvrability and accessibility of transfer trajectories. Secondly, to reduce the mass and complexity of moving parts, the solar panels are fixed to the body; consequently, the craft must rotate itself to point its solar panels towards the Sun to recharge. No thrusting can occur during this time. This magnifies the effect of the third design decision, which is to restrict the dry mass of the craft by giving it very little on-board power storage. After approximately an hour of accelerating it is expected to need to coast for several hours to recharge its batteries, resulting in a relatively high frequency stop-go-stop thrust profile. Due to these constraints, the trajectory optimisation is one of the most complex ever attempted. Since the craft will be built and launched, many simplifications made in purely theoretical studies could not be utilised, such as neglecting the weaker forces acting on the spacecraft in cis-lunar space. The very low thrust results in very long transfer times, during which even small magnitude forces acting on the spacecraft can significantly perturb its trajectory. However, including these forces creates non-linearities in the equations of motion associated with spacecraft trajectories, limiting the optimisation methods that could be used, and increasing computational complexity. Optimisation methods for low-thrust spacecraft trajectories have been the subject of much research, but most studies conclude that knowledge is still lacking in this area. Furthermore, many optimisation methods investigated in existing literature are incompatible with the intermittent thrust profile required by the Lunar Mission BW-1 thrusters. For this reason it was necessary to thoroughly review available optimisation methods and determine which may be adapted to this scenario. The resulting optimisation method was applied to the Lunar Mission BW-1 scenario to determine an efficient thrusting profile that will get the craft to the Moon. It was found that very few established optimisation algorithms can support the number of variables required for such a complex, long duration trajectory. The Sparse Optimal Control Software (SOCS) marketed by The Boeing Corporation was used via an interface… Advisors/Committee Members: Cazzolato, Benjamin Seth (advisor), Tetlow, Matthew Robert (advisor), School of Mechanical Engineering (school).

Subjects/Keywords: trajectory optimisation; trajectory design; orbital mechanics; space; spacecraft; simulation; modelling; low thrust; electric propulsion; ion thrusters

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APA (6^th Edition):

Shimmin, R. (2013). Trajectory design for a very-low-thrust lunar mission. (Thesis). University of Adelaide. Retrieved from http://hdl.handle.net/2440/80842

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

Chicago Manual of Style (16^th Edition):

Shimmin, Rogan. “Trajectory design for a very-low-thrust lunar mission.” 2013. Thesis, University of Adelaide. Accessed January 21, 2021. http://hdl.handle.net/2440/80842.

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

MLA Handbook (7^th Edition):

Shimmin, Rogan. “Trajectory design for a very-low-thrust lunar mission.” 2013. Web. 21 Jan 2021.

Vancouver:

Shimmin R. Trajectory design for a very-low-thrust lunar mission. [Internet] [Thesis]. University of Adelaide; 2013. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/2440/80842.

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

Council of Science Editors:

Shimmin R. Trajectory design for a very-low-thrust lunar mission. [Thesis]. University of Adelaide; 2013. Available from: http://hdl.handle.net/2440/80842

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

Delft University of Technology

21. Molenaar, S. (author). Optimization of interplanetary trajectories with deep space maneuvers - Model development and application to a Uranus orbiter mission.

Degree: 2009, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:8d44eef0-1da0-47fa-b44e-cad4ab3e6a46

Astrodynamics and Satellite Systems

Aerospace Engineering

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

Subjects/Keywords: Deep Space Maneuvers; Orbital Mechanics; Genetic Algorithm Optimization

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APA (6^th Edition):

Molenaar, S. (. (2009). Optimization of interplanetary trajectories with deep space maneuvers - Model development and application to a Uranus orbiter mission. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:8d44eef0-1da0-47fa-b44e-cad4ab3e6a46

Chicago Manual of Style (16^th Edition):

Molenaar, S (author). “Optimization of interplanetary trajectories with deep space maneuvers - Model development and application to a Uranus orbiter mission.” 2009. Masters Thesis, Delft University of Technology. Accessed January 21, 2021. http://resolver.tudelft.nl/uuid:8d44eef0-1da0-47fa-b44e-cad4ab3e6a46.

