| 1. |
- Bazzocchi, Michael C. F., et al.
(author)
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An Assessment of Multiple Spacecraft Formation for Asteroid Redirection
- 2016
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In: Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan. - Tokyo : Japan Society for Aeronautical and Space Sciences. - 1884-0485. ; 14:ists30, s. Pk_137-Pk_146
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Journal article (peer-reviewed)
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| 2. |
- Bazzocchi, Michael C. F., et al.
(author)
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Application of asteroid redirection methods to orbital debris removal
- 2016
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In: 2016 IEEE Aerospace Conference. - Piscataway, NJ : IEEE Communications Society. - 9781467376761
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Conference paper (peer-reviewed)abstract
- This paper discusses the applicability of some of the asteroid redirection methods, prominently studied in the literature, to orbital debris removal. The tasks of asteroid redirection and orbital debris removal share the common goal of controlled redirection of an uncooperative target. Three asteroid redirection methods are systematically compared and analyzed to assess their viability for an orbital debris reentry mission, i.e., ion beam shepherd, laser sublimation, and tugboat. These methods are investigated in terms of the characteristics of the orbital debris population and based on the major criteria for mission design of controlled reentry of uncooperative objects. In addition, the uncertainty intrinsic to the orbital debris population is quantified through the use of a Monte Carlo simulation, which provides insight into the robustness of the methods for various ranges of orbital debris. The Analytical Hierarchy Process will be employed to assess the viability of each method in a logically consistent fashion, namely, through aggregation of the relative preference (of each method) and relative importance (of each criterion). The advantages and drawbacks of each redirection method are discussed in light of the assessment results for orbital debris reentry
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| 3. |
- Bazzocchi, Michael C.F., et al.
(author)
-
Comparative analysis of redirection methods for asteroid resource exploitation
- 2016
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In: Acta Astronautica. - : Elsevier BV. - 0094-5765 .- 1879-2030. ; 120, s. 1-19
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Journal article (peer-reviewed)abstract
- An in-depth analysis and systematic comparison of asteroid redirection methods is performed within a resource exploitation framework using different assessment mechanisms. Through this framework, mission objectives and constraints are specified for the redirection of an asteroid from a near-Earth orbit to a stable orbit in the Earth-Moon system. The paper provides a detailed investigation of five redirection methods, i.e., ion beam, tugboat, gravity tractor, laser sublimation, and mass ejector, with respect to their capabilities for a redirection mission. A set of mission level criteria are utilized to assess the performance of each redirection method, and the means of assigning attributes to each criterion is discussed in detail. In addition, the uncertainty in physical characteristics of the asteroid population is quantified through the use of Monte Carlo analysis. The Monte Carlo simulation provides insight into the performance robustness of the redirection methods with respect to the targeted asteroid range. Lastly, the attributes for each redirection method are aggregated using three different multicriteria assessment approaches, i.e., the analytical hierarchy process, a utility-based approach, and a fuzzy aggregation mechanism. The results of each assessment approach as well as recommendations for further studies are discussed in detail.
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| 4. |
- Bazzocchi, Michael C. F., et al.
(author)
-
Low-thrust orbit transfer of Arjuna-type asteroids
- 2016
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In: AIAA/AAS Astrodynamics Specialist Conference, 2016. - Reston, Virginia : American Institute of Aeronautics and Astronautics. - 9781624104459
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Conference paper (peer-reviewed)abstract
- This paper investigates the accessible low-thrust transfer trajectories for a near-Earth asteroid transfer mission. The target asteroids considered are Arjuna type asteroids, which are characterized by their Earth-like orbital paths including low-eccentricity and low-inclination. The asteroid range is characterized by specific semi-major axes and transfer angles to provide an overall assessment of the potential Arjuna transfer domain. A single hovering ion beam spacecraft is employed for the task of asteroid redirection. The method utilizes a continuous thrust over the duration of the transfer maneuver to redirect the asteroid to an Earth bound orbit. The transfer model employs a minimized form of Gauss's variational equations to determine the available trajectories for asteroid redirection. The transfer model employs, in addition to the aforementioned orbital equations, spacecraft thruster and sizing metrics, as well as mission cost analysis formulae. The system parameters and orbital transfer paths are assessed with regards to key mission parameters, namely, timeframe for redirection, number of orbital revolutions, system mass, propellant mass, thrust, power, system cost, and financial return rate
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