MLA Handbook (7^th Edition):

Molenaar, S (author). “Optimization of interplanetary trajectories with deep space maneuvers - Model development and application to a Uranus orbiter mission.” 2009. Web. 21 Jan 2021.

Vancouver:

Molenaar S(. Optimization of interplanetary trajectories with deep space maneuvers - Model development and application to a Uranus orbiter mission. [Internet] [Masters thesis]. Delft University of Technology; 2009. [cited 2021 Jan 21]. Available from: http://resolver.tudelft.nl/uuid:8d44eef0-1da0-47fa-b44e-cad4ab3e6a46.

Council of Science Editors:

Molenaar S(. Optimization of interplanetary trajectories with deep space maneuvers - Model development and application to a Uranus orbiter mission. [Masters Thesis]. Delft University of Technology; 2009. Available from: http://resolver.tudelft.nl/uuid:8d44eef0-1da0-47fa-b44e-cad4ab3e6a46

22. Pousse, Alexandre. Le quasi-satellites et autres configurations remarquables en résonance co-orbitale : Around quasi-satellites and remarkable configurations in the co-orbital resonance.

Degree: Docteur es, Mécanique céleste, 2016, Paris Sciences et Lettres (ComUE)

URL: http://www.theses.fr/2016PSLEO006

►

L'ensemble des travaux menés au cours de cette thèse concerne l'étude de la résonance co-orbitale. Ce domaine de trajectoires particulières, où un astéroïde et une… (more)

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L'ensemble des travaux menés au cours de cette thèse concerne l'étude de la résonance co-orbitale. Ce domaine de trajectoires particulières, où un astéroïde et une planète gravitent autour du Soleil avec la même période de révolution, possède une dynamique très riche liée aux célèbres configurations équilatérales de Lagrange, L4 et L5, ainsi qu'aux configurations alignées de Euler, L1, L2 et L3. Un exemple majeur dans le système solaire est donné par les astéroïdes « troyens » qui accompagnent Jupiter au voisinage des équilibres L4 et L5. Une deuxième configuration étonnante est donnée par les satellites Janus et Épiméthée qui gravitent autour de la planète Saturne ; suite à la forme décrite par la trajectoire d’un des satellites dans un repère tournant avec l’autre, la dynamique résultante est appelée « fer-à-cheval ». Un nouveau type de dynamique a été récemment misen évidence dans le contexte de la résonance coorbitale : les « quasi-satellites ». Il s’agit de configurations remarquables où, dans un repère tournant avec la planète, la trajectoire de l’astéroïde correspond à celle d’un satellite rétrograde. Des astéroïdes accompagnant les planètes Venus, Jupiter et la Terre ont notamment été observés dans ces configurations. La dynamique des quasi-satellites possède un grand intérêt, pas seulement parce qu’elle relie les différents domaines de la résonance co-orbitale (voir les travaux de Namouni, 1999) mais aussi parce qu’elle semble faire le pont entre les notions de satellisation et celles de trajectoires héliocentriques. Cependant, bien que le terme « quasi-satellite" soit devenu dominant dans la communauté de mécanique céleste, certains auteurs utilisent plutôt la terminologie « satellite rétrograde » révélant ainsi une ambiguïté sur la définition de ces trajectoires. Les récentes découvertes autour des exo-planètes ont motivé le développement de travaux concernant la résonance co-orbitale dans le problème des trois corps planétaire. Dans ce contexte Giuppone et al. (2010) ont mis en évidence (par une méthode numérique) les quasisatellites ainsi que des nouvelles familles de configurations remarquables : les orbites « anti-Lagrange ». La troisième partie de thèse présente alors une méthode analytique pour l'étude planétaire, permettant de révéler analytiquement les orbites anti-Lagrange ainsi qu'une esquisse d'étude des quasisatellites en adaptant à ce contexte plus général la méthode présentée dans la seconde partie. Pour ces raisons, la première partie de cette thèse a consisté à clarifier la définition de ces orbites en revisitant le cas circulaire-plan (trajectoires coplanaires avec la planète qui gravite sur une orbite circulaire) dans le cadre du problème moyen. Dans la deuxième partie de cette thèse, nous avons développé une méthode analytique apte à explorer le domaine des quasi-satellites dans le cadre du problème moyen. Nous avons réalisé cette exploration dans le cas circulaire-plan et proposé une extension aux cas excentrique-plan et circulaire-spatial.

This work of thesis focuses on the study of…

Advisors/Committee Members: Robutel, Philippe (thesis director), Vienne, Alain (thesis director).

Subjects/Keywords: Mécanique céleste; Résonance co-Orbitale; Problème à trois corps; Celestial mechanics; Co-Orbital resonance; Three-Body problem; 520

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APA (6^th Edition):

Pousse, A. (2016). Le quasi-satellites et autres configurations remarquables en résonance co-orbitale : Around quasi-satellites and remarkable configurations in the co-orbital resonance. (Doctoral Dissertation). Paris Sciences et Lettres (ComUE). Retrieved from http://www.theses.fr/2016PSLEO006

Chicago Manual of Style (16^th Edition):

Pousse, Alexandre. “Le quasi-satellites et autres configurations remarquables en résonance co-orbitale : Around quasi-satellites and remarkable configurations in the co-orbital resonance.” 2016. Doctoral Dissertation, Paris Sciences et Lettres (ComUE). Accessed January 21, 2021. http://www.theses.fr/2016PSLEO006.

MLA Handbook (7^th Edition):

Pousse, Alexandre. “Le quasi-satellites et autres configurations remarquables en résonance co-orbitale : Around quasi-satellites and remarkable configurations in the co-orbital resonance.” 2016. Web. 21 Jan 2021.

Vancouver:

Pousse A. Le quasi-satellites et autres configurations remarquables en résonance co-orbitale : Around quasi-satellites and remarkable configurations in the co-orbital resonance. [Internet] [Doctoral dissertation]. Paris Sciences et Lettres (ComUE); 2016. [cited 2021 Jan 21]. Available from: http://www.theses.fr/2016PSLEO006.

Council of Science Editors:

Pousse A. Le quasi-satellites et autres configurations remarquables en résonance co-orbitale : Around quasi-satellites and remarkable configurations in the co-orbital resonance. [Doctoral Dissertation]. Paris Sciences et Lettres (ComUE); 2016. Available from: http://www.theses.fr/2016PSLEO006

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

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

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

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

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

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

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

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

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APA (6^th Edition):

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

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

Chicago Manual of Style (16^th Edition):

Skoulidou, Despoina. “Dynamical evolution of artificial satellites and space debris in near earth region.” 2019. Thesis, Aristotle University Of Thessaloniki (AUTH); Αριστοτέλειο Πανεπιστήμιο Θεσσαλονίκης (ΑΠΘ). Accessed January 21, 2021. http://hdl.handle.net/10442/hedi/46490.

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

MLA Handbook (7^th Edition):

Skoulidou, Despoina. “Dynamical evolution of artificial satellites and space debris in near earth region.” 2019. Web. 21 Jan 2021.

Vancouver:

Skoulidou D. Dynamical evolution of artificial satellites and space debris in near earth region. [Internet] [Thesis]. Aristotle University Of Thessaloniki (AUTH); Αριστοτέλειο Πανεπιστήμιο Θεσσαλονίκης (ΑΠΘ); 2019. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/10442/hedi/46490.

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

Council of Science Editors:

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

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

Rutgers University

24. Erb, Michael Philip, 1985-. The response of radiative feedbacks, equatorial Pacific seasonality, and wetlands to orbital forcing in model simulations.

Degree: Atmospheric Science, 2014, Rutgers University

URL: https://rucore.libraries.rutgers.edu/rutgers-lib/42382/

Subjects/Keywords: Orbital mechanics; Radiative forcing; Climatic changes – Research

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APA (6^th Edition):

Erb, Michael Philip, 1. (2014). The response of radiative feedbacks, equatorial Pacific seasonality, and wetlands to orbital forcing in model simulations. (Thesis). Rutgers University. Retrieved from https://rucore.libraries.rutgers.edu/rutgers-lib/42382/

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

Chicago Manual of Style (16^th Edition):

Erb, Michael Philip, 1985-. “The response of radiative feedbacks, equatorial Pacific seasonality, and wetlands to orbital forcing in model simulations.” 2014. Thesis, Rutgers University. Accessed January 21, 2021. https://rucore.libraries.rutgers.edu/rutgers-lib/42382/.

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

MLA Handbook (7^th Edition):

Erb, Michael Philip, 1985-. “The response of radiative feedbacks, equatorial Pacific seasonality, and wetlands to orbital forcing in model simulations.” 2014. Web. 21 Jan 2021.

Vancouver:

Erb, Michael Philip 1. The response of radiative feedbacks, equatorial Pacific seasonality, and wetlands to orbital forcing in model simulations. [Internet] [Thesis]. Rutgers University; 2014. [cited 2021 Jan 21]. Available from: https://rucore.libraries.rutgers.edu/rutgers-lib/42382/.

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

Council of Science Editors:

Erb, Michael Philip 1. The response of radiative feedbacks, equatorial Pacific seasonality, and wetlands to orbital forcing in model simulations. [Thesis]. Rutgers University; 2014. Available from: https://rucore.libraries.rutgers.edu/rutgers-lib/42382/

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

The Ohio State University

25. Jedrey, Richard M. Development of a Discretized Model for the Restricted Three-Body Problem.

Degree: MS, Aero/Astro Engineering, 2011, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu1306856595

► Spacecraft trajectory design is a science that requires high precision with little error. One of the most classic trajectory design problems is the restricted three-body… (more)

▼ Spacecraft trajectory design is a science that requires high precision with little error. One of the most classic trajectory design problems is the restricted three-body problem. Two methods to develop the trajectory of a spacecraft under the influence of two celestial bodies are through the use of the equations of motion, and the patched-conic approximation. Popular tools such as MATLAB can be used to solve the equations of motion if great care is taken when selecting an ODE solver since the results are dramatically different between different solvers. As a result, these tools aren’t very robust and can create significant errors, so a different approach must be used for generalized scenarios when an exact solution for comparison is unavailable. The patched-conic approximation can be easily used in a program such as MATLAB, but its exclusion of one of the two celestial bodies at every point in the trajectory creates drawbacks and significant errors. To avoid the errors that exist when using the patched-conic approach, research was put into the development of a simple model that could propagate a spacecraft’s trajectory under the effect of two celestial bodies while being robust enough to code and solve in a widely available program such as MATLAB. This model acts as a modification to the patched-conic approach. Throughout the trajectory the effect of the primary celestial body of the system on the spacecraft was calculated, as in the patched-conic approach, however unlike the patched-conic approach this effect is not ignored when the spacecraft reaches the secondary body’s sphere of influence. Furthermore, the effect of the secondary body was also considered even when the spacecraft is outside the secondary body’s sphere of influence. Then, by applying a weighted average to the spacecraft’s radius and velocity components respective to each celestial body, an updated state would be created that would allow the model to accurately propagate the trajectory. This would be compared to a numerically generated ‘exact’ solution to determine the errors. Algorithms that propagate the spacecraft’s trajectory out with respect to both celestial bodies were created and tested, including the propagation of the secondary celestial body’s orbit itself. A scheme based on the geometry was used in an attempt to combine the spacecraft’s states with respect to both celestial bodies using a weighted average. This scheme was tested at multiple points throughout the trajectory using a variety of weights, but no attempts were met with any success. However, the routines propagating the trajectories of the celestial bodies and spacecraft were proven to work correctly, and an initial foundation in creating a scheme to combine the spacecraft’s state has been laid out. Advisors/Committee Members: Oz, Hayrani (Advisor).

Subjects/Keywords: Aerospace Engineering; Engineering; orbital mechanics; spacecraft trajectories; three-body problem; three-body model; n-body problem; n-body model; discretized spacecraft

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

APA (6^th Edition):

Jedrey, R. M. (2011). Development of a Discretized Model for the Restricted Three-Body Problem. (Masters Thesis). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1306856595

Chicago Manual of Style (16^th Edition):

Jedrey, Richard M. “Development of a Discretized Model for the Restricted Three-Body Problem.” 2011. Masters Thesis, The Ohio State University. Accessed January 21, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1306856595.

MLA Handbook (7^th Edition):

Jedrey, Richard M. “Development of a Discretized Model for the Restricted Three-Body Problem.” 2011. Web. 21 Jan 2021.

Vancouver:

Jedrey RM. Development of a Discretized Model for the Restricted Three-Body Problem. [Internet] [Masters thesis]. The Ohio State University; 2011. [cited 2021 Jan 21]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1306856595.

Council of Science Editors:

Jedrey RM. Development of a Discretized Model for the Restricted Three-Body Problem. [Masters Thesis]. The Ohio State University; 2011. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1306856595

University of Cincinnati

26. SYED, ANEES. COLLISON PREDICTION AND AVOIDANCE OF SATELLITES IN FORMATION.

Degree: MS, Engineering : Mechanical Engineering, 2004, University of Cincinnati

URL: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1100034591

► Satellites flying in formation has been the focus of current research. Sometimes,there are issues with the amount of information available about the satellites. Due to… (more)

Subjects/Keywords: satellites; satellite formations; formation control; orbital mechanics

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APA (6^th Edition):

SYED, A. (2004). COLLISON PREDICTION AND AVOIDANCE OF SATELLITES IN FORMATION. (Masters Thesis). University of Cincinnati. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=ucin1100034591

Chicago Manual of Style (16^th Edition):

SYED, ANEES. “COLLISON PREDICTION AND AVOIDANCE OF SATELLITES IN FORMATION.” 2004. Masters Thesis, University of Cincinnati. Accessed January 21, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1100034591.

MLA Handbook (7^th Edition):

SYED, ANEES. “COLLISON PREDICTION AND AVOIDANCE OF SATELLITES IN FORMATION.” 2004. Web. 21 Jan 2021.

Vancouver:

SYED A. COLLISON PREDICTION AND AVOIDANCE OF SATELLITES IN FORMATION. [Internet] [Masters thesis]. University of Cincinnati; 2004. [cited 2021 Jan 21]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1100034591.

Council of Science Editors:

SYED A. COLLISON PREDICTION AND AVOIDANCE OF SATELLITES IN FORMATION. [Masters Thesis]. University of Cincinnati; 2004. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1100034591

Brno University of Technology

27. Stopka, Jiří. Program pro předpověď kolize Země s blízkými vesmírnými tělesy: Predictive software for Earth collision with Near Eartch Objects.

Degree: 2020, Brno University of Technology

URL: http://hdl.handle.net/11012/192867

► Aim of this bachelor’s thesis is to research and discuss the basics of orbital mechanics and their application on a real problem. The application of… (more)

Subjects/Keywords: Země; blízká vesmírná tělesa; Sluneční soustava; orbitální mechanika; Keplerovy zákony; Newtonův gravitační zákon; asteroidy; obežná dráha; kolize; elementy dráhy; Earth; Near-Earth Objects; Solar system; Orbital mechanics; Kepler’s laws; Newton’s law of universal gravitation; asteroids; orbit; collision; orbital elements

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APA (6^th Edition):

Stopka, J. (2020). Program pro předpověď kolize Země s blízkými vesmírnými tělesy: Predictive software for Earth collision with Near Eartch Objects. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/192867

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

Chicago Manual of Style (16^th Edition):

Stopka, Jiří. “Program pro předpověď kolize Země s blízkými vesmírnými tělesy: Predictive software for Earth collision with Near Eartch Objects.” 2020. Thesis, Brno University of Technology. Accessed January 21, 2021. http://hdl.handle.net/11012/192867.

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

MLA Handbook (7^th Edition):

Stopka, Jiří. “Program pro předpověď kolize Země s blízkými vesmírnými tělesy: Predictive software for Earth collision with Near Eartch Objects.” 2020. Web. 21 Jan 2021.

Vancouver:

Stopka J. Program pro předpověď kolize Země s blízkými vesmírnými tělesy: Predictive software for Earth collision with Near Eartch Objects. [Internet] [Thesis]. Brno University of Technology; 2020. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/11012/192867.

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

Council of Science Editors:

Stopka J. Program pro předpověď kolize Země s blízkými vesmírnými tělesy: Predictive software for Earth collision with Near Eartch Objects. [Thesis]. Brno University of Technology; 2020. Available from: http://hdl.handle.net/11012/192867

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

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

Degree: MS, Aerospace Engineering, 2013, Cal Poly

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

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

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

…overview of the orbital path of STK’s simulation and CDPROP’s simulation. STK is in blue while… …6.9 xi Chapter 1 Introduction and Background In terms of the space environment, orbital… …debris is a present and future hazard to all Earth space operations. Orbital debris consists of… …collisions also contribute to the present population. Orbital debris’ time in orbit is dependent on… …the orbital altitude. Debris in lower orbits often reenter within several years to decades…

10 more images…

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APA (6^th Edition):

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

Chicago Manual of Style (16^th Edition):

Diaz, Christina R. “A STUDY OF THE COLLISIONAL EVOLUTION OF ORBITAL DEBRIS IN GEOPOTENTIAL WELLS AND GEO DISPOSAL ORBITS.” 2013. Masters Thesis, Cal Poly. Accessed January 21, 2021. https://digitalcommons.calpoly.edu/theses/1063 ; 10.15368/theses.2013.157.

MLA Handbook (7^th Edition):

Diaz, Christina R. “A STUDY OF THE COLLISIONAL EVOLUTION OF ORBITAL DEBRIS IN GEOPOTENTIAL WELLS AND GEO DISPOSAL ORBITS.” 2013. Web. 21 Jan 2021.

Vancouver:

Diaz CR. A STUDY OF THE COLLISIONAL EVOLUTION OF ORBITAL DEBRIS IN GEOPOTENTIAL WELLS AND GEO DISPOSAL ORBITS. [Internet] [Masters thesis]. Cal Poly; 2013. [cited 2021 Jan 21]. Available from: https://digitalcommons.calpoly.edu/theses/1063 ; 10.15368/theses.2013.157.

Council of Science Editors:

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

Texas A&M University

29. Bourgeois, Scott K. Rock-Around Orbits.

Degree: MS, Aerospace Engineering, 2010, Texas A&M University

URL: http://hdl.handle.net/1969.1/ETD-TAMU-2009-12-7473

► The ability to observe resident space objects (RSOs) is a necessary requirement for space situational awareness. While objects in a Low-Earth Orbit are easily ob-… (more)

▼ The ability to observe resident space objects (RSOs) is a necessary requirement for space situational awareness. While objects in a Low-Earth Orbit are easily ob- servable by ground-based sensors, diffculties arise when trying to monitor objects with larger orbits far above the Earth's surface, e.g. a Geostationary Orbit. Camera systems mounted on satellites can provide an eff ective way to observe these objects. Using a satellite with a speci c orbit relative to the RSO's orbit, one can passively observe all the objects that share the RSO's orbit over a given time without active maneuvering. An orbit can be defi ned by ve parameters: semi-major axis, eccentricity, right ascension of ascending node, inclination, and argument of perigee (a; e; ; i; !). Using these parameters, one can create an orbit that will surround the target orbit allowing the satellite in the Rock-Around Orbit (RAO) orbit to have a 360 degree view of RSOs in the target orbit. The RAO orbit can be applied to any circular or elliptical target orbit; and for any target orbit, there are many possible RAO orbits. Therefore, diff erent methods are required to narrow down the selection of RAO orbits. These methods use distance limitations, time requirements, orbit perturbations, and other factors to limit the orbit selections. The first step is to determine the range of RAO semi-major axes for any given target orbit by ensuring the RAO orbit does not exceed a prescribed maximum al- lowable distance, dmax from the target orbit. It is then necessary to determine the eccentricity range for each possible RAO semi-major axis. This is done by ensuring the RAO still does not exceed dmax but also ensuring that the RAO orbit travels inside and outside of the target orbit. This comprises one half of the rock-around motion. The final step is to determine the inclination of the RAO orbit. Only a small inclination different from that of the target orbit is required to complete the rock-around motion while the maximum inclination is found by making sure the RAO orbit does not exceed dmax. It is then important to consider orbit perturbations, since they can destroy the synchronization between the RAO and target orbit. By examining the e ffects of the linear J2 perturbations on the right ascension of ascending node and argument of perigee, the correct semi-major axis, eccentricity, and inclination can be chosen to minimize the amount of fuel required for station keeping. The optimal values can be found by finding the Delta v needed for di fferent combinations of the variables and then choosing the values that provide the minimum Delta v. For any target orbit, there are multiple RAO orbit possibilities that can provide 360 degree coverage of a target orbit. Even after eliminating some of them based on the methods already described, there are still many possibilities. The rest of the elimination process would then be based on the mission requirements which could be the range of an on-board sensor, the thruster or reaction wheel controls, or any other number of… Advisors/Committee Members: Mortari, Daniele (advisor), Hyland, David (committee member), Pollock, Tom (committee member), Rojas, Maurice (committee member).

Subjects/Keywords: orbit; surveillance; orbital; dynamics; mechanics; geo; geostationary; geosynchronous; rock around; rock-around

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APA (6^th Edition):

Bourgeois, S. K. (2010). Rock-Around Orbits. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-2009-12-7473

Chicago Manual of Style (16^th Edition):

Bourgeois, Scott K. “Rock-Around Orbits.” 2010. Masters Thesis, Texas A&M University. Accessed January 21, 2021. http://hdl.handle.net/1969.1/ETD-TAMU-2009-12-7473.

MLA Handbook (7^th Edition):

Bourgeois, Scott K. “Rock-Around Orbits.” 2010. Web. 21 Jan 2021.

Vancouver:

Bourgeois SK. Rock-Around Orbits. [Internet] [Masters thesis]. Texas A&M University; 2010. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2009-12-7473.

Council of Science Editors:

Bourgeois SK. Rock-Around Orbits. [Masters Thesis]. Texas A&M University; 2010. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2009-12-7473

University of Houston

30. Nallapu, Raviteja 1989-. Orbit Propagation via MRQ Sphere Technique.

Degree: MS, Aerospace Engineering, 2012, University of Houston

URL: http://hdl.handle.net/10657/765

► The Multi-Resolution Quadrature (MRQ) Sphere model, is a newly developed multi- resolution gravity model designed to estimate the gravity fields of arbitrary shaped space bodies,… (more)

Subjects/Keywords: Orbit Propagation; Gravity Estimation; MRQ-Sphere; Spherical harmonics; LAGEOS-II; GPS BIIA-10; Cartesian Formulation; Kepplerian elements; Gravity Potential; Orbital Mechanics; Aerospace engineering

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

APA (6^th Edition):

Nallapu, R. 1. (2012). Orbit Propagation via MRQ Sphere Technique. (Masters Thesis). University of Houston. Retrieved from http://hdl.handle.net/10657/765

Chicago Manual of Style (16^th Edition):

Nallapu, Raviteja 1989-. “Orbit Propagation via MRQ Sphere Technique.” 2012. Masters Thesis, University of Houston. Accessed January 21, 2021. http://hdl.handle.net/10657/765.

MLA Handbook (7^th Edition):

Nallapu, Raviteja 1989-. “Orbit Propagation via MRQ Sphere Technique.” 2012. Web. 21 Jan 2021.

Vancouver:

Nallapu R1. Orbit Propagation via MRQ Sphere Technique. [Internet] [Masters thesis]. University of Houston; 2012. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/10657/765.

Council of Science Editors:

Nallapu R1. Orbit Propagation via MRQ Sphere Technique. [Masters Thesis]. University of Houston; 2012. Available from: http://hdl.handle.net/10657/765

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